УПЛОТНЕНИЕ МЕЖДУ ВРАЩАЮЩИМСЯ КОМПОНЕНТОМ И НЕПОДВИЖНЫМ КОМПОНЕНТОМ И ПАРОВОЙ САЛЬНИКОВЫЙ ЗАТВОР В ТУРБИНЕ, ИСПОЛЬЗУЮЩИЙ УКАЗАННОЕ УПЛОТНЕНИЕ

Изобретение предназначено для уплотнения паровых турбин. Паровой сальниковый затвор включает впускную спиральную камеру для пара и откачивающую спиральную камеру для пара, разнесенные по оси на расстояние друг от друга, определяющие области высокого и низкого давления. Корпус уплотнения расположен между областями и включает пару щеточных уплотнений, разнесенных по оси на расстояние друг от друга. В промежутке между щеточными уплотнениями находится ячеистое уплотнение. Гибридная комбинация щеточного уплотнения и ячеистого уплотнения снижает до минимума утечку пара между областями высокого и низкого давления и устраняет возможность вызываемого теплом повреждения ротора, в то же время оптимизируя характеристику утечки уплотнения. 2 н. и 8 з.п. ф-лы, 5 ил.

ТУРБИНА С О ОБЕСПЕЧИВАЮЩЕЙ УПЛОТНЕНИЕ И ЛАМИНАРНОЕ ТЕЧЕНИЕ КОНФИГУРАЦИЕЙ ТРАЕКТОРИИ ПОТОКА

Турбина содержит ротор, на котором закреплено множество рабочих лопаток. Расположенные на расстоянии друг от друга в аксиальном направлении группы сопел имеют аэродинамические поверхности и внутренние и наружные бандажи на их противоположных концах. Рабочие лопатки имеют ласточкины хвосты и площадки вдоль радиально внутренних концов рабочих лопаток. Площадки, аэродинамические поверхности, внутренние и наружные бандажи частично определяют траекторию потока для потока текучей среды через турбину. На ласточкиных хвостах образованы выступающие элементы, проходящие по существу в аксиальном направлении в сторону одной из указанных групп сопел вдоль мест, расположенных радиально внутри по отношению к площадкам. На соплах из одной группы сопел предусмотрены зубцы лабиринтных уплотнений, образующие вместе с выступающими элементами уплотнение, предназначенное для уменьшения потока утечек с траектории потока в проточную часть между одним рабочим колесом и одной группой сопел. Передние края площадок ...

УЗЕЛ УПЛОТНЕНИЯ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Изобретение относится к узлу уплотнения для использования в газотурбинном двигателе. Узел уплотнения между полостью диска и путепроводом горячего газа секции турбины включает в себя неподвижный узел 12 направляющих лопаток 14 и вращающийся узел 18 рабочих лопаток 20, расположенный ниже по потоку относительно узла 12. Лопатки 20 поддерживаются на платформе 28 и вращаются вместе с ротором турбины и платформой 28 во время работы двигателя 10. Платформа 28 включает в себя обращенную радиально наружу первую поверхность 40, обращенную радиально внутрь вторую поверхность 46, третью поверхность 48 и множество канавок 60, продолжающихся в поверхность 48. Канавки 60 располагаются таким образом, что между смежными канавками 60 образовано пространство. Канавки 60 сужаются в направлении от их входов, расположенных дистально относительно поверхности 40, до их выходов, расположенных проксимально относительно поверхности 40, таким образом, что входы имеют ширину больше, чем выходы. Изобретение направлено ...

ТУРБОМАШИНА (варианты)

Турбомашина, в частности турбокомпрессор, с корпусом, с установленным в корпусе ротором и с сухим газовым уплотнением для герметизации ротора по отношению к корпусу, причем в корпусе проделано, по меньшей мере, одно отверстие для газообразной среды, через которое может направляться газообразная среда для поддержания равномерной температуры сухого газового уплотнения в направлении его самого. Газообразная среда через отверстие может направляться непосредственно в газовую камеру, образованную между корпусом и сухим газовым уплотнением. Дополнительно или в качестве альтернативы отверстие служит для установки направляющей трубы для газообразной среды. Изобретение направлено на создание турбомашины, в которой может эффективно поддерживаться равномерная температура сухого газового уплотнения. 2 н. и 20 з.п. ф-лы, 6 ил.

СПОСОБ И УСТРОЙСТВО ДЛЯ ОХЛАЖДЕНИЯ УПЛОТНЕНИЯ ДЛЯМАШИННОГО ОБОРУДОВАНИЯ

Способ для охлаждения уплотнения турбинного вала, расположенного в стенке камеры. Уплотнение нагревается горячим сжатым паром, который просачивается через лабиринт в камеру, и внутренним трением. Способ содержит этапы: а) обеспечения камеры, в которой расположено уплотнение и в которую просачивается горячий сжатый пар, b) впрыска холодной жидкости в камеру, и с) охлаждения и конденсации горячего сжатого пара в камере. Способ применяется в силовых установках, которые включают в себя испаритель, конденсатор и циркуляционный насос. Такие способ и устройство позволят снизить износ на поверхностях уплотнения. 2 н. и 8 з.п. ф-лы, 6 ил.

СИСТЕМА ПОДАЧИ ОХЛАЖДАЮЩЕГО ВОЗДУХА В ГАЗОВУЮ ТУРБИНУ

Система подачи охлаждающего воздуха в газовую турбину, в которой охлаждающий воздух от источника высокого давления поступает внутрь газовой турбины и перемещается в радиальные ускорители. Радиальные ускорители вызывают тангенциальное ускорение воздуха в направлении окружного движения поверхности ротора. После ускорения охлаждающего воздуха до окружной скорости ротора он входит в радиальные отверстия. Затем охлаждающий воздух выпускается в полый ротор при соответственно уменьшенном радиусе выхода. Система содержит лабиринтное уплотнение в сочетании с щеточным уплотнением для отделения камеры для подачи воздуха в радиальные отверстия от камеры, которая сообщается с передним пространством ротора в 1-й ступени турбины, посредством образования промежуточной камеры, которая предотвращает смешивание потока вследствие утечки от осевого компрессора с потоком охлаждающего воздуха от ускорителей. Лабиринтное уплотнение в сочетании с щеточным уплотнением приспособлено для отделения нагнетательной стороны ...

ДЕТАЛЬ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, СОДЕРЖАЩИЙ ТАКУЮ ДЕТАЛЬ, А ТАКЖЕ СПОСОБ ИЗГОТОВЛЕНИЯ КОЛЬЦЕВОГО ГРЕБЕШКА ЛАБИРИНТНОГО УПЛОТНЕНИЯ НА ТАКОЙ ДЕТАЛИ

Деталь газотурбинного двигателя, вращающаяся вокруг продольной оси, включает кольцевой гребешок лабиринтного уплотнения. Гребешок в радиальном направлении имеет высоту, изменяющуюся вдоль его окружности, образуя несколько выступающих частей, образованных скобой U-образной формы. Каждая скоба закреплена путем установки в полое гнездо, выполненное в гребешке, и имеет профиль, дополняющий этот гребешок. Другое изобретение группы относится к газотурбинному двигателю, включающему указанную выше деталь. При изготовлении кольцевого гребешка подготавливают деталь газотурбинного двигателя с кольцевым гребешком постоянной высоты, и инструмент для обработки с полым профилем. Выполняют, по меньшей мере, одно гнездо на поверхности гребешка, опуская инструмент в радиальном направлении. Затем подготавливают скобу из материала, более твердого, чем материал детали, и имеющую профиль, дополняющий упомянутое гнездо. Устанавливают скобу в гнездо, закрывая его, и соединяют скобу с гребешком. Изобретения позволяют ...

БАРАБАН РОТОРА ОСЕВОЙ ТУРБОМАШИНЫ И ТУРБОМАШИНА

Барабан ротора осевой турбомашины содержит стенку с профилем вращения вокруг оси вращения ротора, образующую пустотелый корпус и содержащую на своей наружной поверхности две кольцевые фиксирующие поверхности для ряда лопаток. Две фиксирующие поверхности стенки барабана в целом расходятся друг от друга, образуя профиль, расширяющийся в радиальном направлении наружу от наружной поверхности стенки. Высота в радиальном направлении фиксирующих поверхностей составляет от 1 до 10% от среднего радиуса стенки барабана, на котором они расположены. Другое изобретение группы относится к турбомашине, включающей ротор, содержащий указанный выше барабан, имеющий ряд групп фиксирующих поверхностей, каждая из которых соответствует ряду лопаток. Группа изобретений позволяет снизить массу и повысить жесткость барабана ротора осевой турбомашины. 2 н. и 13 з.п. ф-лы, 6 ил.

Уплотнение паровой турбины

Полезная модель относится к области турбостроения, а именно к уплотнениям паровых турбин тепловых электростанций, может быть использована в конструкциях надбандажных, диафрагменных, промежуточных и концевых уплотнениях и направлена на обеспечение высокой экономичности по расходу утечки, износостойкости и ремонтопригодности конструкции при работе во всём диапазоне режимных параметров и условий. Известное уплотнение паровой турбины, содержащее вал и соединённую сваркой статорную часть, содержащую цилиндрическую пластину, внутри которой расположены кольцевые пластины, плоскость каждой из которых перпендикулярна оси турбины, а центр совпадает с осью турбины, снабжено цилиндрическими кольцами, установленными в статорной части, при этом вал выполнен гладким с постоянным диаметром, причем в цилиндрические кольца вставлены кольцевые пластины, при этом в кольцевых пластинах выполнены радиальные прорези с образованием между ними плоских лепестков, отогнутых к плоскости кольцевых пластин, при этом ...

Уплотнение турбомашины

Полезная модель относится к области энергетического машиностроения, конкретно, турбостроения, в частности к конструкции концевых и внутренних уплотнений корпусов и концевых уплотнений корпусов подшипников турбомашин. Уплотнение турбомашины содержит верхнее и нижнее полукольца, сегменты с гребнями, размещенные с радиальным зазором в кольцевой расточке полуколец и подпружиненные пружинами. В сегментах между гребнями выполнены кольцевые пазы, в которых жестко закреплены кольцевые уплотнительные элементы, выполненные из полимерного антифрикционного материала, при этом диаметр кольцевых уплотнительных элементов меньше диаметра гребней. 2 ил.

Сотовое щелевое уплотнение для магистральных насосов двухстороннего входа

Полезная модель относится к бесконтактным уплотнительным узлам рабочих колес насосов и может быть использована для магистральных центробежных насосов, перекачивающих нефть и нефтепродукты, в том числе автомобильный бензин, дизельное топливо, топливо для реактивных двигателей и авиационный бензин. Сотовое щелевое уплотнение рабочего колеса магистрального насоса включает цельное металлическое кольцо, содержащее внутреннюю и наружную поверхности, и сотовый элемент. При этом внутренняя поверхность цельного металлического кольца образована входной частью, предназначенной для входа потока жидкости из подвода магистрального насоса в полость рабочего колеса магистрального насоса, и уплотнительной частью, выполненной с возможностью размещения обода рабочего колеса магистрального насоса с образованием кольцевого уплотняющего зазора между уплотнительной частью внутренней поверхности цельного металлического кольца и внешней поверхностью обода рабочего колеса магистрального насоса и радиального зазора ...

УСТРОЙСТВО ВЕНТИЛЯЦИИ РОТОРА ТУРБИНЫ ВЫСОКОГО ДАВЛЕНИЯ ТУРБОМАШИНЫ

... 1. Устройство вентиляции ротора турбины высокого давления турбомашины, в которой турбина расположена позади камеры сгорания и содержит диск, снабженный внутренней расточкой и передней перемычкой для его крепления на выходном конусе компрессора высокого давления, и фланец, расположенный перед указанным диском и отделенный от него полостью, фланец содержит массивную радиальную внутреннюю часть, также снабженную внутренней расточкой, через которую проходит передняя перемычка диска, и переднюю перемычку для крепления на указанном выходном конусе, устройство содержит первый контур охлаждения лопаток, который питается первым воздушным потоком, отбираемым у основания камеры сгорания, и подает первый воздушный поток в указанную полость через основные воздушные сопла, расположенные перед фланцем, и через вентиляционные отверстия, выполненные во фланце, и второй контур охлаждения фланца, который питается вторым воздушным потоком через выпускной лабиринт, расположенный за компрессором высокого давления ...

СПОСОБ ИЗГОТОВЛЕНИЯ МНОГОСТУПЕНЧАТОГО УПЛОТНЕНИЯ И МНОГОСТУПЕНЧАТОЕ УПЛОТНЕНИЕ

... 1. Способ изготовления многоступенчатого уплотнения (10), включающий определение исходных первого и второго щеточных уплотнений (20, 22), имеющих одинаковые конструкции для совместного уплотнения перепада давления вдоль поверхности (12), вращающейся относительно уплотнений, модификацию общего конструктивного признака уплотнений для распределения нагрузки от перепада давления без учета отклонения под давлением, модификацию уплотнений для обеспечения вращательной устойчивости относительно поверхности, испытание уплотнений под испытательным давлением для определения их отклонения под давлением, и модификацию общего конструктивного признака уплотнений для распределения по существу поровну нагрузки давлением с учетом отклонения под давлением. 2. Способ п.1, в котором уплотнение (10) имеет по существу идентичные конструкции первого и второго уплотнений (20, 22), за исключением одного конструктивного признака, имеющего разные конфигурации в уплотнениях для распределения по существу поровну нагрузки ...

МОДИФИКАЦИЯ ПЛАТФОРМЫ РОТОРА И СПОСОБ, ИСПОЛЬЗУЮЩИЙ ЩЕТОЧНЫЕ УПЛОТНЕНИЯ В УПЛОТНЯЮЩЕЙ ОБЛАСТИ ДИАФРАГМЫ ПАРОВЫХ ТУРБИН ДЛЯ УСТРАНЕНИЯ ПРОГИБА РОТОРА

... 1. Паровая турбина, содержащая вращающийся элемент (11), включающий в себя вал (12) ротора, имеющий поверхность вала ротора, и невращающийся элемент (17) вокруг вращающегося элемента, щеточное уплотнение (26), удерживаемое невращающимся элементом для уплотняющего зацепления с вращающимся элементом, по меньшей мере, два рабочих колеса (14) на вращающемся элементе, разнесенных аксиально одно от другого, причем вращающийся элемент включает в себя множество рабочих лопаток (16), разнесенных одна от другой по окружности на каждом из рабочих колес, средство (40, 46) для предотвращения неравномерной по окружности передачи тепла на поверхность вала ротора вследствие тепла, образуемого фрикционным контактом между щеточным уплотнением и вращающимся элементом, тем самым устраняя или минимизируя прогиб вращающегося элемента, причем средство для предотвращения включает в себя кольцевую платформу (40), выступающую радиально наружу из поверхности вала ротора в осевом расположении между рабочими колесами ...

УЗЕЛ УПЛОТНЕНИЯ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, ВКЛЮЧАЮЩИЙ В СЕБЯ КАНАВКИ В ОБРАЩЕННОЙ РАДИАЛЬНО НАРУЖУ СТОРОНЕ ПЛАТФОРМЫ

УПЛОТНИТЕЛЬНОЕ КОЛЕСО С СОЕДИНЕНИЕМ ТИПА "ЛАСТОЧКИН ХВОСТ"

... 1. Уплотнительное кольцо в многоступенчатой турбине, содержащее два кольцевых сегмента 20, 22, соединенных посредством соединения 23 типа «ласточкин хвост». ! 2. Уплотнительное кольцо по п.1, в котором соединение 23 типа «ласточкин хвост» содержит охватываемую часть/охватывающую конфигурацию. ! 3. Уплотнительное кольцо по п.1, в котором соединение 23 типа «ласточкин хвост» содержит конфигурацию вставка/канавка. ! 4. Уплотнительное кольцо по п.3, в котором вставка 24 конфигурации вставка/канавка представляет собой выступ, который проходит от приблизительно плоской поверхности торца одного из кольцевых сегментов 20. ! 5. Уплотнительное кольцо по п.3, в котором канавка 26 конфигурации вставка/канавка представляет собой выемку в приблизительно плоской поверхности торца одного из кольцевых сегментов 22. ! 6. Уплотнительное кольцо по п.3, в котором вставка 24 конфигурации вставка/канавка и канавка 26 конфигурации вставка/канавка имеют одинаковые размеры так, что вставка 24 плотно входит в канавку ...

ГЕРМЕТИЗИРУЮЩЕЕ УСТРОЙСТВО С ПРИМЕНЕНИЕМ ОБРАТНОГО ГРАДИЕНТА ДАВЛЕНИЯ

... 1. Уплотнительное устройство (100) с противоположным градиентом давления, предназначенное для использования с компонентами (110), имеющими переменные скорости вращения, содержащее лабиринтные зубцы (120), расположенные на компоненте (110), и уплотнение (130) с противоположным градиентом давления, расположенное между парой из указанных лабиринтных зубцов (120) и содержащее перегородки (140), каждая из которых имеет расположенный под углом конец (160). ! 2. Уплотнительное устройство (100) по п.1, в котором указанный компонент (110) является вращающимся компонентом (110). ! 3. Уплотнительное устройство (100) по п.2, в котором вращающийся компонент (110) представляет собой уплотнительное кольцо (115) или ротор (50, 52). ! 4. Уплотнительное устройство (100) по п.2, в котором вращающийся компонент (110) представляет собой ротор (38), расположенный внутри корпуса (46) уплотнения. ! 5. Уплотнительное устройство (100) по п.2, в котором вращающийся компонент (110) представляет собой турбинную лопатку ...

УПЛОТНИТЕЛЬНЫЙ УЗЕЛ ДЛЯ УПЛОТНЕНИЯ СТАЦИОНАРНОГО КОМПОНЕНТА И ВРАЩАЮЩЕГОСЯ КОМПОНЕНТА И ТУРБИНА

... 1. Уплотнительный узел для уплотнения стационарного компонента и вращающегося компонента, имеющий сопрягающуюся с уплотнительным зубцом поверхность, предназначенную для сопряжения с уплотнительным зубцом и имеющую ровную часть, предназначенную для совмещения с уплотнительным зубцом с обеспечением уплотнения во время установившегося режима работы уплотнительного узла, и первую вогнутую часть, расположенную смежно с ровной частью и предназначенную для совмещения с уплотнительным зубцом с зазором во время первого неустановившегося режима работы уплотнительного узла, при этом уплотнительный зубец присоединен к одному из компонентов, стационарному или вращающемуся, а сопрягающаяся с уплотнительным зубцом поверхность присоединена к другому из компонентов, стационарному или вращающемуся.2. Уплотнительный узел по п.1, дополнительно содержащий вторую вогнутую часть, расположенную смежно с ровной частью противоположно первой вогнутой части и предназначенную для совмещения с указанным уплотнительным ...

УПЛОТНИТЕЛЬНАЯ СИСТЕМА С ДВУМЯ РЯДАМИ ДОПОЛНЯЮЩИХ ДРУГ ДРУГА УПЛОТНИТЕЛЬНЫХ ЭЛЕМЕНТОВ

СИСТЕМА, СОДЕРЖАЩАЯ МЕЖСТУПЕНЧАТОЕ УПЛОТНЕНИЕ (ВАРИАНТЫ), И СВЯЗАННЫЙ С НЕЙ СПОСОБ

... 1. Система, содержащая:многоступенчатую турбину, имеющую:межступенчатое уплотнение, проходящее в осевом направлении между первой и второй ступенями турбины и содержащее:верхнюю часть, проходящую от верхнего по потоку опорного плеча к нижнему по потоку опорному плечу, причем верхнее и нижнее опорные плечи выполнены с обеспечением ограничения перемещения межступенчатого уплотнения в радиальном направлении многоступенчатой турбины, инижнюю часть, проходящую от опорного конца к крюкообразному концу, причем опорный конец выполнен с обеспечением ограничения перемещения межступенчатого уплотнения в радиальном направлении, а крюкообразный конец имеет выступ, проходящий в поперечном направлении относительно основания нижней части, при этом крюкообразный конец выполнен с обеспечением ограничения перемещения межступенчатого уплотнения в радиальном направлении и в осевом направлении многоступенчатой турбины.2. Система по п.1, в которой перемещение в радиальном направлении верхнего по потоку опорного ...

ТУРБИНА, ВКЛЮЧАЮЩАЯ СИСТЕМУ КЛАПАНОВ УПЛОТНИТЕЛЬНОГО ВОЗДУХА

... 1. Турбина, содержащая:ротор (2);гидродинамический подшипник (31) для опоры с возможностью вращения ротора;систему (45, 47) подающих воздух каналов для подачи воздуха к гидродинамическому подшипнику;систему (57, 59, 61, 63) отводных каналов для отвода части подаваемого воздуха;систему (67, 71) управления, предназначенную для изменения количества воздуха, отводимого через систему отводных труб, на основе рабочего режима турбины.2. Турбина по п.1, в которой система управления предназначена для уменьшения количества воздуха, отводимого через систему отводных каналов, если скорость вращения ротора меньше заданного значения.3. Турбина по п.1, дополнительно содержащая внешний компрессор (73) для подачи воздуха в систему подающих воздух каналов.4. Турбина по п.2, дополнительно содержащая внешний компрессор (73) для подачи воздуха в систему подающих воздух каналов.5. Турбина по п.3, в которой система управления дополнительно предназначена для изменения количества воздуха, подаваемого с помощью ...

УПЛОТНИТЕЛЬНОЕ СОЕДИНЕНИЕ ДЛЯ ГАЗОТУРБИННОЙ УСТАНОВКИ

ЦЕНТРОБЕЖНОЕ РАБОЧЕЕ КОЛЕСО И ТУРБОМАШИНА

... 1. Центробежная турбомашина (1), содержащаякорпус (2),роторный узел (3), содержащий по меньшей мере одно центробежное рабочее колесо (10) для текучей среды, проходящей от впускной стороны (11) рабочего колеса (10) к его выпускной стороне (12),уплотнение (20) входного отверстия рабочего колеса, проходящее между входным отверстием (15) центробежного рабочего колеса (10) и корпусом (2) и предназначенное для предотвращения протечки текучей среды от стороны высокого давления к стороне низкого давления рабочего колеса (10),при этом указанное уплотнение (20) имеет по меньшей мере первую часть (21а), расположенную с впускной стороны (11), и последнюю часть (21е), расположенную с выпускной стороны (12) рабочего колеса (10), причем диаметр последней части (21е) меньше диаметра первой части (21а).2. Центробежная турбомашина (1) по п. 1, в которой уплотнение (20) входного отверстия представляет собой уплотнение лабиринтного типа с набором зубцов (21а-е), проходящих в радиальном направлении к оси (X ...

УПЛОТНЕНИЕ ДЛЯ РОТОРНОЙ МАШИНЫ

... 1. Роторная машина, содержащая ротор, статор, лабиринтное уплотнение, расположенное между ротором и статором машины, и сухое газовое уплотнение, расположенное между ротором и статором машины ниже по потоку от лабиринтного уплотнения, причем лабиринтное уплотнение содержит ротор и статор, который имеет полость, содержащую теплопередающую среду, предназначенную для передачи тепла между статором лабиринтного уплотнения и зоной, смежной с этим статором, для охлаждения или нагрева сжатой рабочей текучей среды до взаимодействия указанной рабочей текучей среды с сухим газовым уплотнением.2. Машина по п. 1, в которой статор лабиринтного уплотнения выполнен с возможностью охлаждения сжатой рабочей текучей среды до температуры ниже максимальной рабочей температуры сухого газового уплотнения.3. Машина по п. 1, в которой теплопередающая среда содержит воду.4. Машина по п. 1, в которой сжатая рабочая текучая среда проходит через указанную зону.5. Машина по п. 1, в которой статор лабиринтного уплотнения ...

ТУРБИННАЯ ЛОПАТКА С УПЛОТНИТЕЛЬНЫМ ЭЛЕМЕНТОМ

... 1. Лопатка (2) ротора турбины, содержащая внутреннюю поверхность (8) и внешнюю поверхность (10), расположенные по разные стороны оси (XX′) лопатки, причем лопатка (2) содержит также наконечник (6), расположенный на ее вершине, и, по меньшей мере, один уплотнительный элемент (12, 14), установленный на указанном наконечнике, причем указанный уплотнительный элемент (12, 14) расположен перпендикулярно внутренней поверхности (8) и внешней поверхности (10) и содержит первую оконечность (16, 18) со стороны внешней поверхности (10) и вторую оконечность (20, 22) со стороны внутренней поверхности (8), причем указанная первая оконечность (16, 18) имеет большую высоту, чем указанная вторая оконечность (20, 22), причем указанный уплотнительный элемент (12, 14) содержит наружную контактную поверхность (26) уплотнительного элемента, расположенную между указанными первой (16, 18) и (20, 22) второй оконечностями, отличающаяся тем, что указанная наружная контактная поверхность (26) уплотнительного элемента ...

Dichtvorrichtung für drehende Turbinenschaufeln

Es wird eine verbesserte Dichtung für eine Turbine beschrieben, die aufeinanderfolgende Düsendeckel enthält, die einen äußeren Träger für eine radiale Anordnung von statischen Schaufeln liefern, die abwechselnd in axialer Richtung angeordnet sind, wobei radial und axial getragene äußere Dichtungsbauteile Teil einer Dichtung sind, die den Fluidstrom um die Spitze von drehenden Schaufeln verringert, wobei der radiale Träger des äußeren Dichtungsbauteils als ein von Keilen in Stellung gehaltener Ring und eine Umfangserweiterung geformt ist, derart, dass die Keile und die Umfangserweiterung einen ausreichenden Abstand haben, um eine relative radiale Bewegung zwischen dem Ring und dem Gehäuse zu erlauben, während eine Druckdichtungsseite und ein Träger in axialer Richtung gegen das Gehäuse geliefert werden, und wobei der Ring einen ausreichenden Abstand vom Gehäuse und/oder den Düsendeckeln hat, um im Wesentlichen von einer radialen Lageveränderung im Fall einer Drehbewegung der Düsendeckel ...

Rotierende Dichtung

APPARATUS FOR THE AUTOMATIC CONTROL OF THE PLAY OF A LABYRINTH SEAL OF A TURBO MACHINE

Überlappungsdichtung für eine Turbinenleitdüsenbaugruppe

Es werden Systeme zur thermischen Regelung einer Turbine (100, 200, 300, 500, 902, 906) offengelegt. In einer Ausführungsform enthält eine Turbinenleitdüsenbaugruppe (17): einen äußeren Leitapparatring (505); eine physisch mit dem äußeren Leitapparatring (505) verbundene Leitschaufel (503); und einen physisch mit der Leitschaufel (503) verbundenen inneren Leitapparatring (507), wobei der innere Leitapparatring (507) einen ersten axialen Zahn (508, 509, 808, 809) enthält, der zur Wechselwirkung und im Wesentlichen zur Ausbildung einer Dichtung (207) mit einem auf einem Laufschaufelschaft (502) angeordneten zweiten axialen Zahn (508, 509, 808, 809) ausgestaltet ist.

Sealing arrangement for use in e.g. gas turbine of aircraft engine, has rotor sealing element for sealing of gap between chambers and arranged at rotor, where peripheral surface of sealing element is partially formed in helical shape

The arrangement (1) has a rotor (11) i.e. shaft, rotatable relative to the stator, where a gap (13) between two chambers (R1, R2) is formed between the rotor and the stator. A rotor sealing element (2) for sealing the gap is arranged at the rotor, where a peripheral surface of the sealing element is partially formed in helical shape. The peripheral surface comprises an increase from one of the chambers to the other chamber. The chamber is formed as a storage chamber, and the sealing element is in contact with fluid i.e. oil, in any one of the chambers. An independent claim is also included for a method for sealing two chambers against each other.

Einrichtung zur Spaltabdichtung fuer Gleichdruckdampfturbinen

DICHTUNGSVORRICHTUNG UND TURBOMASCHINE

Eine Dichtungsvorrichtung gemäß der Ausführungsform weist eine Dichtlippe, die zwischen dem Rotationskörper und dem stationären Körper vorgesehen ist und sich in Umfangsrichtung des Rotationskörpers erstreckt, und eine Wirbelbremslamelle, die auf dem stationären Körper stromaufwärts der Dichtlippe vorgesehen ist, auf. Die Wirbelbremslamelle reduziert eine Umfangsgeschwindigkeitskomponente des Arbeitsfluids. Die Wirbelbremslamelle weist eine Unterdruckfläche, die auf einer Seite einer Drehrichtung des Rotationskörpers und eine Überdruckfläche, die auf einer der Unterdruckfläche gegenüberliegenden Seite angeordnet ist, auf. Die Überdruckfläche erstreckt sich in einer Richtung entgegengesetzt zur Drehrichtung des Rotationskörpers von radial nach außen zu radial nach innen.

Rotationsdichtung mit organischem abschleifbarem Material

Dichtungsanordnung für eine Gasturbine

Gasturbine

Arrangement of labyrinth packing for a rotary type of fluid-pressure apparatus

... 624,384. Labyrinth packing; leakage-preventing devices. ARMSTRONG SIDDELEY MOTORS, Ltd., CLARK, T., and ATKINS, J. H. C. Dec. 9, 1946, No. 36282. '[Classes 110(i), 110(iii) and 122(v)] In a labyrinth packing for a rotary type of fluid-pressure apparatus particularly intended to operate at high linear speeds in which a series of axially spaced annular discs interact between the stator and a ring to provide a tortuous passage for pressure fluid, the ring is rigidly supported from the rotor by a pair of separate supporting discs fast with the rotor and secured to the ring, at least one of the supporting discs being conical and disposed concavely to the other. The packing comprises a series of discs 17 carried by a stator ring 18 and secured by rivets 19. The inner peripheries of the discs co-operate without contact with the stepped surface 20 of a ring 21 carried from the rotor 11 by a pair of supporting discs 23, 24. The latter are preferably of high tensile steel and are shrunk on a drum ...

Improvements in or relating to turbine glands

... 532,992. Stuffing-box substitutes. WESTING- HOUSE ELECTRIC INTERNATIONAL CO. Sept. 29, 1939, No. 26904. Convention date, Oct. 1, 1938. [Class 122 (v)] Labyrinth packing for a turbine spindle comprises overlapping collars 13, 17 carried by the housing 10 and the spindle 11 respectively, the collars 17 having stepped radial surfaces 18. Each of the fixed collars 13 has a number of coaxial circular sealing-strips 19 of relatively thin flexible metal extending laterally from one face and providing close clearances with the stepped surfaces 18. Single sealing-strips 22 of relatively heavy section extend radially from the housing and co-operate with axial surfaces 26 at the circumference of the rotatable collars. Similar sealing-strips 27 extend radially from the spindle and co-cperate with the axial end surfaces of the fixed collars, The sealing-strips are secured in grooves by caulking- strips 2.1, 24, 29. The radial sealing-strips 22, 27 may be replaced by pairs of strips of lighter material ...

A seal assembly

NOZZLE GUIDE VANE FOR GAS TURBINE ENGINE

Gas turbine engine sealing arrangement

In a sealing arrangement between two discs 64, 74 of a gas turbine engine a split sealing arrangement comprising a pair of sealing formations each made up of a plurality of sealing segments 86, 100 is provided. Each of the segments 86, 100 has a root 84, 98 accommodated in serrations 66, 76 of the discs 64, 74 and a sealing strip 106 may be provided. The roots 84, 98 of the sealing segments (86, 100) are positively connected to roots 68, 78 of the rotor blades 70, 80 by dovetail or T-shaped tongues 83 and grooves 85 (Figures 6 to 9). The sealing segments may also provided with internal cooling passages. Details of a cooling system involving steam and air and utilising passages in sealing elements to convey fluid between discs is also disclosed (Figures 10 to 12).

A device for reducing the sealing gap between a rotating component and a stationary component inside a rotary turbo-engine

A device for reducing the sealing gap between a rotating component 1 and a stationary component 2 inside a rotary turbo-engine though which a flow passes axially in which each of the components 1, 2 has an abradable planar sealing structure 7, 9 on opposing surfaces (3, 4 in Figs 2a and 2b) which forms a sealing gap 5. The abradable planar sealing structure 7, 9 may be of the form of either a honeycomb structure 7 or a layer of abradable material 9. In the latter case the abradable material 9 is typically an abradable metallic alloy (e.g. of the MCrAlY type where M is Co, Ni or Fe) which can be applied to the components by means of flame spraying and have a porosity which results in the desired surface roughness.

A sealing arrangement for sealing a leakage gap between relatively moveable parts in a flow path

A sealing arrangement 48 for sealing a leakage gap between relatively moveable parts in a flow path between a region of high fluid pressure and a region of low fluid pressure (D and E respectively in Fig. 2), comprises a sealing member 58 having an upstream surface 60, a downstream surface 62, a radially outer surface 64 and a radially inner surface 66, the sealing member 58 being in communication with a housing 54 via resilient means 56. The resilient means 56 is fixedly joined to the upstream surface 60 of the sealing member 58 such that, during operation, both the radial force induced on the sealing member 58 by fluid flowing axially into and circumferentially over the radially inner surface 66 and the axial force induced on the sealing member 58 because of a pressure difference across the sealing member 58 is resisted by the resilient means 56. Sealing means 72 may also be provided between the downstream surface 62 and te housing 54.

Sealing assembly for rotary machines

Improvements in elastic fluid turbine rotor cooling

... 1,077,251. Steam turbines. GENERAL ELECTRIC CO. Jan. 7, 1966 [Feb. 15, 1965], No.754/66. Heading F1T. A multi-stage axial-flow elastic-fluid turbine is provided with collecting passages in the working fluid path, for example on the leading edge of a nozzle partition, through which working fluid is conducted to the space between the upstream side of the diaphragm and the adjacent rotor disc, the arrangement acting to cool the leakage fluid present in that space. The steam turbine shown comprises rotor discs 4, 5 formed integrally with a shaft portion 3, the rotor discs carrying blades 6, 7 respectively. Inter-stage diaphragms 11, 12 are supported from the stator casing 1, the diaphragms carrying nozzle partitions 13, 14 by which steam is directed on to the rotor blades 6, 7 respectively. The diaphragms carry seal members 15, 19, 25 and define with the adjacent rotor discs chambers 18, 21, 24. Pressure balancing ports 16, 17 are provided and extend through the rotor discs 4, 5. Slots 27 are ...

A sealing arrangement for a turbine

A sealing arrangement 41 between first and second relatively rotatable bodies of a machine such as a steam turbine separates a region of relatively high pressure p0 from a region of relatively low pressure Pf. The seal arrangement comprises a series of sealing elements or units S1, S2, S3, at least one of which comprises a brush seal (see also in Fig. 4). A seal bypassing device, preferably comprising a pressure relief valve 42, 43, 44 limits the pressure differential across the brush seal.

A sealing arrangement for sealing a rotating shaft of a turbo machine including a dry gas blow down seal

A sealing assembly 100a, 100b configured to seal a rotating shaft 104 of a turbo machine 102 having a high pressure process gas comprises: a housing 106 defining a bore configured to receive the rotating shaft 104; and sealing assembly 100a, 100b. The housing 106 is mounted to a casing 103 of the turbo machine 102. A first sealing stage 100a comprises a single dry gas seal 114 configured to blow down the high pressure process gas to a lower pressure; a labyrinth seal 116 mounted longitudinally outward from the first sealing stage 114; a second sealing stage 118 mounted longitudinally outward from the labyrinth seal 116; and a separation seal 122 mounted longitudinally outward from the second sealing stage 118. The second sealing stage 118 comprises a tandem dry gas seal having a primary dry gas seal 204 and a secondary dry gas seal 206 axially spaced with an intermediate labyrinth seal 120.

Sealing arrangement using brush seals

Labyrinth seal and rotating machine comprising such a seal

Turbomachine comprising an electric current generator allowing oil injection from the inside of a rotor shaft

Disclosed is a turbomachine for an aircraft comprising a rotor shaft 14, a turbomachine case, a bearing chamber 90, at least one bearing supporting the rotor shaft and located in the bearing chamber, a lubrication device 91 comprising oil injection means 92 to inject oil into the bearing chamber and oil supply means 96 to supply oil to the oil injection means, and an electric current generator 100 comprising an armature 102 driven by the rotor shaft and a field coil 104 fixed to the turbomachine case. The generator has an orifice 110, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator. The generator may be used to power an auxiliary device such as a de-icer. The invention allows the generator to be positioned downstream of the rotor shaft and allows lubricating oil to be injected to the bearing from inside the rotor shaft.

A spring assembly for an active or passive retractable turbine rotor seal

A spring assembly 52 for a retractable turbine rotor seal supported in an arcuate segment includes: a first radially inner restraining plate 54 having a lower surface 56 adapted to engage a surface of a turbine stator, and a flat upper surface 58 provided with an upstanding hub 60; a second radially outer restraining plate 64 having a flat lower surface 66 and an upper surface 68 adapted to engage a surface of the arcuate segment, the radially outer restraining plate 64 formed with an opening 70 receiving the upstanding hub 60; and at least one spring 62 telescoped over the upstanding hub 60 and exerting a radially outward biasing force on the second radially outer restraining plate 64, and adapted to exert a radially outward retracting force on the arcuate segment. The radially inner plate may have a central recess 88 instead of the upstanding hub and the radially outer plate may be a button plate 92.

Sealing of turbine engine enclosures produced by brush seal and labyrinth

Sealing device for an enclosure El, (E2, fig.1) of a turbine engine 1 formed by an assembly of juxtaposed rotating and/or static bodies, the sealing device comprising at least one brush seal 10 having a brush body 101, carried by at least one first member 11, and bristles 102, eg of carbon fibre, extending from said brush body and arranged so as to rub against at least one second member 12 rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure E1 and its outer environment E3, characterised in that said device further comprises a labyrinth-type seal 6 positioned in series with the brush seal 10 between the inside of said enclosure and its outer environment. The labyrinth seal 6 may have only one knife-edge seal 13 ...

Labyrinth seal for a turbine engine of an aircraft

A labyrinth seal for a turbine engine, e.g. for an aircraft, comprises a rotor element 14 and a stator element 16 extending around the rotor element. The rotor element 14 comprises a series of annular lips 12 extending radially outwards and surrounded by an abradable element 18 carried by the stator element 16. Each lip 12 comprises an inner peripheral body portion 12a, an outer peripheral body portion 12b and an upstream annular face 20a for impact of an air flow during operation. The lip 12 has, looking from said upstream annular face 20a, a first annular cavity 22 with a concave rounded cross-section on its inner peripheral body portion 12a and a second annular cavity 24 with a concave rounded cross-section on its outer peripheral body portion 12b, which crosses a median plane of the lip. The asymmetric lip may increase turbulance and the pressure drop across the lip, improving seal performance.

Shaft seals for thermal machines

... 1,059,435. Shaft seals. ESCHER WYSS A.G. June 17, 1965 [June 26, 1964], No. 25744/65. Heading F2B. [Also in Division F1] A shaft seal between the hot part of the housing 1 of a gas turbine and a shaft 2 comprises a stuffing box, the shaft bearing assembly incorporating a cold bearing housing 4 and a bearing bush 3, a housing 13 extending between the housings 1 and 4, the housing 13 being mounted in axially-movable and radially-fixed relationship to the housing 4 but in axiallyfixed relationship to the housing 1 and being connected to the housing 1 by means of a diaphragm 25. The housing 13 comprises a sealing part 14 and an annular part 16. The bush 3 is rigidly connected to the housing 13 and the annular space 17 is fluid-tight relative to the surroundings and to the interior of the bearing housing 4. The sealing part 14 has labyrinths 10, 11 and 12. Opening 18 in the housing 1 is confined by a hub ring 22 to which a ring 24 is secured, the diaphragm 25 securing the housing 13 to the ring ...

Improvements relating to impulse turbines

... 1,149,616. Boundary layer control. ESCHER WYSS A.G. 20 April, 1966 [22 April, 1965], No. 17277/66. Heading F2R. [Also in Division F1] To improve the efficiency of a gas or steam turbine of impulse type having guide blades 11 directing working fluid on to rotor blades 21, the circumferentially extending surfaces SW 2i and SW 2a extending between the rotor blade roots and tips to define the flow passage through the rotor 20 are of radii with respect to the corresponding surfaces SW 1i and SW 1a of the guide blade ring 10 such as to extend into the boundary layer flow zones of the fluid delivered by the guide blades. The radial offset h, Fig. 3, between the adjacent rotor and guide ring surfaces is between 0À5 and 2 times where # 0 is the thickness of the boundary layer adjacent the guide ring surfaces, #S is the axial gap between the guide ring 10 and rotor 20 and 1 is the angle between the direction of fluid flow at the guide ring outlet and a plane normal to the rotational axis of the turbine ...

A gas turbine engine

Improvements in or relating to labyrinth seals

... 803,452. Making labyrinth packing; soldering. COMERY, P. D. Sept. 21, 1956 [Sept. 22, 1955], No. 28994/56. Classes 83 (2) and 83 (4). [Also in Group XXVI] An element for a labyrinth seal is constituted by a metallic strip 14 which is formed across its width with crimps which are of greater magnitude at one edge than at the other so as to cause it to take up the desired circular or helical form. For sealing the space between a rotary shaft 18, Fig. 2, and a stationary mounting 15 the latter may be formed with a helical groove 17 for receiving a helical strip 14 or a number of annular grooves each of which receives a strip crimped to circular form. The strip may be secured in the groove by brazing, the brazing material being provided in the form of a band 22, Fig. 4, at the bottom of the groove 17, and/or a ring 23 placed against the crimped strip at the top of the groove, and the assembly is heated until the brazing material flows within and/or into the groove. The radius of the crimped ...

Improvements in or relating to turbines, turbine type compressors and the like rotating machines

... 580,805. Gas turbines ; air compressors. BAUMANN, K., and METROPOLITANVICKERS ELECTRICAL CO., Ltd. May 7, 1941, No. 5954. [Class 110 (iii)] A turbine or turbo-compressor drum 1 is balanced against end-thrust by balance discs 15 and 12 within the axial length of the drum. High-pressure fluid is introduced, by passages in a stator part 17, to the interior of the drum. Fluid at a low pressure is introduced through other passages in the part 17 into a space 35 and the space 49 is open to atmosphere. The space 35 is bounded by a rotating wall 26 and a stator wall 23. The space 40 is bounded by a rotating wall 12 and a stator wall 42a. Labyrinth packings are provided at 20, 21, 44 and 47.

Reaction turbine.

HYDRODYNAMIC BRUSH POETRY

POETRY FOR A STEAM TURBINE

Centrifugal impeller and turbomachine

A centrifugal turbomachine (1) comprises a casing (2); a rotor assembly (3) including at least one centrifugal impeller (10) for a fluid flowing from an inlet side (11) to an outlet side (12) of the impeller (10 and an eye seal (20) extending between an impeller eye (15) of the centrifugal impeller (10) and the casing (2) for preventing the fluid from leaking between the casing (2) and the centrifugal impeller (10); wherein the eye seal (20) comprises at least a first portion (21a) toward the inlet side (11) and a last portion (21e) toward the outlet side (12) of the impeller (10), the last portion (21e) being smaller in diameter than the first portion (21a).

Steam seal air removal system

Seal assembly and rotary machine containing such seal

Geothermal steam turbine

Shaft seal arrangement for a fluid machine and method for sealing a shaft of a fluid machine

The invention relates to a shaft seal arrangement, comprising a first seal (1), a second seal (2) and a third seal (3) which are arranged in series between a product side (15) which is to be sealed and an atmosphere side (16), wherein the second seal (2) is arranged between the first seal (1) and the third seal (3), wherein a first pressure (P1) prevails in a space (6; 61) adjoining the second seal (2) in the direction of the product side (15), and a second pressure (P2) prevails in a space (7; 71) adjoining the second seal (2) in the direction of the atmosphere side (16), wherein the space (7; 71) adjoining in the direction of the atmosphere side (16) is connected to a pressure supply line (25) via which a pressure medium can be supplied to the space, and wherein the first pressure (P1) is equal or essentially equal to the second pressure (P2), such that the second seal (2) can be operated with a pressure difference, between the first pressure (P1) and the second pressure (P2), of zero ...

METHOD FOR PRODUCING A LEAK PREVENTION UNIT FOR A SEALING LABYRINTH, THERMOMECHANICAL PART AND TURBINE ENGINE COMPRISING SUCH A LEAK PREVENTION UNIT

Selon ce procédé, on fournit un support (20) présentant une base (12) de léchette (10) annulaire, et on construit la partie saillante de la léchette (10) par le dépôt successif de couches sur la base (12), par réalisation des étapes suivantes : - on active une source laser reliée à une tête optique (34) focalisée sur un point de la surface du sommet de la base (12) et une source (35;45) de poudre reliée à une buse de projection (38), ce par quoi on forme un bain de fusion localisé au niveau dudit point, dans lequel est injecté la poudre d'où il en résulte la formation d'une surépaisseur localisée ; et - on règle la tête optique (34) et la buse (38) sur un autre point adjacent à ladite surépaisseur et on retourne à l'étape précédente jusqu'à la formation d'une couche sur sensiblement toute la base (12).

REPAIRABLE LABYRINTH SEAL

A repairable labyrinth seal of a gas turbine engine comprises at least one fin having a base with a thickness and a tip portion extending therefrom. A shoulder distinguishes the base from the tip portion. The shoulder defines a machining site suitable for receiving a welded replacement piece for shaping a new tapered tip portion following removal of a worn tapered tip portion.

SEALING RING FOR NON-HERMETIC FLUID SEALS

Sealing ring for non-hermetic fluid seals with a restricted passage between sealing elements rotating relative to one another, with a carrier and with at least one sealing rib extending radially on the outside or inside around the carrier, the edge of which rib forms a flow restriction with an opposing running-in surface, the sealing rib presenting an abrasive geometry. The/each sealing rib has for the most part a smooth, rotationally symmetrical contour, and one or a few cutting elements are arranged at one or a few points on the/each sealing rib so that each element projects radially and axially on one or both sides from the sealing rib contour.

LABYRINTH SEAL CONSTRUCTION

LABYRINTH SEALS

LEAF SEAL

A leaf seal assembly 10' is disclosed for use in a gap between a rotating component 1 and a stationary component 2, for example of a turbo-machine. The leaf seal assembly 10 comprises at least one leaf seal 20' having a generally planar surface. A runner 50'is coupled to a distal end of the least one leaf seal 20'. The at least one leaf seal 20' maintains the runner 50' in a first position away from the rotating component 1 in an unpressurised inoperative state. The runner 50' moves to a second position, close to, but not contacting, the rotating component 1 in a pressurised operative state. In some embodiments the at least one leaf seal is angled in the direction of the flow. In some embodiments a first leaf seal is vented. In some embodiments the leaf seal assembly is segmented. In some embodiments the runner comprises segments having a radial thickness which varies circumferentially ...

METHOD OF AND APPARATUS FOR COOLING A SEAL FOR MACHINERY

A method for cooling a seal located in a wall of a chamber. The seal being heated by hot pressurized vapor that leaks through a labyrinth into the chamber (20) and internal friction. The method comprising the steps of a) providing a chamber in which the seal is located and into which the hot pressurized vapor leaks, b) injecting cool liquid into the chamber, and c) cooling and condensing the hot pressurized vapor in the chamber. The method is used in a power plant that includes a vaporizer (12), a condenser (16), a cycle pump (18).

SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT

A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.

TURBINE ASSEMBLY OF AN AIRCRAFT TURBINE ENGINE

La présente invention concerne un ensemble de turbine (10) de turbomachine (1), comprenant au moins un premier rotor aubagé (12), un stator aubagé (13) et un deuxième rotor aubage (14) disposés successivement, les rotors (12, 14) étant montés sur un arbre (2), une platine d'étanchéité (20) s'étendant entre le stator (13) et l'arbre (2) et séparant une première cavité (C1) disposée entre le premier rotor (12) et le stator (13), d'une deuxième cavité (C2) disposée entre le stator (13) et le deuxième rotor (14), des moyens (300, 31) de diminution de la pression étant positionnés au sein de la première cavité (C1), l'ensemble étant caractérisé en ce que lesdits moyens (300, 31) de diminution de la pression comprennent une pluralité d'ailettes de recompression (300) sensiblement radiales s'étendant dans la première cavité (C1).

HYBRID METAL AND COMPOSITE SPOOL FOR ROTATING MACHINERY

A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers may be between the metal rings and composite shell which may be connected by a shrink bonded joint. The metal rings may include a single seal tooth ring with an annular radially extending seal tooth. A method for fabricating the spool may include fabricating one or more metal rings with the features therein, positioning the metal rings in place on an outer surface of an uncured composite spool shell of the spool before curing the shell, and curing the shell with the one or more metal rings positioned in place. Alternatively, rings may be heated to a temperature at least sufficient to slide rings over a cured composite shell, and allowed to cool and shrink onto shell.

LABYRINTH SEAL

A labyrinth seal (25,...,27), for sealing the annular interspace (11) between the rotor (12) and the stator (10) of a steam turbine or gas turbine, comprises a multiplicity of sealing strips (13) which are arranged in series in the axial direction, are fastened on the stator (10) and project into the interspace (11), which sealing strips interact, with sealing effect, with rotor-side sealing elements (14, 19) which are arranged in a staggered manner. With such a labyrinth seal (25,...,27), an improved sealing effect is achieved by the sealing strips (13) in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance (29) by which the sealing strip (13) is displaced relative to adjacent rotor-side sealing elements (14, 19) as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating ...

COATED GAS TURBINE ENGINE COMPONENTS

A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

GAS TURBINE AIR SEPARATOR

An air separator for a gas turbine, in which cracks are prevented from occurring at a flange portion of the air separator due to the fretting fatigue. On the other hand, the air separator is easily replaced by that of the prior art. An air separator 20 has a cylindrical split structure of separators 20-1 and 20-2, of which the separator 20-1 is mounted on a rotor 1 whereas the separator 20-2 is mounted on a disc portion 7 on the side of a moving blade 2 by bolts 28 through bolt holes 23 of a flange portion 22. Cooling air from a compressor enters a space 6 from a duct 5 and passes a passage 32 from a clearance 33 so that it is fed to air feed holes 43 and radial holes 44 of the disc portion 7. The air separator of the prior art is of the overhang type fixed by bolts 8, and the flange on the side of the moving blade 2 only contacts to cause the cracks due to the fretting fatigue, which can be prevented by the invention. On the other hand, air holes 50 to be formed in the flange portion 22 ...

SEAL STRUCTURE FOR GAS TURBINE

The invention relates to a structure of a seal ring separating surface for a gas turbine, which sets a shape of an end portion in the separation surface to a perpendicular cutting surface and reduces a leaking amount of a sealing air. A seal ring holding ring (1) within a stationary blade fixes brush seals (3, 4) to an upstream side by bolts (5, 6) respectively, so as to form a seal with respect to a rotor disc (69). Further, it fixes and supports a seal ring (2) to a downstream side by a bolt (7) so as to constitute a seal with respect to a seal portion (8) in a disc (69) side. The brush seals (3, 4) and the seal ring (2) are structured such as to have a circular ring shape and a separation construction, and each of the separation pieces has a gap, so that a sealing air leaks to a downward side from an upward side through the gap, however, since the separation piece end portion is formed in a perpendicular cutting surface and a shape of the gap is formed in a bypass passage, a resistance ...

Dichtung an sich drehenden Maschinenteilen, insbesondere von Kreiselmaschinen.

Mit einer Turbine zusammengebauter Dampferzeuger.

Einrichtung zum Aufrechterhalten eines Abdichtungsspaltes zwischen sich zueinander bewegenden Körpern.

Turbine à fluide élastique.

Kraftanlage.

Machine rotative à fluide.

Installation comprenant une turbo-machine à écoulement axial et à plusieurs étages

Labyrinthgasdichtung

Installation à turbine à gaz

Gasturbinenanlage.

Labyrinthdichtung zum Abdichten der Gehäuse von Maschinen mit umlaufenden Wellen

Dispositif d'étanchéité de sortie d'arbre de machine

Einrichtung zum Abdichten eines umlaufenden Teils an Dampfturbinen und andern Kreiselmaschinen.

Labyrinthdichtung für sich drehende Maschinenteile, insbesondere an Dampf- und Gasturbinen.

Kreiselmaschine mit Abdichtungsvorrichtung.

Mehrstufige Axialströmungsturbine

Einrichtung zur Messung der Menge eines durch eine Labyrinthstopfbüchse strömenden Mediums

Entspannungsturbine

Gleichdruck-Turbinenstufe

Сотовое привальное уплотнение паровой турбины

Использование: в паровых турбинах. Сотовое привальное уплотнение паровой турбины содержит корпусы сегментов и уплотняющую сотовую поверхность. Напротив сотовой уплотняющей поверхности расположен вал ротора, на котором выполнены гребни. Корпусы сегментов имеют заплечики, которые прижимаются пружинами к заплечикам статора турбины. Корпусы сегментов имеют паз, образованный буртиками, расположенными по краям корпусов сегментов, в который вставлены пластины из нержавеющей коррозионно-стойкой стали, к которым припаяны сотоблоки, образующие уплотняющую сотовую поверхность, которая обрабатывается в точный размер до установки пластины в паз корпуса сегмента. Крепление пластины к корпусам сегментов осуществляется вальцовкой (загибкой) буртиков, в середине, в окружном направлении каждого сотоблока выполнен цилиндрический паз. В сотоблоках дополнительно выполнены два цилиндрических паза, каждый из которых находится на расстоянии 15÷20 мм от торцов корпуса сегмента, а коаксиально пазам в пластине выполнены отверстия. В корпусах сегментов напротив отверстий в пластинах выполнены цилиндрические пазы, в которые вставлены шляпки заклепок. Шляпки заклепок приварены к корпусам сегментов, цилиндрическая часть заклепки развальцована на поверхности пластины. 6 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 190 835 U1 (51) МПК F01D 11/02 (2006.01) F16J 15/44 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F01D 11/02 (2019.02); F16J 15/442 (2019.02) (21)(22) Заявка: 2019103368, 07.02.2019 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Ушинин Сергей Владимирович (RU) Дата регистрации: 15.07.2019 (56) Список документов, цитированных в отчете о поиске: RU 115829 U1, 10.05.2012. RU 2493372 C1, 20.09.2013. SU 1749495 A1, 23.07.1992. RU 2150627 C1, 10.06.2000. US 6257586 B1, 10.07.2001. US 4162077 A1, 24.07.1979. (45) Опубликовано: 15.07.2019 Бюл. № 20 1 9 0 8 3 5 (54) СОТОВОЕ ПРИВАЛЬНОЕ УПЛОТНЕНИЕ ПАРОВОЙ ...

Axially angled annular seals

A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction for engaging in sliding contact with a peripheral surface of the rotatable shaft. The seal strips are mounted to the stator structure with the tip portions of the seal strips at an angle to the axial direction. Each of the tip portions are formed with a curvature in a radially extending plane between a leading edge and a trailing edge of each seal strip.

Seal assembly for controlling fluid flow

A seal assembly ( 50, 60 ) for a gas turbine engine for controlling air flow between a diffuser ( 48 ) and rotor disks comprising first and second annular flange ends ( 52, 54 ) and an annular seal mid-section ( 56 ) between and operatively connected to the flange ends ( 52, 54 ). The first and second annular flange ends ( 52, 54 ) abut respective outer frame members ( 46 ) of the diffuser, whereby a fluid flow path is formed between the seal assembly ( 50, 60 ) and the rotor disks ( 42 ). The first and second end flanges ( 52, 54 ) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members ( 46 ). In addition, the material of the seal mid-section ( 56 ) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends ( 52, 54 ) and outer frame members ( 46 ).

Low deflection bi-metal rotor seals

A seal assembly for use in a turbomachine is provided. The seal assembly has an annular division wall with outside and inside surfaces, a carrier ring disposed adjacent the inside surface of the annular division wall, and a sealing substrate metallurgically-bonded to an inner-most surface of the carrier ring. The sealing substrate is machined to form a seal surface that can be disposed proximate a rotor and maintained substantially parallel thereto during operation of the turbomachine.

Seal apparatus

A seal apparatus including at least first and second adjacent seal segments, each including an elongate body with ends defined at opposing elongate body ends, to be arranged such that an end of the first seal segment joins with a complementary end of the second seal segment, the end of the first seal segment including a first male component protruding from a plane of a first seal surface to define a first female mating section about the first male component, the end of the second seal segment including a second male component protruding from a plane of a second seal surface to define a second female mating section about the second male component, the first and second male components being receivable in the second and first female mating sections, respectively, to form first and second male component overlaps in at least two dimensions.

Turbine

The turbine is provided with a blade ( 50 ) and a structure body ( 11 ) which rotates relatively with respect to the blade ( 50 ). A stepped part ( 52 A) having a step surface ( 53 A) is installed at one of the leading end of the blade ( 50 ) and the structure body ( 11 ) corresponding to the leading end thereof, while a seal fin ( 15 A) which extends toward the stepped part ( 52 A) to form a small space (H) is installed at the other of them. A cavity (C 1 ) is formed between the blade ( 50 ) and the structure body ( 11 ) and also between the seal fin ( 15 A) and the partition wall which faces thereto in the rotating shaft direction of the structure body ( 11 ) on the upstream side. When a distance of the cavity (C 1 ) between the partition wall and the seal fin ( 15 A) is given as a cavity width (W), and a distance between the seal fin ( 15 A) and the end edge ( 55 ) of the stepped part ( 52 A) in the rotating shaft direction on the upstream side is given as (L), at least one of the distances (L) satisfies the following formula (1). 0.7H≦L≦0.3W  (1)

Segmented seal assembly

Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.

System and method for controlling flow in turbomachinery

A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge.

Sealing arrangement

A seal assembly for a bearing chamber of a gas turbine engine. The seal assembly includes a seal land having a sealing surface and a non-sealing surface, and at least one non-contact seal member having a sealing surface and a non-sealing surface. The opposing sealing surfaces define a fluid flow path for a sealing fluid such as air from a compressor of the gas turbine engine. The seal assembly includes a sealing fluid cooling arrangement comprising an oil jet configured to provide cooling oil to one or both of the seal member and the seal runner non-sealing surfaces.

High temperature seal system

A hydrodynamic sealing system for use in an oxidizing environment includes a rotor and a sealing stator. The stator includes a solid lubricant or a surface treatment and the rotor is hardened or the stator is hardened and the rotor includes the solid lubricant or the surface treatment. The stator is located proximate to the rotor to provide a seal. The stator and the rotor are robust at extreme temperatures above 700 degrees Fahrenheit (F) such that at least one of the stator and the rotor have a wear rate and a surface roughness sufficient to maintain an operating gap between the stator and rotor.

LABYRINTH SEALS

A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow. 1. A labyrinth seal arranged to impede leakage flow though a gap between confronting surfaces of static and moving parts in an axial fluid flow turbomachine , the labyrinth seal comprising:a plurality of axially spaced and circumferentially extending sealing fins arranged in leakage flow series, the fins projecting across the gap from at least one of the confronting parts towards an opposing confronting part such that distal ends of the fins are in sealing proximity to the opposing confronting part;a plurality of chambers defined by successive fins in leakage flow series;each fin having an upstream-facing surface of which at least a distal portion thereof is inclined towards the upstream direction of the leakage flow to form a vortex-producing flow recirculation surface operative to deflect the leakage flow in the upstream direction and create recirculating vortices in the leakage flow within the chambers defined by successive fins.2. The labyrinth seal of claim 1 , wherein one of the confronting surfaces of the static and moving parts is castellated and comprises at least one land and at least one relatively recessed portion claim 1 , each land and each recessed portion being in sealing proximity to the distal end of a sealing fin and wherein successive sealing fins alternately comprise at least one first fin having a straight upstream- ...

Turbine

The turbine ( 1 ) according to the present invention includes: a blade body ( 50 ) having a blade ( 59 ) provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction toward the other side from one side and a shroud ( 51 ) extending in a circumferential direction at a tip portion in the radial direction of the blade ( 59 ); and an accommodating concave body ( 11 ) provided at the other of the rotor and the stator, extending in the circumferential direction, accommodating the shroud ( 51 ) with a gap (G) interposed therebetween, and relatively rotating with respect to the blade body ( 50 ), wherein leakage flow (L) leaked from main flow (M) flowing along the blade ( 59 ) flows into the gap (G); and wherein the shroud is provided with a guide curved surface formed between a peripheral surface ( 53 C) facing the accommodating concave body ( 11 ) and a trailing edge end portion ( 56 ) formed closer to the main flow (M) side in a downstream of the leakage flow (L) than the peripheral surface ( 53 C) in a downstream of the leakage flow (L), wherein a guide curved surface ( 57 ) is configured to guide the leakage flow (L) along the peripheral surface ( 53 C) from the peripheral surface ( 53 C) to the trailing edge end portion ( 56 ).

SHAFT SEAL MECHANISM

An inner wall surface of a low-pressure-side side plate opposite to a lateral surface of a thin plats is formed along a direction crossing an axial direction of a rotating shaft such that a gap between the inner wall surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate. 1. A shaft seal mechanism blocking fluid flowing through an annular space between a rotating shaft and a stationary portion in an axial direction of the rotating shaft , the shaft-seal mechanism comprising;a leaf seal housing held inside the stationary portion;a plurality of thin plates provided in a circumferential direction of the rotating shaft with gaps formed between the thin plates, wherein each of the thin plates comprises an outer circumferential, base end fixed in the leaf seal housing and an inner circumferential leading end subtending an acute angle to a circumferential, surface of the rotating shaft, having a width in the axial direction of the rotating shaft and contacting the circumferential surface of the rotating shaft in a slidable manner; anda low-pressure-side side plate and a high-pressure-side side plate provided on a low pressure side and a high pressure side, respectively, of the leaf seal housing, sandwiching each of the plurality of thin plates between the side plates,wherein an inner wall surface of the low-pressure-side side plate opposite to a lateral surface of the thin plate is formed along a direction crossing the axial direction of the rotating shaft such that a gap between the inner wail surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate,2. The shaft seal mechanism according to claim 1 , wherein the inner wall surface of the low-pressure-side side plate and an outer wall surface of the low-pressure-side side plate are connected together by a rounded curved surface projecting toward the inner ...

Aerodynamic seals for rotary machine

An aerodynamic seal assembly for a rotary machine is provided. The assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward-shoe section and an aft-shoe section having multiple labyrinth teeth therebetween facing the rotor. The shoe plate is configured to allow a high pressure fluid to a front portion of the plurality of the labyrinth teeth and a low pressure fluid behind the plurality of the labyrinth teeth and further configured to generate an aerodynamic force between the shoe plate and the rotor. The sealing device segment also includes multiple bellow springs or flexures connected to the shoe plate and to a top interface element, wherein the multiple bellow springs or flexures are configured to allow the high pressure fluid to occupy a forward cavity and the low pressure fluid to occupy an aft cavity. Further, the sealing device segments include a secondary seal attached to the top interface element at one first end and positioned about the multiple bellow springs or flexures and the shoe plate at one second end.

SEALING DEVICE, AXIAL TURBINE AND POWER PLANT

In one embodiment, a sealing device includes seal fins provided on an inner circumferential surface of a stationary body or an outer circumferential surface of a rotating body so as to be adjacent to each other in an axial direction of the rotating body in a gap between the outer circumferential surface of the rotating body and the inner circumferential surface of the stationary body. The device further includes at least one opening member provided on the inner circumferential surface of the stationary body, the opening member being provided at a position between seal fins adjacent to each other in the axial direction, and having holes opened on a side of the inner circumferential surface of the stationary body. 1. A sealing device comprising:seal fins provided on an inner circumferential surface of a stationary body or an outer circumferential surface of a rotating body so as to be adjacent to each other in an axial direction of the rotating body in a gap between the outer circumferential surface of the rotating body and the inner circumferential surface of the stationary body; andat least one opening member provided on the inner circumferential surface of the stationary body, the opening member being provided at a position between seal fins adjacent to each other in the axial direction, and having holes opened on a side of the inner circumferential surface of the stationary body.2. The device of claim 1 , whereinthe seal fins are provided on the outer circumferential surface of the rotating body,the inner circumferential surface of the stationary body has a first surface which is an inner circumferential surface of the opening member, and a second surface placed between opening members adjacent to each other in the axial direction, placed on an upstream side of the most upstream opening member, or placed on an downstream side of the most downstream opening member, andthe seal fins are provided at positions facing the second surface on the outer circumferential ...

SHAFT SEAL INSERT

A shaft seal insert for the shaft seal of a turbomachine extending along a rotational axis includes:—a rotor part attachable on a shaft of a rotor,—a stator part insertable into a stator receiving area, and—a dry gas seal having a rotating seal element attached to the rotor part and a fixed seal element attached to the stator part to seal an intermediate space between the two seal elements, which lie opposite each other on a sealing surface extending radially and in the circumferential direction. A labyrinth seal is provided on a high-pressure side in a serial arrangement with the dry gas seal to seal the intermediate space, having a fixed and rotating labyrinth seal parts. The fixed labyrinth seal part is part of the stator part or is fixed thereto. The rotating labyrinth seal part is part of the rotor part or is fixed thereto. 16-. (canceled)7. A shaft seal insert for a shaft seal of a turbomachine , which extends in an axial direction along an axis of rotation , the shaft seal insert comprising:a rotor part which is configured such that it can be mounted on a shaft of a rotor which extends along the axis of rotation,a stator part which is configured such that it can be inserted into a stator recess,at least one dry gas seal having a rotating sealing element mounted on the rotor part and one static sealing element mounted on the stator part in order to seal an intermediate space between the rotating sealing element and the static sealing element,wherein the static sealing element and the rotating sealing element are arranged facing each other on a sealing surface which extends radially and in the circumferential direction, wherein the shaft seal insert has a high-pressure side at one axial end and a low-pressure sid at the other axial end,wherein a labyrinth seal for sealing the intermediate space is provided on the high-pressure side in a serial arrangement with the dry gas seal, comprising a static labyrinth seal part and a rotating labyrinth seal part, wherein ...

Spring carrier and removable seal carrier

A seal assembly includes a seal support, a spring carrier, a plurality of springs, and a seal carrier. The spring carrier is connected to the seal support by a guide assembly. The plurality of springs are disposed between the seal support and the spring carrier. The seal carrier is connected to the spring carrier and is removable therefrom.

Seal design and active clearance control strategy for turbomachines

A labyrinth seal design, an actuation control clearance strategy, and a method of operating a turbomachine. The labyrinth seal design including a plurality of features configured to open and close radial clearances in response to relative axial movement between a stationary component and a rotating component. The actuation control clearance strategy and method of operating a turbomachine effective to achieve relative motion between a rotating component and a stationary component of the turbomachine using active elements. Axial displacement of the rotating component relative to the stationary component provides an adjustment in a radial clearance at one or more sealing locations between the rotating component and the stationary component to suit a given operating condition of the turbomachine.

HIGH-RELIABLITY TURBINE METAL SEALING MATERIAL

A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant. 17-. (canceled)8. A turbine metal sealing material arranged in a gap between a stator and a rotor of a turbine ,wherein the metal sealing material comprises a porous metal layer and the porous metal layer comprises a surface layer directly coming into contact with a working fluid and a lower layer lying thereunder,wherein the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75%.9. The turbine metal sealing material according to claim 8 , wherein the porous metal layer comprises claim 8 , as a main component claim 8 , an MCrAlY alloy where M is either one of the Ni and Co or both thereof claim 8 , and hexagonal boron nitride (h-BN).10. The turbine metal sealin material according to claim 9 , wherein the MCrAl alloy comprises 15 to 30% of Cr claim 9 , 6 to 15% of Al and 0.3 to 1.0% of Y claim 9 , the balance comprising either one of Ni and Co or both thereof.11. The turbine metal sealing material according to claim 8 , wherein a thickness of the porous metal layer is in the range of 0.3 to 3.0 mm claim 8 , and a ratio of the surface layer to the lower layer is in the range of 0.1 to 1.0.12. The turbine metal sealing material according to claim 8 , wherein the metal sealing material is used in a steam turbine.13. A steam turbine claim 8 , comprising a metal sealing ...

NON-CONTACT SEAL ASSEMBLY WITH MULTIPLE AXIALLY SPACED SPRING ELEMENTS

An assembly is provided for rotational equipment. This assembly includes a plurality of seal shoes, a seal base and a spring system. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the seal shoes. The spring system connects the seal shoes to the seal base. The spring system includes a first spring element and a second spring element. The first spring element extends axially along the centerline in a first axial direction from the seal base to the first seal shoe. The second spring element extends axially along the centerline in a second axial direction from the seal base to the first seal shoe. The second axial direction is opposite the first axial direction. 1. An assembly for rotational equipment , comprising:a plurality of seal shoes arranged about a centerline in an annular array, the plurality of seal shoes comprising a first seal shoe;a seal base circumscribing the plurality of seal shoes; anda spring system connecting the plurality of seal shoes to the seal base, the spring system including a first spring element and a second spring element;the first spring element extending axially along the centerline in a first axial direction from the seal base to the first seal shoe; andthe second spring element extending axially along the centerline in a second axial direction from the seal base to the first seal shoe, the second axial direction opposite the first axial direction.2. The assembly of claim 1 , whereinthe seal base includes a first flange that radially overlaps the first seal shoe; andthe first spring element extends axially from the first flange to the first seal shoe.3. The assembly of claim 2 , whereinthe seal base further includes a second flange that radially overlaps the first seal shoe; andthe second spring element extends axially from the second flange to the first seal shoe.4. The assembly of claim 1 , whereina first radius extends from the centerline to the ...

DICHTEINRICHTUNG UND STROMUNGSMASCHINE

A sealing device () is disclosed for sealing a radially inner gas channel () between a guide vane ring () and a rotor () of a turbomachine, wherein the sealing device () has a sealing ring () for forming a sealed space () with a rear segment, with an inner wall structure () oriented in the opposite direction, which are joined to each other via an annular arch (), wherein the radial flange () transitions into the outer wall structure () and the cylinder () forms the sealing ring (), wherein the inner wall structure () transitions, via an annular web (), into at least one inner body segment (), wherein the sealing device () has a uniform, preferably relatively reduced wall thickness over its individual segments integrally formed with one another, so that the sealing device () is resilient within certain limits. 112461810124141611812262830321828268. A sealing device () for sealing a radially inner gas channel () between a guide vane ring () and a rotor () of a turbomachine , wherein the sealing device () has a sealing ring () for forming a sealed space () with a rear segment , when considered in the direction of a principal flow , of an integral inner ring () of the guide vane ring () , into which penetrates a front platform overhang () of a downstream row of rotating blades () , and wherein the sealing device () has an outer radial flange () for connecting to the integral inner ring () and a double-walled cylinder () with an outer wall structure () oriented in a first direction and with an inner wall structure () oriented in the opposite direction , which are joined to each other via an annular arch () , wherein the radial flange () transitions into the outer wall structure () and the cylinder () forms the sealing ring () ,{'b': 30', '36', '38', '50', '40, 'wherein the inner wall structure () transitions, via an annular web (), into at least one inner body segment (, ), which is oriented parallel to the first direction or to the opposite direction, for the radially ...

LABYRINTH SEAL FOR TURBINES

An improved labyrinth seal is described with the seal including a group of several fins forming circumferential barriers against the flow of a working fluid between stationary and rotating parts in a turbine, wherein within the group the volume between the penultimate fin and the last fin is altered compared to the average volume between other adjacent fins of the group. 1. A labyrinth seal arrangement for an axial flow turbine comprising:a stationary part and a rotating part;an axial series of fins, distributed equidistantly along points of the stationary part and each extending from the stationary part towards the rotating part to a tip so as to form a circumferential barrier against a flow of a working fluid between the stationary part and the rotating part, anda groove in the stationary part located between a penultimate fin and a last fin wherein, as a result of the groove, a volume between the penultimate fin and the last fin is greater than the average volume of any other two adjacent fins of the series.2. The arrangement of wherein all fins but the last fin of the series of fins are slanted against the direction of flow of the working fluid across the seal.3. The arrangement of wherein all fins of the series have essentially the same length.4. The arrangement of wherein the distance between each of the tips of the series of fins and the rotating part are essentially equal.5. The arrangement of wherein all fins but the last of the series of fins are slanted against the direction of flow of the working fluid across the seal and the last fin is essentially straight.6. The arrangement of being part of a gland seal between a casing and a rotor shaft in a steam turbine. This application claims priority to PCT/EP2013/055877 filed Mar. 21, 2013, which claims priority to European application 12160516.6 filed Mar. 21, 2012, both of which are hereby incorporated in their entireties.The present invention relates to a seal mounted between rotating and static parts of a ...

TIP SHROUDED HIGH ASPECT RATIO COMPRESSOR STAGE

A gas turbine engine compressor stage includes a rotor. Compressor blades are supported by the rotor. The blades include an inner flow path surface each supporting an airfoil that has a chord that extends radially along a span to a tip. A shroud is supported at the tip and provides an outer flow path surface. The shroud provides a noncontiguous ring about the compressor stage. 1. A gas turbine engine compressor stage comprising:a rotor;compressor blades supported by the rotor, the blades include an inner flow path surface each supporting an airfoil that has a chord extending radially along a span to a tip, a shroud supported at the tip and providing an outer flow path surface, wherein the shroud provides a noncontiguous ring about the compressor stage.2. The compressor stage according to claim 1 , wherein the airfoils have an aspect ratio corresponding to the airfoil span to the airfoil chord claim 1 , the shroud extends the full chord claim 1 , wherein the aspect ratio is in a range of 1 to 5.3. The compressor stage according to claim 2 , wherein the aspect ratio is in a range of 1.4 to 3.0.4. The compressor stage according to claim 3 , wherein the aspect ratio is in a range of 1.6 to 2.8.5. The compressor stage according to claim 1 , wherein the shroud includes a sealing structure on a side of the shroud opposite of the outer flow path surface.6. The compressor stage according to claim 5 , wherein the sealing structure has labyrinth seals.7. The compressor stage according to claim 1 , wherein the blades each include a root received in a slot in the rotor.8. The compressor stage according to claim 1 , wherein shroud includes ring segments circumferentially spaced apart from one another and separated by gaps claim 1 , wherein multiple blades share a common ring segment.9. The compressor stage according to claim 1 , wherein blades are integrated with the rotor.10. A gas turbine engine comprising:engine static structure;first and second turbine sections rotatable ...

SEALING STRUCTURE FOR TURBOCHARGER HOUSING

Bolt holes are formed in a joint part of a turbine housing , with flanged bolts screwed in the bolt holes . A flange part of a bearing housing is sandwiched between bearing surfaces of the flanged bolts and an inner end face of the joint part . A sealing ring is interposed in an annular space s. Before the flanged bolts are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring , between an outer end face of the joint part and a bolt receiving surface of the flange part . The flanged bolts are screwed into the bolt holes until the bearing surfaces make tight contact with the outer end face so as to resiliently deform the sealing ring 1. A sealing structure for sealing joint surfaces of a turbine housing and a bearing housing of a turbocharger , comprising:an end face of the turbine housing comprising an inner end face in contact with a flange part of the bearing housing and forming a sealing surface, and an outer end face that does not form a sealing surface with the flange part, said outer end face having a height difference from the inner end face and from a bolt receiving surface of the flange part;a resiliently deformable member forming the sealing surface, wherein the flange part is sandwiched between the inner end face and a bearing surface of a head of a bolt screwed in the end face of the turbine housing;wherein a compression allowance for the sealing surface forming element to resiliently deform is set by a height difference between the flange part and the outer end face formed before the bolt is fastened, andsaid sealing structure further comprising a heat shielding wall integrally formed on a backside of the flange part to shield the resiliently deformable member from an inner space of the turbine housing.2. The sealing structure for a turbocharger housing according to claim 1 , wherein the flange part is formed of a plate spring claim 1 , and a height difference corresponding to the compression ...

ROTOR BLADE WITH WHEEL SPACE SWIRLERS AND METHOD FOR FORMING A ROTOR BLADE WITH WHEEL SPACE SWIRLERS

The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank. 1. A rotor blade , comprising;a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion;an airfoil that extends radially outwardly from the top side of the platform;a shank extending radially inwardly from the bottom side of the platform, the shank having a forward wall, an aft wall, a pressure side wall and a suction side wall and a lip that extends axially outwardly from the forward wall, the lip defining a radially inward surface and a radially outward surface, wherein the lip defines a plurality of slots; anda plurality of swirler vane inserts, each swirler vane insert disposed within a respective slot of the plurality of slots, wherein each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.2. The rotor blade as in claim 1 , wherein at least one slot of the plurality of slots includes a laterally extending step.3. The rotor blade as in claim 1 , wherein a portion of each swirler vane insert of the plurality of swirler vane inserts is curved towards the suction side wall of the shank.4. The rotor ...

Seals for gas turbine engine nacelle cowlings

A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core. The core nacelle cowling has a cowling member that extends radially inward towards the engine core. The cowling member is offset axially from the core member to form a labyrinth seal that bounds a coolant inlet, thereby fluidly coupling the fan duct flow of the gas turbine engine with a core compartment defined between the engine core and core nacelle cowling.

GAS TURBINE ENGINE VANE END DEVICES

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two. 1. An apparatus comprising:a moveable airfoil member structured for use in a working fluid flow path of a gas turbine engine; anda brush seal disposed at an end of the moveable airfoil member, the brush seal having a plurality of extensions projecting outwardly and configured to discourage a flow of working fluid through the extensions as the working fluid traverses the working fluid flow path.2. The apparatus of claim 1 , which further includes the gas turbine engine claim 1 , the engine including a plurality of the moveable airfoil members claim 1 , wherein each of the plurality of moveable airfoil members is a rotatable vane that includes a range of travel claim 1 , and wherein the extensions contact the wall in the range of travel.3. The apparatus of claim 1 , wherein the plurality of extensions each have a first end and a second end both disposed toward a distal side of the plurality of extensions claim 1 , the first end and second end connected via a body that is looped around a central member.4. The apparatus of claim 3 , which further includes a crimp to couple the plurality of extensions to the central member claim 3 , the central member extending along a chord of the moveable airfoil member claim 3 , and wherein the moveable airfoil member is a rotatable turbine vane.5. The apparatus of claim 1 , wherein the plurality of extensions cover a ...

AFT OUTER RIM SEAL ARRANGEMENT

An outer rim seal arrangement (), including: an annular rim () centered about a longitudinal axis () of a rotor disc (), extending fore and having a fore-end (), an outward-facing surface (), and an inward-facing surface (); a lower angel wing () extending aft from a base of a turbine blade () and having an aft end () disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (); an upper angel wing () extending aft from the turbine blade base and having an aft end () disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (); and guide vanes () disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins () may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap. 1. An outer rim seal arrangement for a gas turbine engine , comprising:an annular and stationary rim centered about a longitudinal axis of a rotor disc, extending fore and comprising a fore-end, an outward-facing surface, and an inward-facing surface;a lower angel wing extending aft from a base of a turbine blade and comprising an aft end disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap between a rotor cavity and an outer cavity;an upper angel wing extending aft from the base of the turbine blade and comprising an aft end disposed radially outward of the rim outward-facing surface to define an upper angel wing seal gap between the outer cavity and a hot gas path;guide vanes disposed on the rim inward-facing surface in the lower angel wing seal gap and configured to discourage flow through the lower angel wing seal gap and into the rotor cavity during operation of the gas turbine engine, andan air supply passage providing fluid communication between the rotor cavity and a source of ambient air.2. The outer rim seal arrangement of claim 1 , wherein the guide vanes impart swirl about the rotor disc longitudinal axis to a flow of ...

Ceramic matrix composite seal segment for a gas turbine engine

A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

COMPLIANT ROTATABLE INTER-STAGE TURBINE SEAL

Compliant bellow seal may be axially disposed between first and second cooling plates bounding first and second cooling passages between cooling plates and first and second stage disks in turbine. Bellow seal includes two or more convolutions with oppositely facing forward and aft sealing surfaces, which may be flat, on forward and aft annular sealing walls and cylindrical annular outer and inner contact and sealing surfaces on and facing radially outwardly or inwardly from one of the convolutions. A snake bellow seal embodiment may have at least two of the convolutions being full convolutions of unequal width and a forwardmost partial convolution including the sealing wall. 1. A compliant bellow seal comprising:two or more convolutions circumscribed about an axis of rotation,oppositely facing forward and aft sealing surfaces on axially spaced apart forward and aft annular legs or sealing walls, andcylindrical annular outer and inner contact and sealing surfaces on and facing radially outwardly or inwardly with respect to the axis of rotation from one of the convolutions.2. The bellow seal as claimed in claim 1 , further comprising the outer contact and sealing surface being located on a radially outwardly extending cylindrical extension on one of the convolutions.3. The bellow seal as claimed in claim 1 , further comprising the forward and aft sealing surfaces being flat.4. The bellow seal as claimed in claim 3 , further comprising the outer contact and sealing surface being located on a radially outwardly extending cylindrical extension on one of the convolutions.5. The bellow seal as claimed in claim 1 , further comprising:the bellow seal being a snake bellow seal,at least two of the convolutions being full convolutions of unequal width, anda forwardmost partial convolution including the forward annular leg or sealing wall.6. The bellow seal as claimed in claim 5 , further comprising the outer contact and sealing surface being located on a radially inwardly ...

NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT

Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal. 1. An assembly for rotational equipment , the assembly comprising:a first bladed rotor assembly;a second bladed rotor assembly including a rotor disk structure;a stator vane assembly axially between the first and the second bladed rotor assemblies;a stator structure mated with and radially within the stator vane assembly; anda seal assembly configured for sealing a gap between the stator structure and a seal land of the rotor disk structure, wherein the seal assembly includes a non-contact seal, and the seal land is configured as a cantilevered tubular body.2. The assembly of claim 1 , wherein the non-contact seal is a hydrostatic non-contact seal.3. The assembly of claim 1 , wherein the non-contact seal comprises:an annular base;a plurality of shoes arranged around and radially adjacent the rotor disk structure; anda plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the base.4. The assembly of claim 3 , wherein the base is configured with a monolithic full hoop body.5. The assembly of claim 1 , wherein the stator structure is floating radially within the stator vane assembly.6. The assembly of claim 1 , whereinthe first and the second bladed rotor assemblies are turbine rotor assemblies; andthe first bladed rotor assembly is upstream of the second bladed rotor assembly.7. The assembly of ...

COOLING BEARING CHAMBERS IN A GAS TURBINE ENGINE

A cooling arrangement for cooling a bearing in a gas turbine engine, the gas turbine engine comprising a compressor section, a combustor section and a turbine section, the turbine section comprising a low pressure (LP) sub-section and a high pressure (HP) sub-section, a first shaft for carrying rotors of the compressor section and of the HP turbine sub-section and a second shaft for carrying rotors of the LP turbine sub-section the second shaft coaxially aligned with and located within the first shaft, and the bearing arranged downstream of the HP turbine sub-section and upstream of the LP turbine sub-section and arranged for rotatably mounting the second shaft with respect to a support structure. The cooling arrangement comprising a first bleed taken off from the compressor, one or more inlet holes in the second shaft located upstream of the combustor and one or more outlet holes in the second shaft located downstream of the HP turbine sub-section and upstream of the bearing, and an air guide for guiding flow from the first bleed to the one or more inlet holes whereby to separate the flow from the first bleed from a coolant flow directed to cool discs of the turbine section. 1. A cooling arrangement for cooling a bearing in a gas turbine engine , the gas turbine engine comprising a compressor section , a combustor section and a turbine section , the turbine section comprising a low pressure sub-section and a high pressure sub-section , a first shaft for carrying rotors of the compressor section and of the high pressure turbine sub-section and a second shaft for carrying rotors of the low pressure turbine sub-section the second shaft coaxially aligned with and located within the first shaft , and the bearing arranged downstream of the high pressure turbine sub-section and upstream of the low pressure turbine sub-section and arranged for rotatably mounting the second shaft with respect to a support structure , the cooling arrangement comprising:a first bleed taken ...

FILM RIDING SEAL ASSEMBLY FOR TURBOMACHINERY

An aerodynamic seal assembly for a rotary machine includes multiple sealing segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward load-bearing section and an aft load-bearing section configured to generate an aerodynamic force between the shoe plate and the rotor. The shoe plate includes at least one labyrinth teeth facing the rotor and positioned between the forward load-bearing section and the aft load-bearing section. The sealing segment also includes at least one spring connected to a pedestal located about midway of an axial length of the shoe plate and to a stator interface element. Further, the sealing segment includes a rigid segmented secondary seal attached to the stator interface element at one first end and in contact with the pedestal of the shoe plate at one second end. 1. (canceled)2. An aerodynamic seal assembly for a rotary machine , the seal assembly comprising: a shoe plate with a forward load-bearing section and an aft load-bearing section configured to generate an aerodynamic force between the shoe plate and the rotor, wherein the shoe plate comprises at least one labyrinth teeth facing the rotor and positioned between the forward load-bearing section and the aft load-bearing section, wherein the shoe plate is further configured to allow a flow of high pressure fluid into a front portion of the at least one labyrinth teeth and a low pressure fluid into a rear portion of the at least one labyrinth teeth;', 'at least one spring connected to a pedestal located about midway of an axial length of the shoe plate and to a stator interface element; and', 'a rigid segmented secondary seal attached to the stator interface element at one first end and in contact with the pedestal of the shoe plate at one second end, wherein the rigid segmented secondary seal is L-shaped and comprises of an L-shaped spline slot forming a radial spline slot and an axial spline slot ...

GAS TURBINE SPINDLE BOLT STRUCTURE WITH REDUCED FRETTING FATIGUE

A spindle bolt structure is provided in a gas turbine engine, and includes a pilot region located within a bolt hole extending through a seal disk. The pilot region includes a circumferential pilot ridge located adjacent to a downstream axial face of the seal disk and a circumferential trough portion located between a bolt shoulder and the pilot ridge. The trough portion defines a trough diameter that is less than a diameter of the bolt shoulder and less than a diameter of the pilot ridge. The bolt shoulder and pilot ridge are formed with an applied compressive residual stress and are positioned for engagement with the seal disk. 1. In a gas turbine engine , a rotor including a plurality of turbine disks for supporting rows of blades , a torque tube located on a compressor side of the turbine disks , and a seal disk located between the torque tube and a first stage turbine disk , a spindle bolt structure comprising:a spindle bolt extending through the turbine disks and disposed offset from a rotational axis of the turbine disks;the seal disk including an upstream axial face and an opposing downstream axial face, and a bolt hole extending between the upstream and downstream axial faces;the spindle bolt extending through the bolt hole and including a bolt shoulder engaged on the seal disk within the bolt hole;a pilot region formed on the spindle bolt and located within the bolt hole for effecting a reduction in fretting fatigue of the spindle bolt, the pilot region including a circumferential pilot ridge located in the bolt hole adjacent to the downstream axial face of the seal disk and a circumferential trough portion located between the bolt shoulder and the pilot ridge, the trough portion defining a trough diameter that is less than a diameter of the bolt shoulder and that is less than a diameter of the pilot ridge.2. The spindle bolt structure of claim 1 , wherein the diameter of the pilot ridge is less than the diameter of the bolt shoulder.3. The spindle bolt ...

COVER PLATE FOR ROTOR ASSEMBLY OF A GAS TURBINE ENGINE

A cover plate according to an exemplary aspect of the present disclosure includes, among other things, a body, a first tab near a bore of the body, and a second tab circumferentially spaced from the first tab. A slot is defined between the first tab and the second tab, the first tab, the second tab and the slot extending at an angle relative to a slot axis that extends through the bore. In another embodiment, the cover plate includes a bumper that limits deflection of the body. 1. A gas turbine engine , comprising:a rotor section rotatable about an axis and includinga cover plate including a body, wherein said body includes at least one radial retention feature extending from a face of said body;a first tab near a bore of said body;a second tab circumferentially spaced from said first tab with respect to said axis;a slot defined between said first tab and said second tab, said first tab, said second tab, and said slot extending at an angle relative to a slot axis that extends through said bore; andwherein said radial retention feature extends axially forward from an axially forward surface of said face that is radially inward of said radial retention feature.2. The gas turbine engine as recited in claim 1 , wherein said cover plate is part of a turbine rotor assembly or a compressor rotor assembly.3. The gas turbine engine as recited in claim 1 , comprising a seal land that extends from said body.4. The gas turbine engine as recited in claim 3 , wherein said seal land includes at least one seal that seals against a static structure adjacent to said body.5. The gas turbine engine as recited in claim 4 , wherein said static structure is part of an adjacent stator assembly.6. The gas turbine engine as recited in claim 3 , wherein said seal land is radially outward of said radial retention feature.7. The gas turbine engine as recited in claim 1 , wherein said rotor section includes a rotor disk claim 1 , and said radial retention feature engages said rotor disk to ...

TURBINE FOR A TURBINE ENGINE

The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type. 1. A turbine for a turbine engine , the turbine having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards , with sealing means radially extending about the vanes and comprising a sealing ring; with the radially external end of the lip cooperating with said sealing ring so as to form a seal of the labyrinth type , wherein said sealing ring comprises at least one first portion and one second portion radially offset relative to one another , with the first portion and/or the second portion defining a groove wherein the lip is inserted , with the first portion and/or the second portion each cooperating with at least one lip of the vanes axially located opposite said first and second portions , with the first portion comprising a first protruding zone engaged in a form-fitting manner in the axial direction into a first recessed zone of the second portion , with the stator comprising means for holding the first and second portions in position relative to the stator.2. The turbine according to claim 1 , wherein the position-holding means comprise a stop for radially bearing the first portion and means for tightening the second portion against the stator claim 1 , with the first portion being positioned upstream of the second portion.3. The turbine according to claim 1 , wherein the first portion is radially held claim 1 , upstream claim 1 , by the stator claim 1 , with the first portion being radially held claim 1 , downstream claim 1 , by the second portion.4. The ...

Ceramic component for a turbomachine

A ceramic component for a turbomachine, the ceramic component ( 1 ) being configured to be destroyed in response to a contacting with another component ( 2 ) of the turbomachine that moves relative to the ceramic component ( 1 ). A turbomachine component pairing and a turbomachine including such a ceramic component.

SEAL PLATFORM

A partial seal platform for mounting a seal and securing seal to a rotor or a casing including a first arcuate securing segment with a first securing notch for receiving a first securing ridge of rotor or casing; a second arcuate securing segment with a second securing notch for receiving a second securing ridge of rotor or casing; an arcuate coupling segment with a first flat ridge forming a first and second lateral notch on each side of the first flat ridge for receiving the first arcuate securing segment and the second arcuate securing segment; and an arcuate mounting segment including a second flat ridge forming a lateral notch on each side of second flat ridge for receiving first arcuate securing segment and second arcuate securing segment. 1. A partial seal platform for mounting a seal and securing the seal to one of a rotor or a casing , comprising:a first arcuate securing segment including a first securing notch for receiving a first securing ridge of the rotor or the casing;a second arcuate securing segment including a second securing notch for receiving a second securing ridge of the rotor or the casing;an arcuate coupling segment including a first flat ridge forming a first and second lateral notch on each side of the first flat ridge for receiving the first arcuate securing segment and the second arcuate securing segment,wherein the first securing notch and the second securing notch open away from each other, andwherein the arcuate coupling segment has at least one passage in the first flat ridge for receiving a part of a coupling bolt;an arcuate mounting segment including a second flat ridge forming a lateral notch on each side of the second flat ridge for receiving the first arcuate securing segment and the second arcuate securing segment,wherein the arcuate mounting segment has at least one passage in the second flat ridge for receiving a part of the coupling bolt, andwherein the second flat ridge aligns with the first flat ridge.2. The device of ...

SECONDARY SEAL IN A NON-CONTACT SEAL ASSEMBLY

A seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis. The seal assembly includes a seal carrier, a primary seal, a mid plate, at least one secondary seal, and a front plate. The at least one secondary seal interfaces with the front plate and the mid plate. A harder material is introduced at the interface of the mid plate and the front plate with the at least one secondary seal, that is made from a more wear resistant material than the other components at the interface, to provide the other component/s as a wear component that is replaced more often. 1. A seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis in the axial direction , comprising:a seal carrier that holds all the components of the seal assembly together along an outer ring; at least one shoe extending along one of the first and second machine components, producing a non-contact seal therewith, the shoe being formed with a slot;', 'at least one spring element adapted to connect to one of the first and second machine components, and being connected to the at least one shoe, the at least one spring element being effective to deflect and move with the at least one shoe in response to fluid pressure applied to the at least one shoe by a fluid stream to assist in the creation of a primary seal of the circumferential gap between the first and second machine components;, 'a primary seal comprisinga mid plate comprising a groove, extending into the slot formed in the at least one shoe;at least one secondary seal comprising at least one sealing element, the at least one sealing element is flush into the groove of the mid plate and extend into the slot formed in the at least one shoe, sealing the at least one spring element in ...

Box Rim Cavity for a Gas Turbine Engine

A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.

TURBINE

A turbine is provided with a seal device. The seal device includes: at least one step surface disposed in a region of an outer peripheral surface of a rotor facing a shroud of a stationary vane in the radial direction of the rotor, the at least one step surface facing upstream in a flow direction of the fluid and dividing the region of the outer peripheral surface into at least two sections in an axial direction of the rotor: at least two seal fins protruding toward the at least two sections from the stationary vane and facing the at least two sections via a seal gap; and a swirling-component application portion disposed on an end side of the shroud of the stationary vane with respect to the axial direction of the rotor and configured to be capable of applying a swirling component to the fluid flowing toward the seal gap. 1. A turbine , comprising:a casing;a rotor extending inside the casing;a plurality of rotor blades fixed to the rotor and arranged in a circumferential direction of the rotor:a plurality of stationary vanes fixed to the casing and arranged in the circumferential direction of the rotor, each of the stationary vanes having a vane body and a shroud which is connected to the vane body and which faces an outer peripheral surface of the rotor via a clearance in a radial direction of the rotor; anda seal device capable of restricting a flow of a fluid in he clearance, at least one step surface disposed in a region of the outer peripheral surface of the rotor facing the shroud of the stationary vane in the radial direction of the rotor, the at least one step surface facing upstream in a flow direction of the fluid and dividing the region of the outer peripheral surface into at least two sections in an axial direction of the rotor;', 'at least two seal fins protruding toward the at least two sections from the stationary vane and facing the at least two sections via a seal gap; and', 'a swirling-component application portion disposed on an end side of the ...

NUT FOR AXIALLY LOCKING A BEARING RING IN A TURBOMACHINE

A nut for a turbine engine, in particular for axially locking a bearing race. The nut comprises a thread for screwing onto a part of the turbine engine, and a lock for ensuring the nut cannot rotate relative to the engine part. The nut further comprises at least one dynamic seal. 1. A nut for a turbine engine , the nut comprising:a thread configured to screw onto a part of the turbine enginelocking means for ensuring the nut cannot rotate relative to said partat least one dynamic sealing means,wherein said nut comprises a part having a substantially C or U-shaped axial section of which the opening is oriented axially, said part comprising inner and outer substantially cylindrical walls, said thread being located on the inner substantially cylindrical wall, and said dynamic sealing means being located on the outer substantially cylindrical wall.2. The nut according to claim 1 , comprising two independent dynamic sealing means.3. The nut according to claim 1 , wherein the sealing means comprises a series of annular wipers claim 1 , crescent-shaped holes claim 1 , a sealing surface claim 1 , a twist and/or an element of a labyrinth sealing joint.4. The nut according to claim 1 , comprising an outer radial wall which forms a deflector.5. The nut according to claim 4 , wherein said outer radial wall is located at a downstream end of said outer substantially cylindrical wall.6. The nut according to claim 1 , wherein another dynamic sealing means is located on an axial extension upstream of said inner substantially cylindrical wall.7. The nut according to claim 1 , comprising centring means claim 1 , independent of said thread claim 1 , and designed to engage with said part.8. The nut according to claim 1 , wherein said locking means comprise an inner radial rim which comprises axial recesses which are designed to receive axial lugs of a locking ring.9. The nut according to claim 1 , wherein said opening is designed to define a cooling cavity.10. A turbine engine claim 1 , ...

NON-CONTACT SEAL WITH NON-STRAIGHT SPRING BEAM(S)

An assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes to the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to the first seal shoe. The second mount is connected to the seal base and disposed a circumferential distance away from the first mount. The spring beam extends longitudinally along a non-straight centerline between and connected to the first mount and the second mount. 1. An assembly for rotational equipment , comprising:a plurality of seal shoes arranged around an axis in an annular array, the seal shoes comprising a first seal shoe;a seal base circumscribing the annular array of the seal shoes; and a first mount connected to the first seal shoe;', 'a second mount connected to the seal base and disposed a circumferential distance away from the first mount; and', 'a spring beam extending longitudinally along a non-straight centerline between and connected to the first mount and the second mount., 'a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes and the seal base, the spring elements comprising a first spring element that includes2. The assembly of claim 1 , wherein the non-straight centerline is a generally arcuate centerline.3. The assembly of claim 1 , wherein the non-straight centerline extends circumferentially about the axis.4. The assembly of claim 1 , wherein the non-straight centerline has a substantially constant radius to the axis as the spring beam extends longitudinally between the first mount and the second mount.5. The assembly of claim 1 , wherein the non-straight centerline has a variable radius to the axis as the spring ...

HYDROSTATIC NON-CONTACT SEAL WITH SEAL CARRIER ELIMINATION

Aspects of the disclosure are directed to a non-contact seal assembly comprising a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing the annular array of the seal shoe, the seal base comprising first, second and third inner radial seal base surfaces where the third inner radial seal base surface is axially between the first and second inner radial seal base surfaces and is radially proximate the centerline with respect to the radially distal first and second inner radial seal base surfaces. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes and radially proximate the third inner radial seal base surface. 1. A non-contact seal assembly , comprising:a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end;a seal base circumscribing the annular array of the seal shoe, the seal base comprising first, second and third inner radial seal base surfaces where the third inner radial seal base surface is axially between the first and second inner radial seal base surfaces and is radially proximate the centerline with respect to the radially distal first and second inner radial seal base surfaces; anda plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes and radially proximate the third inner radial seal base surface.2. The non-contact seal assembly of claim 1 , further comprising a first ring structure configured and arranged to at least one of position claim 1 , support or mount to a secondary seal ...

HYDROSTATIC NON-CONTACT SEAL WITH OFFSET OUTER RING

A non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing axially offset from the annular array of the seal shoes. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes, and each of the plurality of spring elements is axially adjacent to the seal base. 1. A non-contact seal assembly , comprising:a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end;a seal base circumscribing axially offset from the annular array of the seal shoes; anda plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes, and each of the plurality of spring elements is axially adjacent to the seal base.2. The non-contact seal assembly of claim 1 , where the seal base is connected to a seal carrier surface that is substantially cylindrical and extends circumferentially around and faces towards the centerline.3. The non-contact seal assembly of claim 1 , further comprising a first ring structure configured and arranged to at least one of position claim 1 , support or mount to a secondary seal device axially separated from the seal base and radially adjacent to the first seal shoe4. The non-contact seal assembly of claim 1 , further comprising a secondary seal device axially and radially adjacent to the seal base and axially adjacent to first the seal shoe.5. The non-contact seal assembly of claim 1 , where the seal assembly comprises nickel alloy.6. The non-contact assembly of claim 1 , where the ...

NON-CONTACT SEAL WITH PROGRESSIVE RADIAL STOP(S)

An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes. 1. An assembly for rotational equipment , comprising:a plurality of seal shoes arranged around an axis in an annular array;a seal base circumscribing the annular array of the seal shoes;a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes and the seal base, a first of the spring elements including a first mount, a second mount and a spring beam, the first mount connected to a first of the seal shoes, the second mount connected to the seal base, and the spring beam extending longitudinally between and connecting the first mount and the second mount; anda frangible element configured to restrict radial outward movement of the first of the seal shoes.2. The assembly of claim 1 , wherein the frangible element is configured to progressively restrict the radial outward movement of the first of the seal shoes.3. The assembly of claim 1 , whereinthe frangible element is adapted to enable a first magnitude of the radial outward movement of the first of the seal shoes during a first mode of operation;the frangible element is adapted to enable a second magnitude of the radial outward movement of the first of the seal shoes during a ...

Fish mouth seal carrier

A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier.

Fluid Flow Machine

A fluid flow machine, in particular turbocompressor, with a housing, having a rotor mounted in the housing, and with a dry gas seal for sealing the rotor relative to the housing. The housing at least one recess or bore for a gaseous medium is introduced, via which the gaseous medium for temperature-controlling the dry gas seal can be conducted in the direction of the same. The gaseous medium can be directly conducted into a gas space formed between the housing and the dry gas seal via the or each recess or bore. Additionally or alternatively, the or each recess or bore receives a guide tube for the gaseous medium.

SWIRL INTERRUPTION SEAL TEETH FOR SEAL ASSEMBLY

A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics. 1. A seal assembly for sealing between a rotating component and a stationary component in a turbomachine , the seal assembly comprising:a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough, the axially extending hole extending through the at least one of the plurality of teeth from an upstream, high-pressure side to a downstream, low-pressure side of the at least one tooth and being distanced radially inwardly from a radially innermost surface of an arcuate packing ring,wherein the upstream, high-pressure side is in fluid communication with the downstream, low-pressure side via the at least one axially extending hole.2. The seal assembly of claim 1 , wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth on the upstream claim 1 , high-pressure side.3. The seal assembly of claim 1 , wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth and a second tooth on the upstream claim 1 , high-pressure side.4. The seal assembly of claim 1 , wherein the plurality of teeth comprise arcuate segments of teeth claim 1 , and wherein the at least one hole comprises a plurality of circumferentially spaced holes along the arcuate portion of teeth.5. The seal assembly of claim 1 , wherein the plurality of holes comprise ...

ASPIRATING SEAL ASSEMBLY AND METHOD OF ASSEMBLING

An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface. 1. An aspirating seal assembly for use in a turbine engine including a stator assembly and a rotor assembly , said aspirating seal assembly comprising:a face seal of the stator assembly, said face seal comprising a first annular seal surface;a rotary component of the rotor assembly, said rotary component comprising a second annular seal surface positioned adjacent said first annular seal surface and defining a seal interface therebetween, wherein said face seal is configured to discharge a flow of air towards said seal interface;a first seal member extending between said first and second annular seal surfaces such that the flow of air induces a pressure drop across said seal interface; anda second seal member positioned radially inward from said first seal member and extending between said first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, wherein a length of said second seal member is selected to increase the back pressure induced across said seal interface.2. The assembly in accordance with claim 1 , wherein the length of said ...

SEAL STRUCTURE AND ROTARY MACHINE

In a seal structure that seals a gap between a first structure and a second structure which faces the first structure in a radial direction and rotates relative to the first structure, one of the first structure and the second structure has a base surface and a step surface that protrudes toward the other side from the base surface, and the other is provided with: a first fin which extends toward the step surface and forms a first gap between the step surface; a second fin that, on the downstream side of the first fin, extends toward the base surface and forms a second gap between the base surface; and a protrusion part that is disposed between the first fin and the second fin and that divides a leak flow, into a first vortex along the first fin and a second vortex along the second fin. 1. A seal structure that seals a gap between a first structure and a second structure which faces the first structure in a radial direction and rotates relative to the first structure about an axis , whereinone of the first structure and the second structure has a base surface and a step surface that protrudes toward the other side from the base surface,wherein the other is provided with:a first fin which extends toward the step surface and forms a first gap at a space with respect to the step surface;a second fin that, on a downstream side of the first fin, extends toward the base surface and forms a second gap at a space with respect to the base surface; anda protrusion part that is disposed between the first fin and the second fin and that divides a leak flow which has passed through the first gap, into a first vortex along the first fin and a second vortex along the second fin,and wherein the protrusion part includes a reattachment edge that extends in the circumferential direction and causes the leak flow to be reattached thereon, wherein the reattachment edge is provided in a position between a downstream side end part of the step surface and the second fin in the axial ...

GAS TURBINE ENGINE TURBINE VANE RING ARRANGEMENT

A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes. 1. A gas turbine engine comprising:an engine static structure;a compressor section;a combustor fluidly connected downstream from the compressor section;a turbine section fluidly connected downstream from the combustor and including high and low pressure turbine sections;a vane pack arranged in one of the compressor or turbine sections, the vane pack including a reinforcement ring secured around an annular arrangement of vanes and extending proud of an axial end of the vanes to an end, the end interleaving with an adjacent rotating component to provide a seal; anda sealing ring supported by the engine static structure and engaged with the reinforcement ring.2. The gas turbine engine according to claim 1 , wherein the vane pack is arranged in the turbine section.3. The gas turbine engine according to claim 1 , wherein the rotating component include one of a pocket and a lip claim 1 , the reinforcement ring providing the other of the pocket and the lip claim 1 , the lip arranged in the pocket to provide the seal.4. The gas turbine engine according to claim 3 , wherein the rotating component is a stage of rotating blades is provided by the high pressure turbine section claim 3 , and the vane pack provides a mid-turbine frame.5. The gas turbine engine according to claim 1 , wherein the vanes are hung from the engine static structure.6. The gas turbine engine according to claim 1 , wherein the end includes an annular lip that is received in an annular pocket of the rotating component.7. The gas turbine engine according to claim 1 , wherein the reinforcement ring and the vanes include interlocking features engaging one another and configured to prevent relative axial movement between the reinforcement ring and the vanes.8. The gas turbine engine according to claim 1 , wherein the reinforcement ring is secured to ...

NON-CONTACT SEAL WITH RESILIENT BIASING ELEMENT(S)

A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount. 1. An assembly for rotational equipment , comprising:a seal device comprising a plurality of seal shoes, a seal base, a plurality of spring elements and a coil spring;the seal shoes arranged around an axis in an annular array;the seal base circumscribing the annular array of the seal shoes;each of the spring elements radially between and connecting a respective one of the seal shoes and the seal base, a first of the spring elements including a first mount, a second mount and a spring beam, the first mount connected to a first of the seal shoes, the second mount connected to the seal base, and the spring beam connecting the first mount to the second mount; andthe coil spring radially between and engaged with first and second components of the seal device, the first component comprising the first of the spring elements.2. The assembly of claim 1 , wherein the coil spring is configured to increase a stiffness of the first of the spring elements.3. The assembly of claim 1 , wherein the coil spring is configured to bias a first portion of the first of the seal shoes radially away from the seal base and a second portion of the first of the seal shoes radially towards the seal base.4 ...

SEAL ASSEMBLY FOR SEALING AN AXIAL GAP BETWEEN COMPONENTS

A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component. 1. An assembly for a turbine engine , comprising:a turbine engine first component;a turbine engine second component; andan annular seal assembly extending along an axis and sealing a radial gap between the first component and the second component;the annular seal assembly including a seal carrier and a seal element;the seal element extending between a first portion and a second portion;the first portion slidingly arranged within a slot in a radial side of the seal carrier; andthe second portion radially engaging the second component.2. The assembly of claim 1 , wherein the slot extends axially and radially inward into the seal element from the radial side.3. The assembly of claim 1 , wherein an included angle between the second portion of the seal element and the second component is an acute angle.4. The assembly of claim 1 , wherein the second portion of the seal element contacts the second component.5. The assembly of claim 1 , wherein an axial end of the seal carrier axially contacts the first component.6. The assembly of claim 1 , whereinthe annular seal assembly further includes a second seal element extending between a first portion and a second portion;the first portion of the second seal element is slidingly arranged within a second slot in a second radial side of the seal carrier; andthe second portion of the second seal element radially engages the first component.7. The assembly of claim 1 , whereinthe annular seal assembly further ...

Seal Assembly for Counter Rotating Turbine Assembly

The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion. 1. A gas turbine engine , comprising:a first turbine rotor, the first turbine rotor comprising a rotatable outer shroud;a turbine frame surrounding the rotatable outer shroud of the first turbine rotor;a seal assembly positioned in operable arrangement at the turbine frame and the turbine rotor, the seal assembly comprising a fluid bearing positioned between the first turbine rotor and the turbine frame.2. The engine of claim 1 , wherein the seal assembly is an aspirating face seal assembly.3. The engine of claim 1 , the engine comprising a clearance gap between a second turbine rotor and the rotatable outer shroud of the first turbine rotor claim 1 , the second turbine rotor rotatable at a speed different from the first turbine rotor.4. The engine of claim 3 , wherein the clearance gap is between a radially outward end of an airfoil of the second turbine rotor and the rotatable outer shroud of the first turbine rotor.5. The engine of claim 1 , wherein the first turbine rotor comprises a first tooth structure and a second tooth structure each extended toward the seal assembly.6. The engine of claim 5 , wherein the fluid bearing is positioned between the first tooth structure ...

HYDROSTATIC SEAL WITH ABRADABLE TEETH FOR GAS TURBINE ENGINE

A hydrostatic seal assembly includes a seal support, a seal shoe integral to the seal support and radially movable relative to the seal support. A plurality of seal teeth are located at a radially inboard surface of the seal shoe. The seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component. 1. A hydrostatic seal assembly , comprising:a seal support;a seal shoe integral to the seal support and radially movable relative to the seal support;a plurality of seal teeth disposed at a radially inboard surface of the seal shoe; anda secondary seal located upstream of the seal shoe, the secondary seal configured to prevent airflow to and/or from a seal cavity located radially outboard of the seal shoe at an upstream side of the seal assembly;wherein the seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component.2. The hydrostatic seal of claim 1 , wherein the second material is a metal alloy.3. The hydrostatic seal of claim 1 , wherein the second material is tin or lead based babbitt material.4. The hydrostatic seal of claim 1 , wherein a seal surface between adjacent seal teeth of the plurality of seal teeth is formed from the second material.5. The hydrostatic seal of claim 1 , wherein the radially inboard surface is formed via a coating process.6. The hydrostatic seal of claim 1 , wherein the radially inboard surface is formed via one or more of a spray claim 1 , plating or dip process.7. The hydrostatic seal of claim 1 , further comprising one or more seal beams connecting the seal support to the seal shoe.8. A turbine ...

SEAL RING

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe. 1. A seal , comprising: 'a first petal extending radially inward with respect to the first central axis of the first seal ring;', 'a first seal ring having a first central axis, the first seal ring comprising 'a second petal axially proximate the first petal, offset from the first petal in a circumferential direction, and extending radially inward with respect to the second central axis of the second seal ring;', 'a second seal ring having a second central axis substantially equal to the first central axis, the second seal ring comprising;'}a sealing disk axially proximate the second seal ring and having a seal shoe configured as a primary seal, wherein the second petal extends toward the seal shoe.2. The seal of claim 1 , wherein the first seal ring comprises a first plurality of separate segments and the second seal ring comprises a second plurality of separate segments.3. The seal of claim 1 , wherein the second seal ring further comprises a lip configured to engage the seal shoe.4. The seal of claim 1 , wherein the first seal ring is on a high-pressure side in a gas turbine engine and the second seal ring is on a low-pressure side in ...

Gas turbine casing thermal control device

A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.

ROTATING SEAL CONFIGURATION AND METHOD OF SEALING A ROTATING MEMBER TO A HOUSING

A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face. 1. A rotating seal configuration , comprising:a housing; anda rotatable member rotationally mounted relative to the housing having at least one portion defining an outer perimetrical face being configured to contact the housing during some operational conditions, the at least one portion having opposing axial surfaces with at least one of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.2. The rotating seal configuration of claim 1 , wherein the outer perimetrical face is oriented substantially parallel to a rotational axis of the rotatable member.3. The rotating seal configuration of claim 1 , wherein an angle between the outer perimetrical face and each of the opposing axial surfaces is acute.4. The rotating seal configuration of claim 1 , wherein the outer perimetrical face cuts into the housing in response to contact therewith while the rotatable member is rotating.5. The rotating seal configuration of claim 1 , wherein the rotating seal configuration is configured such that neither of the opposing axial surfaces make contact with the housing after the rotatable member has cut a groove into the housing.6. The rotating seal configuration of claim 1 , wherein the at least one portion is ...

BEARING COMPARTMENT SEALING SYSTEM WITH PASSIVE COOLING

The present disclosure relates to sealing systems for bearing compartments. In one embodiment, a sealing system includes a runner configured to extend circumferentially around a rotating component, the runner is formed of a material with low radial thermal growth and is configured to tit to the rotating component to remove heat away from the runner. The runner can include an outer surface configured to provide passive cooling for the runner in the bearing compartment. The sealing system can also include a seal configured to operate with the runner, wherein the seal includes a clearance seal on an air side of the runner. The runner can be configured to operate without direct oil cooling. 1. A sealing system for a bearing compartment comprising:a runner configured to extend circumferentially around a rotating component, wherein the runner is formed of a material with low radial thermal growth, wherein the runner is configured to fit to the rotating component to remove heat away from the runner and wherein the runner includes an outer surface configured to provide passive cooling for the runner in the bearing compartment; anda seal configured to operate with the runner, wherein the seal includes a clearance seal on an air side of the runner.2. The sealing system of claim 1 , wherein the runner is substantially cylindrical with a hollow core configured for the rotating component.3. The sealing system of claim 1 , wherein the material of the runner includes a nickel alloy.4. The sealing system of claim 1 , wherein the runner is configured to be fit to the rotating shaft by an interference fit.5. The sealing system of claim 1 , wherein the outer surface of the runner extends into the bearing compartment a distance in order to receive passive oil to cool the runner.6. The sealing system of claim 1 , wherein the runner is configured to operate without direct oil cooling.7. The sealing system of claim 1 , wherein the runner includes a substantially rectangular cutout along ...

TURBINE STATOR, STEAM TURBINE, AND PARTITION PLATE

A turbine stator includes a partition plate including an inner ring that extends along a circumferential direction, an outer ring that is disposed on an outer side of the inner ring in a radial direction, and extends in the circumferential direction, a plurality of nozzles that are disposed in the circumferential direction between the inner ring and the outer ring, and are configured to guide a fluid from an upstream side toward a downstream side in an axial direction, and an annular protruding portion, protrudes from the outer ring to the downstream side in the axial direction, and extends along the outer ring in the circumferential direction, and a casing surrounding the partition plate from the outer side in the radial direction, and having a contact support surface that is in contact with the annular protruding portion from the downstream side in the axial direction. 1. A turbine stator comprising:a partition plate including an inner ring that extends along a circumferential direction around an axis, an outer ring that is disposed on an outer side with respect to the inner ring in a radial direction with respect to the axis, and extends in the circumferential direction, a plurality of nozzles that are disposed between the inner ring and the outer ring in the circumferential direction, and are configured to guide a fluid from an upstream side toward a downstream side in an axial direction in which the axis extends, and an annular protruding portion, protrudes from the outer ring to the downstream side in the axial direction, and extends along the outer ring in the circumferential direction; anda casing surrounding the partition plate from the outer side in the radial direction, and having a contact support surface that is in contact with the annular protruding portion from the downstream side in the axial direction.2. The turbine stator according to claim 1 , wherein the annular protruding portion protrudes to the outer side in the radial direction from an outer ...

SHROUDED BLADE ASSEMBLIES

A rotor system for a gas turbine engine may comprise a shrouded blade assembly. The shrouded blade assembly may include a blade configured to rotate about a central longitudinal axis of the gas turbine engine, an inner diameter shroud located at a proximal end of the blade, and a blade tip shroud located at a distal end of the blade. A radial seal assembly may be located radially outward of a distal surface of the blade tip shroud. 1. A rotor system for a gas turbine engine , comprising: a blade configured to rotate about a central longitudinal axis of the gas turbine engine;', 'an inner diameter shroud located at a proximal end of the blade; and', 'a blade tip shroud located at a distal end of the blade; and, 'a shrouded blade assembly comprisinga radial seal assembly located radially outward of a distal surface of the blade tip shroud.2. The rotor system of claim 1 , wherein the radial seal assembly comprises a non-contact radial seal.3. The rotor system of claim 2 , wherein the non-contact radial seal comprises a shoe and a housing supporting the shoe claim 2 , wherein the shoe is configured to translate towards the distal surface of the blade tip shroud in response to a pressure differential between a forward end of the shoe and an aft end of the shoe.4. The rotor system of claim 3 , wherein the non-contact radial seal is configured to maintain a predetermined clearance between a proximal edge of the shoe and the distal surface of the blade tip shroud.5. The rotor system of claim 4 , wherein the non-contact radial seal is configured such that at the predetermined clearance an equilibrium is established preventing the shoe from translating radially inward.6. The rotor system of claim 3 , further comprising a support structure located radially outward of the radial seal assembly claim 3 , wherein the housing is contacting the support structure.7. The rotor system of claim 1 , wherein an axial length of the blade tip shroud is greater than a chord of the blade.8. ...

Helical seal system for a turbomachine

A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.

Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine

A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange. 1. A turbine assembly , comprising:a rotor;at least one bucket extending radially from the rotor;a stator assembly positioned adjacent to the at least one bucket; and a first flange extending from the at least one bucket in a substantially axial direction; and', 'a second flange extending from the stator assembly in a substantially axial direction opposite the first flange, wherein the second flange comprises at least one protuberance projecting towards the first flange., 'a seal assembly, comprising2. The turbine assembly of claim 1 , wherein the at least one protuberance is disposed about a distal end of the second flange.3. The turbine assembly of claim 1 , wherein the at least one protuberance is disposed between a distal end of the second flange and the stator assembly.4. The turbine assembly of claim 1 , further comprising a second at least one protuberance projecting from the distal end of the second flange in the substantially axial direction opposite the first flange.5. The turbine assembly of claim 1 , wherein the second flange comprises a discourager seal.6. The turbine assembly of claim 1 , wherein the first flange comprises an angle wing seal.7. The turbine assembly of claim 1 , wherein the first flange and the second flange define a gap therebetween.8. The turbine assembly of claim 1 , wherein the at ...

Cover plate for a rotor assembly of a gas turbine engine

A cover plate according to an exemplary aspect of the present disclosure includes, among other things, a body, a first tab near a bore of the body, and a second tab circumferentially spaced from the first tab. A slot is defined between the first tab and the second tab, the first tab, the second tab and the slot extending at an angle relative to a slot axis that extends through the bore. In another embodiment, the cover plate includes a bumper that limits deflection of the body.

SEAL ASSEMBLY FOR A BEARING ASSEMBLY IN A GAS TURBINE ENGINE

A seal assembly for a bearing assembly in a gas turbine engine includes a first annular runner disposed around a shaft rotatable about an axis defining an axial direction. The first annular runner is rotatable with the shaft about the axis. A seal element is spaced apart from the first annular runner and cooperating therewith to provide a gap seal. An annular lip axially extends from the gap seal to an open end. The lip is disposed at least partially around the seal runner. A second annular runner is disposed coaxially with and spaced radially apart from the lip. The second annular runner extends axially opposite to the lip so as to provide a tortuous path leading to the open end of the lip. A restrictor extends between the lip and the second annular runner to impede the passage oil through the tortuous path to the open end of the lip. 1. A seal assembly for a bearing assembly in a gas turbine engine , the seal assembly comprising:a first annular runner disposed around a shaft rotatable about an axis defining an axial direction, the first annular runner rotatable with the shaft about the axis;a seal element spaced apart from the first annular runner and cooperating therewith to provide a gap seal;an annular lip axially extending from the gap seal to an open end, the lip disposed at least partially around the seal runner;a second annular runner disposed coaxially with and spaced radially apart from the lip, the second annular runner extending axially opposite to the lip so as to provide a tortuous path leading to the open end of the lip; anda restrictor extending between the lip and the second annular runner to impede the passage oil through the tortuous path to the open end of the lip.2. The seal assembly of claim 1 , where in the second annular runner is disposed radially outwardly of the lip.3. The seal assembly of claim 1 , wherein the lip is generally parallel to the first annular runner.4. The seal assembly of claim 1 , wherein the restrictor is a lip extending ...

METHOD FOR PRODUCING A ROTOR OF A CHARGING APPARATUS

A method of producing a rotor of a charging apparatus may include the steps of providing at least one compressor wheel and a turbine wheel. The compressor wheel and the turbine wheel may each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bearing housing. At least one of the radial bearing surfaces may include a radial oversizing corresponding to a rotationally asymmetric geometry between at least the bearing section of the compressor wheel and the bearing section of the turbine wheel. The method may include the step of assembling the compressor wheel, the turbine wheel and each bearing section together to form a unitary structure, and machining the at least one of the radial bearing surfaces to reduce the respective radial oversizing until each of the radial bearing surfaces are rotationally symmetrical with respect to each other. 1. A method for producing a rotor of a charging apparatus , comprising the steps of: providing at least one compressor wheel and a turbine wheel , wherein the compressor wheel and the turbine wheel each include a bearing section having a radial bearing surface at a longitudinal end for mounting a bearing housingwherein at least one of the radial bearing surfaces includes a radial oversizing corresponding to a rotationally asymmetric geometry between at least the bearing section of the compressor wheel and the bearing section of the turbine wheel,assembling the compressor wheel, the turbine wheel and each bearing sections together to form a unitary structure, andmachining the at least one of the radial bearing surfaces to reduce the respective radial oversizing until each of the radial bearing surfaces are rotationally symmetrical with respect to each other.2. The method according to claim 1 ,wherein the step of assembling the compressor wheel, the turbine wheel and each bearing section together further includes connecting the turbine wheel compressor wheel via a labyrinth seal, andmachining ...

METHOD FOR SEALING AN ANNULAR GAP IN A TURBINE, AND TURBINE

Provided is a method for sealing an annular gap in a turbine with a housing and a rotor, in which method a) an annular recess, which is arranged coaxially with respect to the rotor and opposite the tips of the rotor blades of a stage, is provided in the housing or in at least one element attached to the housing, b) a subdivided insert ring, which is formed such that it can be inserted into the recess in a form-fitting manner with play, is provided, c) the insert ring is inserted into the recess, more particularly in that the insert ring is pushed into the recess at least substantially in the axial direction, and d) the insert ring is fixed using securing elements in such a way that an at least substantially axially directed clamping force is applied by means of the securing elements. A turbine is also provided. 1. A method for sealing an annular gap in a turbine having a casing and a rotor which is arranged in the casing , is mounted so that it can rotate about its central longitudinal axis , and is equipped with a plurality of rotor blade stages , in whicha) an annular depression, coaxial with the rotor and situated opposite the tips of the rotor blades of a stage, is provided in the casing or in at least one element fastened to the casing,b) a split insert ring is provided which is designed such that it is inserted positively into the depression with play,c) the insert ring is inserted into the depression by the insert ring being pushed into the depression in an at least essentially axial direction, andd) the insert ring is fixed with fastening elements in such a way that an at least essentially axially directed tensile force is applied by means of the fastening elements.2. The method as claimed in claim 1 , wherein the insert ring is fixed by elongated fastening elements claim 1 , wherein the elongated fastening elements are screws and/or threaded rods and/or bolts claim 1 , which are inserted at least essentially axially into the insert ring.3. The method as ...

Turbomachinery sealing apparatus and method

A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

LABYRINTH SEAL ASSEMBLY

A labyrinth seal assembly for a gas turbine engine having a rotatable shaft. The labyrinth seal assembly has: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine, the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing, the insulation layer composed of a material different than those used for the seal stator and the housing. 1. A labyrinth seal assembly for a gas turbine engine having a rotatable shaft , the labyrinth seal assembly comprising: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine , the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing , the insulation layer composed of a material different than those used for the seal stator and the housing.2. The labyrinth seal assembly of claim 1 , wherein the material is air and the insulation layer includes an air gap extending from the seal stator to the housing outside the cavity.3. The labyrinth seal assembly of claim 1 , wherein the seal stator is connected to the housing at an inboard side of the seal stator.4. The labyrinth seal assembly of claim 1 , wherein the seal rotor is spaced apart from the shaft by an air gap located outside the cavity.5. The labyrinth seal assembly of claim 1 , further comprising a second labyrinth seal claim 1 , the cavity located between the labyrinth seal and the second labyrinth seal claim 1 , the second labyrinth seal having a second seal stator in sealing engagement with a second seal rotor claim 1 , the second seal stator secured to the housing claim 1 , a second insulation layer between the second seal stator and the housing.6. The labyrinth seal assembly ...

APPARATUS AND METHOD FOR SECURING SEALING ELEMENTS

The invention relates to an apparatus () for securing sealing elements () in a recess (), more particularly in an installation slot in a turbomachine, having at least one sealing support element () comprising at least one sealing element (). At least one fixing piece () is fitted between the sealing support element () and a clamping piece () associated with the sealing support element (), and the fixing piece () is integrally joined to the sealing support element () and the clamping piece () by strut-like connections () that can be broken by the application of force. The invention also relates to a securing method and to a method for manufacturing the claimed apparatus (). 112141812142018221820182224. An apparatus for securing sealing elements ( , ) in an installation slot formed in a turbomachine , having at least one sealing support element () comprising at least one sealing element ( , ) wherein at least one fixing piece () is disposed between the sealing support element () and a clamping piece () associated with the sealing support element () , wherein the fixing piece () can be joined integrally to the sealing support element () and to the clamping piece () by strut-like connections () that can be broken off by means of applying force.2202018222020182216. The apparatus according to claim 1 , wherein the fixing piece () is formed in such a way that when the connection is broken between the fixing piece () and the sealing support element () claim 1 , and between the clamping piece () and the fixing piece () claim 1 , a force closure is achieved between the fixing piece () claim 1 , the sealing support element () claim 1 , the clamping piece () and side walls of the recess ().31812. The apparatus according to wherein the sealing support element () is formed as a housing for the uptake of the sealing element ().412. The apparatus according to claim 3 , wherein the sealing element () is formed as a brush seal.5181414. The apparatus according to claim 1 , wherein the ...

GAS TURBINE COOLING SYSTEMS AND METHODS

A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part. 2. The gas turbine of claim 1 , comprising:a sealing fin attached to the rotor casing, the vane or the rotating part and extending into the gap.3. The gas turbine of claim 2 , wherein the sealing fin is moveable in a direction of the rotation axis.4. The gas turbine of claim 3 , comprising:a pneumatic system configured and arranged to move the sealing fin in the direction of the rotation axis.5. The gas turbine of claim 3 , comprising:bolts that are configured and arranged to move the sealing fin in the direction of the rotation axis.6. The gas turbine of claim 5 , wherein the bolts comprise:a first type of bolt and a second type of bolt, configured and arranged so that when the first type of bolt is tightened it will move the sealing fin towards the blade, and when the second type of bolt is tightened it will move the sealing fin away from the blade.7. The gas turbine of claim 1 , comprising:a sealing plate extending adjacent to the fir tree on the side of the gap opposite the rotor casing, the sealing plate having at least one hole configured and arranged to allow cooling fluid from the gap to enter a fir tree cooling channel, wherein the fir tree cooling channel is arranged between the rotor and the fir tree.8. The gas turbine of claim 7 , comprising:at least one rib attached to the side of ...

SELF CRYSTALLINE ORIENTATION FOR INCREASED COMPLIANCE

Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation. 1. A seal comprising:a shoe; andat least one beam coupled to the shoe,wherein the seal includes a single crystal material with a predetermined crystalline orientation.2. The seal of claim 1 , wherein the single crystal material is a nickel-based alloy.3. The seal of claim 1 , wherein the orientation accommodates a requirement associated with at least a geometrical profile of the seal.4. The seal of claim 3 , wherein the geometrical profile is specified in terms of at least a radius of the seal.5. The seal of claim 3 , wherein the geometrical profile is specified in terms of at least a length of the at least one beam.6. The seal of claim 1 , wherein the orientation accommodates a requirement associated with at least a natural frequency associated with the seal.7. The seal of claim 6 , wherein the orientation provides for the natural frequency being greater than a frequency associated with a speed of a rotating component in an amount that is greater than a threshold.8. The seal of claim 1 , wherein the orientation accommodates a requirement associated with at least a range of deflection associated with the seal.9. The seal of claim 1 , wherein the seal is included in an engine.10. The seal of claim 1 , wherein the seal is included in an engine of an aircraft.11. The ...

Seal device for turbine, turbine, and thin plate for seal device

A seal device for a turbine includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor, each of the thin plates including a root portion disposed on an outer side in a radial direction of the rotor and supported on a stationary part of the turbine and a tip portion disposed on an inner side in the radial direction of the rotor and having a tip surface facing the outer peripheral surface of the rotor. Each of the thin plates is configured such that a width direction of the thin plate is parallel to an axial direction of the rotor at a side of the root portion, and the tip portion of each of the thin plates is configured such that an end on a side of the high-pressure space is positioned downstream of another end on a side of the low-pressure side.

NON-CONTACT SEAL WITH REMOVAL FEATURES

An assembly includes a plurality of seal shoes arranged about an axial centerline in an annular array. The assembly also includes a seal base and a plurality of spring elements. The seal base circumscribes the annular array of the seal shoes. A threaded base aperture extends axially through the seal base. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base. The spring elements are formed integral with the seal base and the seal shoes as a unitary body. 1. An assembly with an axial centerline , comprising:a plurality of seal shoes arranged about the centerline in an annular array;a seal base circumscribing the annular array of the seal shoes, wherein a threaded base aperture extends axially through the seal base; anda plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes with the seal base;wherein the spring elements are formed integral with the seal base and the seal shoes as a unitary body.2. The assembly of claim 1 , whereinthe threaded base aperture is one of a plurality of threaded base apertures arranged about the centerline in an annular array; andeach of the threaded base apertures extends axially through the seal base.3. The assembly of claim 2 , further comprising:a support ring including a surface that axially engages the seal base;wherein a ring aperture extends axially through the support ring, and the ring aperture is aligned with a first of the threaded base apertures; andwherein a second of the threaded base apertures is closed off by the surface.4. The assembly of claim 3 , wherein the ring aperture comprises a threaded ring aperture.5. The assembly of claim 2 , further comprising:a support ring including a surface that axially engages the seal base;wherein a plurality of ring apertures arranged about the centerline in an annular array, and each of the ring apertures extends axially through the support ring and is ...

LABYRINTH SEALING DEVICE

A device configured to seal a circumferential gap between a first turbomachine component and a second turbomachine component mutually rotatable about a longitudinal axis. The device is provided with a first sealing element connected to the first turbomachine component and with a second scaling element having an inner part provided with a plurality of projections extending towards the second machine component to define the teeth of a labyrinth seal between the high pressure region and the low pressure region of the turbo machine. The outer part of the second sealing element is connected to the first sealing element through an clastic element. One or more pressure chambers located between the first sealing element and the second sealing element are in fluid communication with the processing fluid of the turbomachine to derive a force acting on the outer part of the second scaling element in the direction of gap closure.

Non-contact seal for rotational equipment with axially extended seal shoes

An assembly is provided for rotational equipment. This rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially about an axial centerline in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the annular array. The spring elements include a first spring element. The first spring element connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. An axial end portion of the first seal shoe projects axially along the axial centerline, in a direction away from the first spring element, beyond the secondary seal assembly.

ROTARY MACHINE

A rotary machine includes: a stationary body having a stationary-side peripheral surface; a rotating body having a rotating-side peripheral surface facing the stationary side-peripheral surface. One surface which is one of the stationary-side peripheral surface and the rotating-side peripheral surface has an upstream-side peripheral surface, a downstream-side peripheral surface, and a rearward step surface. The other surface has an upstream-side seal fin forming a minute gap between the upstream-side seal fin and the upstream-side peripheral surface; a downstream-side seal fin forming a minute gap between the downstream-side seal fin and the downstream-side peripheral surface. The rearward step surface has a guide surface extending downstream Da while directed toward the other surface and connected to the upstream-side peripheral surface. 15-. (canceled)6. A rotary machine comprising:a stationary body having a stationary-side peripheral surface extending in a circumferential direction of an axis; anda rotating body that rotates around the axis and has a rotating-side peripheral surface facing the stationary-side peripheral surface,wherein one surface which is one of the stationary-side peripheral surface and the rotating-side peripheral surface includes:an upstream-side peripheral surface extending in an axial direction;a downstream-side peripheral surface that is located on a downstream side of a fluid on the upstream-side peripheral surface and extends in the axial direction and retreats from the other surface which is the other of the stationary-side peripheral surface and the rotating-side peripheral surface with respect to the upstream-side peripheral surface;a rearward step surface that connects the upstream-side peripheral surface and the downstream-side peripheral surface and faces the downstream side;an upstream-side seal fin extending from the other surface toward the upstream-side peripheral surface and forming a minute gap between the upstream-side seal ...

SEAL STRUCTURE AND TURBOMACHINE

There is provided a seal structure to suppress a leak flow of a working fluid from a gap between a rotating structure and a stationary structure, the rotating structure being configured to rotate in a prescribed direction about an axial center line, the stationary structure facing an outer periphery of the rotating structure in a radial direction with the gap inbetween, wherein the stationary structure has a cavity in which the rotating structure is accommodated, an inner peripheral surface of the cavity is provided with a seal fin that extends toward the axial center line and a plurality of stationary-side recesses arranged along a flow direction of the leak flow, and as compared with a first stationary-side recess disposed on a most upstream side, a second stationary-side recess disposed on an immediately downstream side of the first stationary-side recess is set to have a smaller depth dimension. 1. A seal structure to suppress a leak flow of a working fluid from a gap between a rotating structure and a stationary structure , the rotating structure being configured to rotate in a prescribed direction about an axial center line , the stationary structure facing au outer periphery of the rotating structure in a radial direction with the gap inbetween ,wherein the stationary structure has a cavity in which the rotating structure is accommodated,an inner peripheral surface of the cavity is provided with a seal fin that extends from the inner peripheral surface toward an inner periphery side and a plurality of stationary-side recesses provided from the inner peripheral surface toward an outer periphery side and arranged along a flow direction of the leak flow, andas compared with a first stationary-side recess disposed on a most upstream side in the flow direction, a second stationary-side recess disposed on an immediately downstream side of the first stationary-side recess in the flow direction is set to have a smaller depth dimension.2. The seal structure according ...

Method and Device for Sensorless Control of a Separately Excited Synchronous Machine

A blade wheel for a rotary electric machine may include a hollow cylindrical main body having an outer surface extending around an axis of rotation in a circumferential direction of the main body; a first end region and a second end region of the main body, each peripherally extending around the main body in the circumferential direction, the first and second end regions lying opposite each other in the direction of the axis of rotation; a recess extending along the outer surface and between the first end region and the second end region of the main body in the circumferential direction; and at least one web-shaped vortexing element extending within the recess and between the first and second end regions. The at least one vortexing element is designed to generate a movement of air away from the outer surface when the blade wheel rotates about the axis of rotation. 1. An impeller wheel for a rotating electric machine , the impeller wheel comprising:a hollow cylindrical base body having an outer peripheral surface, extending around an axis of rotation of the impeller wheel in a circumferential direction,a first end region that encircles the base body in the circumferential direction, and a second end region that encircles the base body in the circumferential direction, wherein the first end region and the second end region lie opposite one another in the direction of the axis of rotation,a groove extending along the peripheral surface in the circumferential direction, the groove extending between the first end region and the second end region of the base body, andat least one web-shaped impeller element that extends across the groove between the first end region and the second end region, such that at least one impeller element is configured to generate an air movement away from the peripheral surface during rotation of the impeller wheel about the axis of rotation.2. The impeller wheel of claim 1 , wherein the at least one impeller element at least partially ...

NON-CONTACT SEAL ASSEMBLY WITH CHAMFERED SEAL SHOE

An assembly is provided for rotational equipment. The assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged around an axis in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the annular array of seal shoes. The spring elements include a first spring element. The first spring element is radially between and connects the first seal shoe and the seal base. The first seal shoe extends circumferentially about the axis between a first end and a second end. The first seal shoe extends radially between an inner side and an outer side. The first seal shoe is configured with a chamfered corner at an interface between the first end and the inner side. 1. An assembly for rotational equipment , comprising:a plurality of seal shoes arranged around an axis in an annular array, the plurality of seal shoes comprising a first seal shoe;a seal base circumscribing the annular array of seal shoes; anda plurality of spring elements comprising a first spring element, the first spring element radially between and connecting the first seal shoe and the seal base;the first seal shoe extending circumferentially about the axis between a first end and a second end, and the first seal shoe extending radially between an inner side and an outer side;wherein the first seal shoe is configured with a chamfered corner at an interface between the first end and the inner side.2. The assembly of claim 1 , whereinthe chamfered corner comprises a corner surface; andthe corner surface is angularly offset from an inner surface of the first seal shoe at the inner side by an angle when viewed in a plane perpendicular to the axis.3. The assembly of claim 2 , wherein the inner surface has an arcuate sectional geometry.4. The assembly of claim 2 , wherein the angle is an obtuse included angle.5. The assembly of claim 2 , wherein the angle is equal to or greater than one hundred and thirty-five degrees and is ...

NON-CONTACT SEAL WITH AXIAL ENGAGEMENT

An assembly is provided for rotational equipment. This assembly includes a stationary structure, a rotating structure rotatable about an axial centerline, and a non-contact seal assembly. The non-contact seal assembly is configured to substantially seal a gap between the stationary structure and the rotating structure. The non-contact seal assembly includes a seal shoe configured to sealingly engage the rotating structure axially along the axial centerline. 1. An assembly for rotational equipment , comprising:a stationary structure;a rotating structure rotatable about an axial centerline; anda non-contact seal assembly configured to substantially seal an annular gap between the stationary structure and the rotating structure, the non-contact seal assembly comprising a seal shoe configured to sealingly engage the rotating structure axially along the axial centerline.2. The assembly of claim 1 , wherein the non-contact seal assembly is configured as a hydrostatic seal assembly.3. The assembly of claim 1 , wherein the seal shoe is a monolithic full hoop body.4. The assembly of claim 1 , wherein the seal shoe includes a seal shoe base and a seal shoe projection that projects axially along the axial centerline out from the seal shoe base towards the rotating structure.5. The assembly of claim 1 , whereinthe seal shoe sealingly engages and is axially adjacent a radially extending surface of the rotating structure;the radially extending surface of the rotating structure has a first radial height; andthe seal shoe has a second radial height that is less than or equal to the first radial height.6. The assembly of claim 1 , whereinthe non-contact seal assembly further comprises a seal carrier and a spring structure;the seal carrier is mounted to the stationary structure; andthe spring structure flexibly connects the seal shoe to the seal carrier.7. The assembly of claim 6 , whereinthe non-contact seal assembly further comprises a second spring structure; andthe second spring ...

LABYRINTH SEALING SYSTEM AND GAS TURBINE ENGINE WITH A LABYRINTH SEALING SYSTEM

A labyrinth seal system having at least two sealing fins arranged axially one behind the other on a rotor of a turbomachine and having a radially facing run-in element for the at least two sealing fins on a stator of the turbomachine, wherein in each case one radial sealing gap exists between the run-in element and the at least two sealing fins, wherein maxima of the radial sealing gaps are arranged offset with respect to one another in a circumferential direction, such that, in the region of the maxima, a passage exists in targeted fashion, for an air flow to the sealing fins that follow downstream, in the event of rubbing against the stator. This may be applied for example in a gas turbine engine. 1. A labyrinth seal system having at least two sealing fins arranged axially one behind the other on a rotor of a turbomachine and having a radially facing run-in element for the at least two sealing fins on a stator of the turbomachine , wherein in each case one radial sealing gap exists between the run-in element and the at least two sealing fins ,whereinmaxima of the radial sealing gaps are arranged offset with respect to one another in a circumferential direction, such that, in the region of the maxima, a passage exists in targeted fashion, for an air flow to the sealing fins that follow downstream, in the event of rubbing against the stator.2. The labyrinth seal system according to claim 1 , wherein minima of the radial extent of the at least two sealing fins are arranged offset with respect to one another in a circumferential direction.3. The labyrinth seal system according to claim 2 , wherein the maxima of the radial sealing gaps are generated by means of an eccentric offset of the sealing fins around the rotor.4. The labyrinth seal system according to claim 1 , wherein minima of the radial extent of the run-in element are arranged offset with respect to one another in a circumferential direction.5. The labyrinth seal system according to claim 4 , wherein run-in ...

NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT

Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal. 1. An assembly for rotational equipment , the assembly comprising:a first bladed rotor assembly;a second bladed rotor assembly including a rotor disk structure;a stator vane assembly axially between the first and the second bladed rotor assemblies;a stator structure mated with and radially within the stator vane assembly; anda seal assembly configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.2. The assembly of claim 1 , wherein the non-contact seal is a hydrostatic non-contact seal.3. The assembly of claim 1 , wherein the non-contact seal comprises:an annular base;a plurality of shoes arranged around and radially adjacent the rotor disk structure; anda plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the base.4. The assembly of claim 3 , wherein the base is configured with a monolithic full hoop body.5. The assembly of claim 1 , wherein the stator structure is floating radially within the stator vane assembly.6. The assembly of claim 1 , whereinthe first and the second bladed rotor assemblies are turbine rotor assemblies; andthe first bladed rotor assembly is upstream of the second bladed rotor assembly.7. The assembly of claim 1 , wherein the second bladed rotor assembly is coupled with the first ...

LEVERED JOINT

Described is a gas turbine engine, comprising: a first chamber and a second chamber separated by a partition wall; wherein the partition wall includes a stationary element and a rotating element separated by a seal and either of the stationary element and the rotating element of the partition wall is segmented by a levered joint, wherein the levered joint includes a lever having a trigger plate, a fixture portion and a fulcrum portion; and, the other of the stationary element and rotating element includes a hammer which is axially aligned and separated from the trigger plate in a first position, and forcibly contacts the hammer portion in a second position so as to create a moment on the lever via the trigger plate, the moment forcing the levered joint apart. 1. A gas turbine engine , comprising:a first chamber and a second chamber separated by a partition wall;wherein the partition wall includes a stationary element and a rotating element separated by a seal and either of the stationary element and the rotating element of the partition wall is segmented by a levered joint,wherein the levered joint includes a lever having a trigger plate, a fixture portion and a fulcrum portion; and,the other of the stationary element and rotating element includes a hammer which is axially aligned and separated from the trigger plate in a first position, the hammer forcibly contacting the trigger plate in a second position so as to create a moment on the lever about the fulcrum portion via the trigger plate, the moment forcing the levered joint apart.2. A gas turbine engine as claimed in claim 1 , wherein the seal includes the hammer.3. A gas turbine engine as claimed in claim 2 , wherein the seal is a labyrinth seal having a plurality of fins extending from a seal body and the seal body is the hammer.4. A gas turbine engine as claimed in claim 1 , wherein the lever has a first end at which the trigger plate is located and a second end at which the fulcrum portion is located and the ...

SEALING ARRANGEMENTS

A sealing arrangement () for providing sealing between a first structure (), e.g. a rotor shaft, and a second structure (), e.g. a portion of a casing, of an engine, and between first (HP) and second (LP) pressure regions located between the first () and second () structures, the first pressure region (HP) being at a relatively higher pressure than the second pressure region (LP), and the first structure () being moveable relative to the second structure () along an axis, 130101510151015. A sealing arrangement () for providing sealing between a first structure () and a second structure () of an engine , and between first (HP) and second (LP) pressure regions located between the first () and second () structures , the first pressure region (HP) being at a relatively higher pressure than the second pressure region (LP) , and the first structure () being moveable relative to the second structure () along an axis ,{'b': '30', 'wherein the sealing arrangement () comprises{'b': 20', '10', '15, 'a sealing member () carried on the first structure () and extending towards the second structure (), and having opposite first and second sides; and'}{'b': 40', '15', '40, 'claim-text': [{'b': 42', '60', '60, 'a first seal portion () having opposite exterior and interior sides and a first seal face () on the interior side thereof, at least a portion of the first seal face () being in communication with the first pressure region (HP), and'}, {'b': 44', '42', '70', '70, 'a second seal portion () spaced from the first seal portion () and having opposite exterior and interior sides and a second seal face () on the interior side thereof, at least a portion of the second seal face () being in communication with the second pressure region (LP),'}, {'b': 60', '70', '60', '20', '70', '20, 'the first and second seal faces (, ) being spaced apart from one another with the first seal face () located to the first side of the sealing member () and the second seal face () located to the second ...

ROTATING SEAL CONFIGURATION AND METHOD OF SEALING A ROTATING MEMBER TO A HOUSING

A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face. 1. A rotating seal configuration , comprising:a housing; anda rotatable member rotationally mounted relative to the housing having at least one portion defining an outer perimetrical face being configured to contact the housing during some operational conditions, the at least one portion having opposing axial surfaces with at least one of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.2. The rotating seal configuration of claim 1 , wherein the outer perimetrical face is oriented substantially parallel to a rotational axis of the rotatable member.3. The rotating seal configuration of claim 1 , wherein an angle between the outer perimetrical face and each of the opposing axial surfaces is acute.4. The rotating seal configuration of claim 1 , wherein the outer perimetrical face cuts into the housing in response to contact therewith while the rotatable member is rotating.5. The rotating seal configuration of claim 1 , wherein the rotating seal configuration is configured such that neither of the opposing axial surfaces make contact with the housing after the rotatable member has cut a groove into the housing.6. The rotating seal configuration of claim 1 , wherein the at least one portion is ...

SEALING STRUCTURE FOR TURBINES, AND TURBINE AND GAS TURBINE HAVING THE SAME

Disclosed herein may be a sealing structure for turbines, and a turbine and a gas turbine having the sealing structure. The sealing structure is mounted on a sealing housing of a vane sealing assembly of the turbine to prevent combustion gas passing through a blade of the turbine from being drawn into an internal space between a disk of the turbine and the sealing housing. The sealing structure may include a mounting plate mounted to the sealing housing, and baffles which are provided on the mounting plate at positions spaced apart from each other and protrude toward the disk. Therefore, thanks to the sealing structure, turbulent currents are generated in the flow of combustion gas that passes through the turbine blade. The generated turbulent currents block space between the sealing structure and the turbine disk, thus preventing the combustion gas from flowing into the internal space. 1. A sealing structure for a turbine , the sealing structure being mounted on one surface of a sealing housing of a vane sealing assembly of the turbine so as to prevent combustion gas passing through a blade of the turbine from being drawn into an internal space between a disk of the turbine and the sealing housing ,the sealing structure comprising:a mounting plate mounted to the sealing housing; anda plurality of baffles provided on the mounting plate at positions spaced apart from each other from an upper end of the mounting plate to a lower end thereof, the plurality of baffles protruding toward the disk of the turbine.2. The sealing structure according to claim 1 ,wherein the plurality of baffles provided on the mounting plate have lengths different from each other,wherein a length of a baffle that is provided on the upper end of the mounting plate is the shortest, andwherein lengths of the plurality of baffles are gradually increased from the upper end of the mounting plate to the lower end thereof.3. The sealing structure according to claim 2 , wherein the plurality of baffles ...

Segment for Sealing Device, and Turbine Rotor and Turbine Comprising Same

A segment 31 for a sealing device according to the present invention is used in a sealing device 28 provided between a turbine rotor 12 and a stationary body 14 that covers the turbine rotor 12 . The segment 31 for the sealing device is characterized by including a base 32 that engages with the turbine rotor 12 and a free-cutting layer 34 that covers a stationary body opposed surface 37 , which is a surface of the base 32 opposed to the stationary body 14.

FLOATING, NON-CONTACT SEAL WITH OFFSET BUILD CLEARANCE FOR LOAD IMBALANCE

Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where during a non-operational state of the engine a reference point of the shoe is substantially centered within a range of radial deflections of the reference point of the shoe over the operating range of the engine. 1. An engine comprising:a first structure;a second structure configured to rotate relative to the first structure; and a shoe;', 'a first beam coupled to the shoe; and', 'a second beam coupled to the shoe,, 'a floating, non-contact seal that interfaces the first structure and the second structure, wherein the seal includeswherein during a non-operational state of the engine a reference point of the shoe is substantially centered within a range of radial deflections of the reference point of the shoe over the operating range of the engine.2. The engine of claim 1 , wherein the first structure is an engine case.3. The engine of claim 1 , wherein the second structure includes at least one of a shaft or a rotor disk.4. The engine of claim 1 , wherein the first and second structures are part of a compressor section of the engine.5. The engine of claim 1 , wherein the first and second structures are part of a turbine section of the engine.6. The engine of claim 1 , wherein the seal interfaces a first region of the engine to a second region of the engine in terms of an airflow from the first region of the engine to the second region of the engine.7. The engine of claim 6 , wherein the shoe comprises a plurality of teeth claim 6 , and wherein the airflow substantially flows in an axial direction relative to a centerline of the engine claim 6 , radially between the teeth and the second structure.8. The engine ...

FLOATING, NON-CONTACT SEAL WITH ANGLED BEAMS

Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. 1. A floating , non-contact seal comprising:a shoe;a first beam coupled to the shoe; anda second beam coupled to the shoe,wherein the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees.2. The floating claim 1 , non-contact seal of claim 1 , wherein the second beam is oriented at a second angle with respect to the shoe claim 1 , the second angle having a second value that is greater than five degrees.3. The floating claim 2 , non-contract seal of claim 2 , wherein the second value is less than ten degrees.4. The floating claim 1 , non-contract seal of claim 1 , wherein the first value is less than ten degrees.5. The floating claim 1 , non-contact seal of claim 1 , wherein the first beam is coupled to the shoe at a first location of the shoe and the second beam is coupled to the shoe at a second location of the shoe that is different from the first location.6. The floating claim 1 , non-contact seal of claim 1 , wherein the first beam claim 1 , the second beam claim 1 , and the shoe form a four-bar linkage.7. The floating claim 6 , non-contact seal of claim 6 , wherein the four-bar ...

FLOATING, NON-CONTACT SEAL WITH AT LEAST THREE BEAMS

Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. 1. A floating , non-contact seal comprising:a shoe; andat least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.2. The floating claim 1 , non-contact seal of claim 1 , wherein the at least three beams consist of three beams.3. The floating claim 1 , non-contract seal of claim 1 , wherein the seal comprises more than three beams.4. An engine comprising:a first structure;a second structure configured to rotate relative to the first structure; and a shoe; and', 'at least three beams,, 'a floating, non-contact seal that interfaces the first structure and the second structure, wherein the seal includeswherein each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.5. The engine of claim 4 , wherein a first of the beams is located radially outward of a second of the beams and a third of the beams with respect to an axial centerline of the engine claim 4 , and wherein the second of the beams is located radially outward of the third of the beams with respect to the axial centerline ...

FLOATING NON-CONTACT SEAL VERTICAL LIP

A seal assembly includes an annular base, a spring, a shoe, a first channel, a seal cover, and a seal. The spring includes a beam and is connected to the annular base. The shoe is disposed radially inward of the annular base and connected to the spring. The shoe includes an upstream portion, a downstream portion, and a lip connected to and extending radially outward from the upstream portion of the shoe. The spring extends from the annular base to the shoe. The first channel is positioned between the shoe and the beam of the spring. The seal is disposed between the seal cover and the shoe such that a downstream face of the seal is in contact with an upstream face of the shoe. 1. A seal assembly comprising:an annular base;a spring with a beam, wherein the spring is connected to the annular base; an upstream portion;', 'a downstream portion; and', 'a lip connected to and extending radially outward from the upstream portion of the shoe;, 'a shoe disposed radially inward of the annular base and connected to the spring, the spring extending from the annular base to the shoe, wherein the shoe comprisesa first channel between the shoe and the beam of the spring;a seal cover disposed axially upstream of and adjoining the annular base; anda seal disposed between the seal cover and the shoe, wherein a downstream face of the seal is in contact with an upstream face of the shoe.2. The seal assembly of and further wherein the downstream face of the seal is in contact with the lip.3. The seal assembly of claim 1 , wherein the seal overlaps a portion of the shoe such that the seal extends radially inward of a radially outward end of the lip of the shoe.4. The seal assembly of claim 1 , wherein the lip is disposed axially upstream from the spring.5. The seal assembly of and further wherein the lip extends at least half-way across a width of the first channel between the shoe and the beam of the spring.6. The seal assembly of claim 1 , wherein the width of the first channel is ...

DEVICE FOR SEALING BETWEEN THE COAXIAL SHAFTS OF A TURBOMACHINE

A device for sealing the coaxial shafts of a turbomachine includes an annular seal able to perform sealing by contact with the outer shaft, and a lubricating device to lubricate the region of contact between the annular seal and the outer shaft. 1. A device for sealing between coaxial shafts of a turbomachine , comprising:an annular seal configured to perform sealing by contact with an outer shaft of the coaxial shafts, anda lubricating device configured to lubricate a region of contact between said annular seal and said outer shaft.2. The device for sealing between the coaxial shafts of a turbomachine according to claim 1 , wherein the contact between said annular seal and said outer shaft is ensured by an elastic device and/or a hydraulic device.3. The device for sealing between the coaxial shafts of a turbomachine according to claim 2 , wherein said hydraulic device is formed by a cylinder cooperating with a plurality of pistons so as to exert a strain onto said annular seal.4. The device for sealing between the coaxial shafts of a turbomachine according to claim 3 , wherein the pistons are integral with said annular seal.5. The device for sealing between the coaxial shafts of a turbomachine according to claim 3 , wherein a hydraulic strain exerted on said plurality of pistons is made by centrifugation of a hydraulic fluid inside said cylinder.6. The device for sealing between the coaxial shafts of a turbomachine according to claim 3 , wherein part of said plurality of pistons or all of said plurality of pistons has ports able to convey hydraulic fluid to a region of contact between the annular seal and the outer shaft.7. The device for sealing between the coaxial shafts of a turbomachine according to claim 6 , wherein said annular seal has an annular groove arranged facing the ports of the pistons.8. The device for sealing between the coaxial shafts of a turbomachine according to claim 1 , comprising an elastic segment ensuring sealing between said annular seal ...

TURBOMACHINE BUCKET HAVING ANGEL WING FOR DIFFERENTLY SIZED DISCOURAGERS AND RELATED METHODS

A turbomachine bucket may include an airfoil, a shank coupled to the airfoil, and an angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent. Various methods for modifying an angel wing to accommodate different sized discouragers are also disclosed. 1. A turbomachine bucket comprising:an airfoil;a shank coupled to the airfoil; andan angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent.2. The turbomachine bucket of claim 1 , wherein the axially extending tip includes:a foundational tip having an initial axial extent, andan attached material section extending the initial axial extent of the foundational tip.3. The turbomachine bucket of claim 2 , wherein the axially extending tip has substantially identical radial height as the foundational tip without the attached material section.4. The turbomachine bucket of claim 2 , wherein the attached material section is removable.5. The turbomachine bucket of claim 2 , wherein the attached material section includes a block of material in the form of one of: a metal block claim 2 , a metal coating claim 2 , or a ceramic coating.6. The turbomachine bucket of claim 1 , wherein the angel wing further includes a base portion configured to couple to the shank.7. The turbomachine bucket of claim 1 , wherein the axially extending tip is configured to seal with the discourager extending from one of a nozzle and a diaphragm of a turbomachine frame.8. The turbomachine bucket of claim 1 , wherein each of the plurality of discouragers are in a different turbomachine.9. A method comprising:modifying an axial extent of an axially extending tip of an angel wing of a turbomachine bucket to accommodate sealing with a plurality of discouragers having different axial extents.10. The method of claim 9 , ...

LABYRINTH SEAL COMPRISING A LIP PROVIDED WITH A DEFLECTOR

A labyrinth seal lip () comprises, standing on one of its lateral faces (), a deflector () which channels the flow of gas tangent to the lip () towards the facing seal () so as to disturb the leakage flow () through the gap and decrease the flow rate. 17-. (canceled)8561789513149. Labyrinth seal of a turbomachine , the seal comprising a lip () projecting above a base () of a rotor () of the turbomachine , the lip being circular and extending along a tangential direction (T) , comprising two lateral faces ( , ) each connected to the base and , at an end opposite the base , at a face at the tip () of the lip () at which at least one of the lateral faces supports at least one deflector () comprising a deflecting face () intersecting with said lateral face and with an inclination relative to the tangential direction , wherein the inclination of the deflecting face relative to the tangential direction increases with decreasing distance from the face of the tip () , the deflecting face thus being concave.9. Labyrinth seal according to claim 8 , wherein the deflector is repeated on the lip at a regular angular pitch along the tangential direction (T).10. Labyrinth seal according to claim 9 , wherein the angular pitch is between 2° and 10°.1114. Labyrinth seal according to claim 8 , wherein the lip is free to move along the tangential direction and the deflecting face () is directed along a movement direction (T) of the lip.121469. Labyrinth seal according to claim 8 , wherein the deflecting face () extends between the base () and the tip face ().13. Labyrinth seal according to claim 8 , wherein the lateral face supporting the deflector is directed towards the upstream side of a flow passing through the labyrinth seal along an axial direction (X) perpendicular to the tangential direction.1412. Labyrinth seal according to claim 8 , wherein the lip is inclined from the base claim 8 , towards the upstream side of a flow () passing through the labyrinth seal along an axial ...

HYDROSTATIC SEAL WITH SEAL STOPS

A hydrostatic seal assembly includes a seal carrier, a seal shoe located at the seal carrier and configured for travel relative to the seal carrier to maintain a selected gap between the seal shoe and a rotating component, and a travel stop. The travel stop includes a stop rib located at one of the seal carrier or the seal shoe, and a stop groove located at the other of the seal carrier or the seal shoe. The stop rib is positioned at least partially in the stop groove to limit travel of the seal shoe relative to the seal carrier. 1. A hydrostatic seal assembly , comprising:a seal carrier;a seal shoe disposed at the seal carrier and configured for travel relative to the seal carrier to maintain a selected gap between the seal shoe and a rotating component; and a stop rib disposed at one of the seal carrier or the seal shoe; and', 'a stop groove disposed at the other of the seal carrier or the seal shoe, the stop rib disposed at least partially in the stop groove to limit travel of the seal shoe relative to the seal carrier., 'a travel stop including2. The hydrostatic seal assembly of claim 1 , wherein the seal carrier includes:a radial outer wall; andan axial aft wall, one of the stop rib or the stop groove disposed at the axial aft wall of the seal carrier.3. The hydrostatic seal assembly of claim 2 , wherein the stop rib is disposed at the axial aft wall claim 2 , extending axially toward the seal shoe.4. The hydrostatic seal assembly of claim 2 , wherein the seal shoe is configured for radial travel relative to the seal carrier claim 2 , the travel stop configured to limit said radial travel.5. The hydrostatic seal assembly of claim 1 , wherein a groove radial width of the stop groove is greater than a rib radial width of the stop rib claim 1 , thereby allowing full travel of the seal shoe relative to the seal carrier.6. The hydrostatic seal assembly of claim 1 , wherein the stop rib has one of a rectangular claim 1 , triangular or semi-circular cross-sectional ...

HYDROSTATIC SEAL ALIGNED WITH ROTOR ROTATION

A hydrostatic seal and rotor assembly includes a rotor having a rotor rotational direction about a rotor central axis, and a hydrostatic seal assembly including a seal support, a seal shoe configured for sealing between the seal shoe and the rotor, and one or more seal beams operably connecting the seal shoe to the seal support. The one or more seal beams are configured as spring elements integral with the seal shoe to allow radial movement of the seal shoe relative to the seal support. The seal shoe is circumferentially cantilevered from a fixed end to a free end opposite the fixed end. The fixed end is located circumferentially upstream of the free end relative to the rotor rotational direction. 1. A hydrostatic seal and rotor assembly , comprising:a rotor having a rotor rotational direction about a rotor central axis; and a seal support;', 'a seal shoe configured for sealing between the seal shoe and the rotor; and', 'one or more seal beams operably connecting the seal shoe to the seal support, the one or more seal beams configured as spring elements integral with the seal shoe to allow radial movement of the seal shoe relative to the seal support;', 'wherein the seal shoe is circumferentially cantilevered from a fixed end to a free end opposite the fixed end, the fixed end located circumferentially upstream of the free end relative to the rotor rotational direction., 'a hydrostatic seal assembly including2. The hydrostatic seal and rotor assembly of claim 1 , wherein the seal beam extends between a radially fixed first beam end and a radially movable second beam end.3. The hydrostatic seal and rotor assembly of claim 2 , wherein the fixed end of the seal shoe is located at the second beam end.4. The hydrostatic seal and rotor assembly of claim 1 , including one or more stops formed in the seal shoe configured to limit radial travel of the seal shoe.5. The hydrostatic seal and rotor assembly of claim 1 , further comprising a seal carrier configured to axially and ...

EXPANSION SEAL

A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal. 1. A stator and blade outer airseal assembly of a gas turbine engine , comprising:a blade outer airseal having a radially extending first surface relative to a gas turbine engine central axis;a stator having a radially extending second surface relative to the gas turbine engine central axis and axially offset from the first surface defining an axial gap through which a fluid can flow; andat least one recess formed in one of the first surface and the second surface oriented such that the fluid flow through the axial gap crosses the at least one recess, the recess enlarging the axial gap, thereby urging expansion and then contraction of the fluid flow through the axial gap, thereby inhibiting fluid flow through the axial gap.2. The stator and blade outer airseal assembly of claim 1 , wherein the at least one recess forms sharp corners where the at least one recess intersects with the one of the first surface or the second surface in which the recess is formed.3. The stator and blade outer airseal assembly of claim 1 , wherein the at least one recess is at least two recesses claim 1 , a first of the two recesses being formed in the first surface and a second of the two recesses being formed in the second surface.4. The stator and blade outer airseal assembly of claim 3 , wherein the first of the at least two recesses is positioned symmetrically across the gap from the second of the two recesses.5. The stator and blade outer airseal assembly of claim 3 , wherein the ...

Hydrostatic seal

A hydrostatic seal assembly includes a primary seal configured to maintain a selected gap between the primary seal and a rotating component. The primary seal includes a seal support, a seal shoe, and one or more seal beams operably connecting the seal support to the seal shoe. The one or more seal beams are configured as spring elements integral with the seal shoe to allow radial movement of the seal shoe relative to the seal support. A seal carrier including a radial outer wall is configured to radially position the primary seal. The seal carrier is configured for a non-contact relationship with the seal shoe during operation of the hydrostatic seal assembly.