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 ...

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ

Газотурбинный двигатель содержит осевой турбокомпрессор с радиальными лабиринтными уплотнениями между полостями турбины или компрессора, выполненными на роторе и статоре турбины или компрессора в виде лабиринтных колец, на каждом из которых содержится, по меньшей мере, по одному прямому и обратному радиальному зубу. Вершины зубьев противоположно направлены относительно кольцевых полок на статоре или роторе. Уплотнениями прямого и обратного радиальных зубьев образована тупиковая полость, отделяющая трактовую полость турбокомпрессора от думисной полости турбины или компрессора. По меньшей мере, одно лабиринтное кольцо радиального уплотнения снабжено дополнительной наружной или внутренней полками. На одной из этих полок выполнен, по меньшей мере, один дополнительный радиальный зуб, противоположно направленный относительно прямого или, соответственно, обратного радиального зуба на другой полке лабиринтного кольца. Радиальное лабиринтное уплотнение снабжено дополнительным уплотнением на его ...

УПЛОТНИТЕЛЬНОЕ КОЛЬЦО С ИЗМЕНЯЕМЫМ ЗАЗОРОМ И ЕГО КОМБИНАЦИЯ С НЕПОДВИЖНОЙ ДЕТАЛЬЮ (ВАРИАНТЫ)

Изобретение относится к уплотнительной технике. Уплотнительное кольцо с изменяемым зазором содержит множество вытянутых по окружности сегментов, расположенных, как правило, в прорези типа "ласточкин хвост" в неподвижной детали машины, имеющей ротор, вращающийся вокруг оси. Уплотнительное кольцо включает в себя дуговую уплотняющую поверхность напротив ротора и вытянутые по направлению оси выступы внутри прорези типа "ласточкин хвост". Штыри выступают по направлению оси от противоположных сторон неподвижной детали, располагаясь между выступами и уплотняющими поверхностями сегментов. Центрирующее кольцо установлено на штырях для каждого сегмента и имеет коэффициент теплового расширения больший, чем коэффициент теплового расширения сегмента. Центрирующие кольца зацепляют выступы сегментов в первом месте, удерживая уплотняющую поверхность сегментов в первом положении с зазором относительно ротора, и зацепляют выступы во втором месте в ответ на относительное тепловое расширение сегмента и центрирующих ...

ПРИВОДНОЙ УЗЕЛ НА ТЕКУЧЕЙ СРЕДЕ И СПОСОБ ПЕРЕМЕЩЕНИЯ РЕГУЛИРУЕМОГО УПЛОТНЕНИЯ В РАДИАЛЬНОМ НАПРАВЛЕНИИ (ВАРИАНТЫ)

Приводной узел на текучей среде содержит цилиндр с впускным отверстием, поршень, расположенный в цилиндре, кольцевую канавку на поршне или цилиндре, поршневые кольца и пружину. Поршневые кольца расположены в кольцевой канавке с зазором. Пружина вставлена в кольцевую канавку на поверхности высокого давления поршневых колец с образованием зазоров между первой поверхностью пружины и поверхностью высокого давления поршневых колец и между второй поверхностью пружины и поверхностью высокого давления кольцевой канавки. Пружина нагружает поршневые кольца для уплотнения между поверхностью низкого давления поршневых колец и поверхностью низкого давления кольцевой канавки. При перемещении регулируемого уплотнения в осевом направлении размыкают основной осевой контакт между регулируемым уплотнением и поверхностью первичного уплотнения. В одном из вариантов образуют контакт между регулируемым уплотнением и поверхностью вторичного уплотнения. Уменьшают радиальное усилие давления, действующего на регулируемое ...

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.

УСТРОЙСТВО ДЛЯ ЗАКРЕПЛЕНИЯ РАБОЧЕГО КОЛЕСА НА ВАЛУ

Устройство для закрепления рабочего колеса турбонагнетателя на валу содержит рабочее колесо со ступицей, вал и навинчиваемую на шейку вала втулку. В отростке ступицы рабочего колеса со стороны вала выполнено центральное глухое отверстие, в котором посредством резьбы закреплена шейка вала. Втулка с силовым замыканием установлена в глухое отверстие. Отросток ступицы, по меньшей мере, в зоне своего конца со стороны вала выполнен приблизительно в виде цилиндрического полого тела. Радиально снаружи на отростке ступицы предусмотрена соединенная с ним с силовым замыканием напрессованная гильза, при этом указанный отросток ступицы зажат с силовым замыканием между втулкой и напрессованной гильзой. Втулка имеет расположенные аксиально друг за другом отрезки с разными внутренними диаметрами, причем внутренние диаметры уменьшаются в направлении рабочего колеса, а одна внутренняя резьба для навинчивания на шейку вала, выполненная ответной, расположена на отрезке большего диаметра. Изобретение позволяет ...

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 ...

УПЛОТНЕНИЕ РОТОРА ТУРБОМАШИНЫ

Изобретение относится к области турбостроения. Уплотнение ротора турбомашины выполнено из двух одинаковых половин, составленных без зазоров по диаметральной плоскости разъема, каждая из которых содержит корпусную деталь, представляющую собой внутреннее полукольцо с поперечным сечением П-образной формы, выполненное концентрично оси ротора и упруго подвешенное к статору с помощью расположенных внутри него внешнего полукольца и опирающегося на него многослойного пакета, набранного из стальных каленых шлифованных лент одинаковой толщины. Пакеты собраны из нескольких гофрированных лент, соединены друг с другом последовательно вершина к вершине гофра, а между ними установлены гладкие ленты. Все элементы каждой половины уплотнения соединены друг с другом пружинными скобами. Один упругий лепесток скобы с натягом опирается на наружное полукольцо, а второй упругий лепесток скобы своим концом жестко закреплен на внутреннем полукольце. Ответный паз внутреннего полукольца прикрыт пластинкой, жестко ...

СПОСОБ УПЛОТНЕНИЯ ТУРБИНЫ (ВАРИАНТЫ)

Способ уплотнения турбины от утечки рабочего флюида. Турбина имеет неподвижный элемент и вращающийся элемент, уплотнительное кольцо введено с возможностью скольжения по меньшей мере в один паз неподвижного элемента, паз имеет расположенную выше по течению боковую поверхность и расположенную ниже по течению боковую поверхность. Способ включает в себя следующие операции: используют уплотнительное кольцо, содержащее головку и корпус, имеющий элементы дросселирования, выступающие радиально из него. Используют, по меньшей мере, один комплект устройств подвески, который подвешивает уплотнительное кольцо в проектном радиальном зазоре. Устанавливают датчик между элементами дросселирования. Соединяют датчик с комплектом устройств подвески, таким образом, что комплект устройств подвески поддерживал уплотнительное кольцо в проектном радиальном зазоре без повреждения элементов дросселирования, всякий раз когда датчик контактирует с вращающимся элементом. Другой способ уплотнения турбины от утечки рабочего ...

УПЛОТНИТЕЛЬНЫЙ УЗЕЛ И ПАРОВАЯ ТУРБИНА, СОДЕРЖАЩАЯ УПЛОТНИТЕЛЬНЫЙ УЗЕЛ

Паровая турбина (10) содержит корпус (26), ротор (12) и по меньшей мере один гибкий пластинчатый уплотнительный узел (24), расположенный между корпусом и ротором. Указанный уплотнительный узел содержит опорный элемент (28), неподвижный относительно корпуса, пластинчатые элементы (48), которые установлены на указанном опорном элементе с возможностью перемещения и проходят по направлению к ротору и каждый из которых наклонен относительно направления вращения ротора, а также исполнительный механизм (32), предназначенный для избирательного приложения давления с обеспечением втягивания указанных пластинчатых элементов в направлении от ротора. 2 н. и 7 з.п. ф-лы, 11 ил.

УПЛОТНИТЕЛЬНАЯ ВТУЛКА ДЛЯ ПАРОВОЙ ТУРБИНЫ И ПАРОВАЯ ТУРБИНА

Настоящее изобретение относится к уплотнительной втулке (1) для паровой турбины (40). Паровая турбина (40) содержит по меньшей мере ротор (41) турбины и корпус (43) турбины, при этом уплотнительная втулка (1) размещена между валом (42) ротора (41) и корпусом (43) и содержит по меньшей мере два сквозных канала (2, 3), которые проходят от части (4) уплотнительной втулки (1), обращенной к ротору, к части (5) уплотнительной втулки (1), обращенной к корпусу турбины, и выполнены так, что их расположение может соответствовать подобным сквозным отверстиям (44, 45) в корпусе (43) для обеспечения отвода (20) пара турбины (40) через каналы (2, 3) уплотнительной втулки (1) в сквозные отверстия (44, 45) корпуса (43). Кроме того, изобретение относится к паровой турбине (40), содержащей по меньшей мере ротор (41) с валом, корпус (43) и уплотнительную втулку (1) указанного типа. 2 н. и 11 з.п. ф-лы, 4 ил.

ДВУХСТУПЕНЧАТАЯ ТУРБИНА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

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Газотурбинный двигатель содержит компрессор высокого давления с установленным на выходе закомпрессорным лабиринтным уплотнением, камеру сгорания, двухступенчатую турбину высокого давления, а также расположенную ниже по потоку турбину низкого давления. Фланец закомпрессорного лабиринтного уплотнения выполнен с внутренней кольцевой замкнутой полостью, соединенной на выходе с проточной частью турбины низкого давления через внутренние полости первой сопловой и первой рабочей лопаток турбины низкого давления. Замкнутая полость на входе соединена через лабиринтные уплотнения с воздушной полостью на выходе из компрессора и с каналом подвода воздуха из промежуточной ступени компрессора на охлаждение второй рабочей лопатки турбины высокого давления. Изобретение повышает надежность и экономичность двигателя путем снижения температуры газа перед турбиной и охлаждающего воздуха на входе во вторую рабочую лопатку турбины высокого давления за счет исключения попадания утечек закомпрессорного горячего ...

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УСТРОЙСТВО ДЛЯ КРЕПЛЕНИЯ ЛАБИРИНТА ТУРБОМАШИНЫ

СХЕМА КОНЦЕВЫХ УПЛОТНЕНИЙ ПАРОВОЙ ТУРБИНЫ

Схема предназначена для концевых уплотнений паровой турбины. Схема концевых уплотнений паровой турбины включает цилиндры высокого и среднего давления с концевыми уплотнениями, камеры которых соединены трубопроводами с линиями подвода и отсоса пара. На линиях подвода и отсоса пара из камер концевых уплотнений установлены регулирующие бесприводные клапаны, внутренняя полость тарелки которых соединена с отбором турбины или коллектором соответствующего управляющего давления. Применение предлагаемой схемы позволяет поддерживать в камерах отсоса оптимальный уровень давления лабиринтового пара на всех режимах работы установки (работа под нагрузкой, переменные режимы при снижении и наборе нагрузки, пуски и остановы), что обеспечивает минимальные непроизводительные расходы пара из уплотнений, а следовательно, повышает экономичность, кроме того, автоматически исключает такие явления, как подсос воздуха в турбину, либо, наоборот, пропаривание и, как следствие, обводнение масла на любых режимах. Предлагаемую ...

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Изобретение относится к турбинам турбореактивных двигателей повышенной степени двухконтурности. Турбина турбореактивного двигателя включает статор, роторы высокого и низкого давлений с размещенным между ними межвальным уплотнением, содержащим установленный на валу ротора высокого давления фланец и ответный ему лабиринт на валу ротора низкого давления. Фланец выполнен S-образным в поперечном сечении и расположен с внутренней стороны роторного лабиринта, установленного на хвостовике вала ротора высокого давления и фиксирующего в осевом направлении посредством резьбового хвостовика внутреннее кольцо роликоподшипника ротора высокого давления. Фланец зафиксирован в радиальном направлении цилиндрической внутренней поверхностью роторного лабиринта, а в осевом направлении - торцевой поверхностью хвостовика вала ротора высокого давления, с одной стороны, и расположенным на роторном лабиринте стопорным разжимным кольцом, с другой стороны. Передний и задний по потоку газа хвостовики фланца посредством ...

УПЛОТНИТЕЛЬНОЕ УСТРОЙСТВО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Изобретение относится к авиационному двигателестроению, а именно к уплотнительным устройствам за компрессором газотурбинного двигателя. Уплотняющее рабочее тело, перетекающее через уплотнительное устройство через щелевой канал 11 и полость смешения 15 в полость В низкого давления из полости Б высокого давления, создает разрежение на входе в полость смешения 15, куда увлекается через канал 14 низкотемпературный охлаждающий воздух из щелеобразной полости А в полость низкого давления В. Решена техническая задача, заключающаяся в повышении экономичности газотурбинного двигателя за счет обеспечения минимальной величины радиального зазора на всех режимах работы двигателя путем организации газоструйной эжекции на выходе из уплотнительного устройства. 2 ил.

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Изобретение относится к области турбостроения, в частности к устройству бесконтактных уплотнений лабиринтного типа для ступеней паровой турбины, и может быть использовано при конструировании и модернизации уплотнений цилиндров среднего и низкого давлений паровых турбин, в том числе работающих и в составе парогазовых установок. Сущность изобретения заключается в том, что уплотняющие пластины выполнены с "Г-" или "U-образным" профилем в сечении, при этом рабочий участок уплотняющей пластины выполнен под углом, находящимся первоначально в интервале 30-45°, с возможностью его изменения до 90°, при этом уплотняющие пластины установлены с исходным зазором, в диапазоне 1,1-2,2 мм и выполнены из сплава элементов группы металлидов, обладающих эффектом запоминания формы при изменении температуры. Данное уплотнение позволяет исключить возможность задевания ротора и соответственно минимизировать степень износа уплотнительных элементов, что в комплексе позволит существенно снизить объем протечек рабочего ...

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... 1. Устройство для закрепления рабочего колеса (22) на валу (14), в частности рабочего колеса турбонагнетателя на валу турбонагнетателя, включающее навинчиваемую на шейку (20) вала втулку (34) и отросток (30) ступицы рабочего колеса со стороны вала с центральной выемкой, в которую с силовым замыканием установлена втулка, причем отросток (30) ступицы, по меньшей мере, в зоне своего конца со стороны вала выполнено приблизительно в виде цилиндрического полого тела, отличающееся тем, что радиально снаружи на отростке (30) ступицы предусмотрена соединенная с ним с силовым замыканием напрессованная гильза (36), при этом указанный отросток зажат с силовым замыканием между втулкой и напрессованной гильзой. 2. Устройство по п.1, отличающееся тем, что предусмотрен вспомогательный подшипник (44), который расположен аксиально между поддерживающим вал (14) подшипником (16) и отростком (30) ступицы и в смонтированном состоянии преимущественно прижат к участку втулки (34) или к участку напрессованной гильзы ...

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 ...

УСТРОЙСТВО ЛАБИРИНТНОГО УПЛОТНЕНИЯ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

... 1. Устройство лабиринтного уплотнения для газотурбинного двигателя, включающего от входного по потоку конца к выходному по потоку концу компрессор высокого давления с ротором (2), лопатки (6) диффузора и зафиксированный элемент (10) стенки, образующий, по меньшей мере, одну часть внутренней оболочки камеры сгорания (8), причем упомянутое уплотнение (20) содержит часть (22) статора, установленную на элементе стенки посредством крепежного средства (24) с фланцами (25 и 26) и несущую круговую снашивающуюся часть (23), причем упомянутая снашивающаяся часть работает вместе с роторным элементом (28), имеет, по меньшей мере, один периферийный зубец (28А) и выполнена за одно целое с ротором (2) компрессора для образования лабиринтного уплотнения, отличающееся тем, что, по меньшей мере, один из фланцев (25, 26) крепежного средства (24) является достаточно тяжелым для согласования степени расширения части (22) статора со степенью расширения роторного элемента (28) при разгонах двигателя. 2. Устройство ...

ПАРОВАЯ ТУРБИНА

... 1. Паровая турбина (10), содержащая внешний корпус (12), внутренний кожух (14) внутри внешнего корпуса, включающий верхнюю и нижнюю диафрагмы (16, 18), присоединенные друг к другу вдоль горизонтальной соединительной средней линии, причем верхняя и нижняя диафрагмы имеют совмещающие фланцы (19, 21) на соединительной средней линии и углубления (40) во фланцах для совмещения друг с другом, и эластичное уплотнение (43), частично расположенное в каждом из совмещающих углублений, включающее уплотнительную основу (44), образованную из многочисленных слоев (46, 48, 50, 52) из различных материалов для эластичного уплотнения совмещающих фланцев верхней и нижней диафрагм друг с другом вдоль горизонтальной соединительной средней линии. 2. Паровая турбина по п.1, в которой материалы уплотнительной основы содержат плетеный металлический сердечник (46), волокно (48), металлическую фольгу (50) и защитный слой (52). 3. Паровая турбина по п.1, в которой материалы уплотнительной основы содержат внутренний ...

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

СПОСОБ ПРОИЗВОДСТВА НАДВАЛЬНОГО УПЛОТНЕНИЯ ТУРБОМАШИН

РОТОРНАЯ МАШИНА (ВАРИАНТЫ), ПРОКЛАДКА И МОДУЛЬ ДЛЯ РОТОРНОЙ МАШИНЫ

... 1. Роторная машина (10), содержащая в основном цилиндрический корпус (18), лопатку (22) вентилятора, установленную с возможностью вращения внутри упомянутого корпуса (18) вокруг продольной оси упомянутой машины, кольцевую прокладку (24), установленную в упомянутом корпусе (18) между вершиной упомянутой лопатки (22) вентилятора и упомянутым корпусом (18) с возможностью герметизации зазора между упомянутой вершиной лопатки (22) вентилятора и упомянутым корпусом (18), отличающаяся тем, что упомянутая прокладка (24) содержит щеточное уплотнение (34), расположенное по внутренней окружности упомянутого корпуса и имеющее щетинки (38), расположенные проходящими в радиальном направлении вовнутрь от упомянутого щеточного уплотнения (34), и фиксирующую мембрану (36), установленную по окружности упомянутого щеточного уплотнения (34) с препятствованием выступанию упомянутых щетинок (38) в основном в радиальном направлении от упомянутого щеточного уплотнения (34) и с возможностью освобождения упомянутых ...

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 ...

ЩЕТОЧНОЕ УПЛОТНЕНИЕ

... 1. Щеточное уплотнение, содержащее установленный в статоре кольцевой пакет свободных с одного и зафиксированных между малой и большой боковыми пластинами с другого конца волокон и цилиндрический ротор, отличающееся тем, что цилиндрическая поверхность ротора, соприкасающаяся с волокнами, выполнена в виде тонкостенного кольца, закрепленного на поверхности диска ротора, на которой выполнены осевые микроканавки. 2. Щеточное уплотнение по п.1, отличающееся тем, что в цилиндрической поверхности диска ротора, соприкасающейся с волокнами, выполнены осевые микроотверстия.

ДВОЙНОЙ ЛАБИРИНТ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Двойной лабиринт газотурбинного двигателя с осевыми выступами, в которых равномерно расположены каналы подвода охлаждающего воздуха, отличающийся тем, что, осевые выступы выполнены с лабиринтными гребешками, причем L/b = 1-3, m/b = 0,6 - 1,1, n/b = 0,6 - 3, где L - длина входного отверстия канала, b - ширина входного отверстия канала, m - размер перемычки между соседними входными отверстиями, n - минимальная длина канала.

НАДВАЛЬНОЕ УПЛОТНЕНИЕ ТУРБОМАШИНЫ

КОЛЬЦЕВОЙ УПЛОТНИТЕЛЬНЫЙ УЗЕЛ И ТУРБОМАШИНА

... 1. Кольцевой уплотнительный узел (100) для использования в турбомашине между вращающимся элементом (102) и неподвижным элементом (104), содержащий:дугообразный корпус (106), имеющий кольцевую канавку (108),дугообразный кольцевой уплотнительный сегмент (110), имеющий крепежную часть (112), расположенную по меньшей мере частично в кольцевой канавке (108), и уплотнительную часть (114), расположенную вблизи вращающегося элемента (102), иупругий элемент (118), выполненный с обеспечением возможности перемещения кольцевого уплотнительного сегмента (110) в осевом направлении относительно вращающегося элемента (102) между первым и вторым положениями под действием давления.2. Кольцевой уплотнительный узел по п.1, в котором упругий элемент (118) выбран из группы, содержащей пружину и сильфон.3. Кольцевой уплотнительный узел по п.1, в котором уплотнительная часть (114) содержит зубцы (116а, 116b), которые проходят в радиальном направлении от дугообразного кольцевого уплотнительного сегмента (110) к ...

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, НАПРИМЕР АВИАЦИОННЫЙ ТУРБОРЕАКТИВНЫЙ ДВИГАТЕЛЬ

... 1. Газотурбинный двигатель, содержащий лопаточное колесо (14) с лопатками, выполненными полыми и охлаждаемыми изнутри при помощи принудительной циркуляции охлаждающего воздуха, при этом каждую лопатку (22) устанавливают на периферии диска ротора, причем в данном типе двигателя с диском ротора соединяют диск-лабиринт (52), с образованием контура подачи охлаждающего воздуха, сообщающегося с полостями (48) циркуляции воздуха, выполненными в упомянутых лопатках, и открывающего у основания ножек (44) лопаток, соединенных с упомянутым диском ротора, диск-лабиринт, направляющий воздух к этим ножкам лопаток, отличающийся тем, что между наружным краем диска-лабиринта и диском ротора вставляют кольцевой стопорный фланец (70), содержащий стопорный заплечик (72), образующий наружный кольцевой захват, в который заходит наружный край упомянутого диска-лабиринта, и опорный заплечик (74), образующий внутренний кольцевой захват, заходящий в осевую окружную выемку упомянутого диска ротора, причем упомянутый ...

КОНЦЕВОЕ УПЛОТНЕНИЕ ЦИЛИНДРА НИЗКОГО ДАВЛЕНИЯ ПАРОВОЙ ТУРБИНЫ

... 1. Концевое уплотнение цилиндра низкого давления паровой турбины, приспособленное для закрепления между горловиной выхлопного патрубка цилиндра и корпусом выносной подшипниковой опоры ротора, и содержащее выполненную с горизонтальным разъемом внешнюю коробку с диафрагмами, разделяющими полость коробки на камеры подачи уплотняющего пара и отсоса паро-воздушной смеси, и обойменные элементы, связанные с опорными кольцами диафрагм и несущие секции уплотнительных колец, отличающееся тем, что обойменные элементы совмещены в одной детали с горизонтальным разъемом, по окружности которой выполнены два ряда щелей, разграничивающих обойменные элементы, обеспечивая сообщение уплотнительного зазора с камерами внешней коробки, а обойменные элементы связаны с опорными кольцами диафрагм через упругие в радиальном направлении элементы, при этом на одном из концов уплотнения внешняя коробка выполнена с возможностью прикрепления к горловине выхлопного патрубка цилиндра, а на другом конце уплотнения деталь ...

КОНЦЕВОЕ УПЛОТНЕНИЕ ЦИЛИНДРА ПАРОВОЙ ТУРБИНЫ

... 1. Концевое уплотнение цилиндра паровой турбины содержит установленные во внешней коробке обоймы с опорными гребнями, несущие уплотнительные кольца и разделяющими уплотнение на несколько промежуточных камер с, по меньшей мере, двумя камерами отвода перетечек пара со стороны проточной части цилиндра, первая из которых является высокотемпературной, а вторая - охлаждаемой, отличающееся тем, что обойма между указанными камерами со стороны охлаждаемой камеры перекрыта экраном, образующим замкнутую полость с этой обоймой. 2. Концевое уплотнение по п. 1 с охлаждаемой камерой, имеющей на входе больший диаметр по уплотняемому зазору, чем под обоймой с противоположной стороны, отличающееся тем, что опорный гребень указанной обоймы в камере охлаждения выполнен с экраном, образующим с этим гребнем карман, закрытый со стороны внешней обоймы. 3. Концевое уплотнение по п. 1 или 2, отличающееся тем, что экран выполнен из взаимно подвижных секторных элементов. 4. Концевое уплотнение по пп. 2 и 3, отличающееся ...

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 ...

НАПРАВЛЯЮЩИЙ АППАРАТ КОМПРЕССОРА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ С УПЛОТНЕНИЕМ

Полезная модель относится к области авиадвигателестроения и газотурбинным двигателям (ГТД), в частности к компрессорам газотурбинных двигателей. Направляющий аппарат компрессора газотурбинного двигателя с уплотнением состоит из секторов с радиальными лопатками, наружным и внутренним основаниями. Дополнительно лента плоского профиля с уплотнением устанавливается в кольцевой паз внутреннего основания сектора с возможностью дополнительной фиксации от проворота установкой П-образного фиксатора в карман на краю сектора в направлении вращения ротора. Кроме того, применено уплотнение в виде сотового уплотнения или истираемого покрытия. Применена формованная лента плоского профиля из жаропрочного материала на основе никеля. Кроме того, П-образный фиксатор изготовлен методом селективного лазерного сплавления. П-образный фиксатор установлен, например, в каждый сектор или в несколько секторов направляющего аппарата. Кроме того, сектор направляющего аппарата изготовлен, например, паяным методом или ...

Сотовое уплотнение турбомашины

Использование турбостроение, в частности в уплотнениях сотового типа. Сущность изобретения в корпусе 1 установлено статорное коль до 2, на внутренней поверхности которого выполнены скошенные против направления потока утечек сотовые ячейки 3 На роторе 4 с радиальным зазором 5 установлено роторное кольцо 6 с сотовыми элементами 8 и 9, между которыми образован кольцевой паз 10 В корпусе 1 и роторном кольце 6 выполнена система отверстий 12-15 и кольцевых полостей 7 и 11, сообщенных с радиальным зазором 5 для организации дополнительных потоков рабочей среды внутри уплгтнения Зил.

Лабиринтное уплотнение паровой турбины

Изобретение относится к энергомашиностроению и может быть использовано в паровых турбинах. Изобретение позволяет повысить надежность. Уплотнение содержит корпус 1, на внутренней поверхности которого выполнены кольцевые проточки 2 с заплечиками 3, подпружиненные уплотнительные сегментные кольца (СК) 4 с выступами 5. Опорные поверхности последних и заплечиков 3 со стороны высокого давления вьшолнены коническими, а на противоположной им боковой поверхности СК 4 выполнены кольцевые канавки 6. В корпусе 1 вьшолнены радиальные пазы, а СК 4 подпружинены при помощи винтовых пружин 8 сжатия, установленных в упомянутых пазах., Поскольку опорные поверхности выступов 5 и заплечиков 3 вьшолнены коническими, пружины создают дополнительное боковое усилие, прижимающее СК 4 к уплотняемой боковой поверхности проточек 2, а кольцевые канавки 6 образуют дополнительное о лабиринтное уплотнение. 1 з.п. ф-лы, 2 ил.(/) ...

Конструкция ступени паровой турбины

Лабиринтовое уплотнение паровых турбин

Способ восстановления радиальных зазоров в уплотнениях паровых турбин

Kreiselverdichter.

Rotierende Dichtung

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

Dichtungsanordnung für eine drehbeweglich gelagerte Komponente einer Rotationsmaschine

Die Erfindung betrifft eine Dichtungsanordnung (6) für eine drehbeweglich gelagerte Komponente, insbesondere einer Rotationsmaschine (1), mit – einem einen Innendurchmesser aufweisenden äußeren Dichtring (4), der zum Abdichten der Komponente umfänglich um diese anordbar ist und – einer Vielzahl von Labyrinthringen (7), die innenseitig an dem äußeren Dichtring (4) angeordnet sind, wobei die Labyrinthringe (7) radial nach innen vom äußeren Dichtring (4) vorstehen und in einer parallel zu einer Drehachse (R) verlaufenden Richtung derart voneinander beabstandet sind, dass zwischen jeweils zwei Labyrinthringen (7) ein umfänglicher erster Führungskanal (8) für Schmiermittel gebildet ist. Erfindungsgemäß weist der äußere Dichtring (4) zumindest einen, sich in zumindest axialer Richtung erstreckenden zweiten Führungskanal (11) auf, der eine Flussverbindung für Schmiermittel zwischen zumindest zwei umfänglich angeordneten ersten Führungskanälen (8) bereitstellt.

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.

EINRICHTUNG ZUR ABDICHTUNG VON DURCH MEDIEN, WIE FLUESSIGKEITEN UND/ODER GASEN UNTERSCHIEDLICHEN DRUCKES BEAUFSCHLAGTEN RAEUMEN, INSBESONDERE ZWISCHEN WELLEN BEI TURBOMASCHINEN

UEBERGANGSKANALDICHTVORRICHTUNG

Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine

Die Erfindung betrifft eine Einrichtung zur Detektion eines Wellenbruchs an einem Rotor einer ersten Turbine (10), insbesondere einer Mitteldruckturbine, einer Gasturbine, insbesondere eines Flugtriebwerks, wobei stromabwärts der ersten Turbine (10) eine zweite Turbine (11), insbesondere eine Niederdruckturbine, positioniert ist, mit einem zwischen dem Rotor der ersten Turbine (10) und einem Stator der zweiten Turbine (11), gegenüber einem Strömungskanal radial innenliegend positionierten Betätigungselement (16) und mit einem in dem Stator der zweiten Turbine (11) geführten Sensorelement (21), um einen vom radial innenliegend positionierten Betätigungselement (16) detektierten Wellenbruch in ein elektrisches Signal zu wandeln und dieses elektrische Signal an ein Schaltelement zu übertragen, welches gegenüber dem Strömungskanal radial außenliegend an einem Gehäuse der Gasturbine positioniert ist.

DICHTUNGSANORDNUNG

Dichtung zwischen den Stufen einer Gasturbine

Sealing device for the gap between rotor and stator of a turbo machine has brush seal holder with support elements having elastic yield in axial and radial direction

A brush seal holder (7) on the stator (2) has support elements (12), which are elastically yielding in axial and radial direction. The support elements are formed, so that a force directed towards the holder and introduced radially into the elements, combines an elastic radial movement in a section facing the rotor (1), with an elastic axial movement of the section in a direction away from the sealing brush (8).

Dichtungseinrichtung

Einrichtung zur Spaltabdichtung fuer Gleichdruckdampfturbinen

Gasturbine mit gegenläufigen Niederdruckrotoren

Rotationsdichtung mit organischem abschleifbarem Material

Dichtungsanordnung für eine Gasturbine

Gasturbine

Dichtungsanordnung in Turbomaschinen

Eine Dichtungsanordnung in einer Dampfturbine wird in einer Position eingesetzt, in der sie die Dampfströmung entlang einem Strömungsweg in einem Spalt zwischen zwei relativ zueinander drehbaren Bauteilen der Turbine begrenzen kann, wobei der Strömungsweg eine Verbindung zwischen einem Raum mit relativ hohem Druck und einem anderen mit relativ niedrigem Druck bereitstellen kann. Die Dichtungsanordnung umfasst eine Blattdichtung, die an einem der Bauteile angebracht ist und mit dem anderen abdichtend in Eingriff steht. In einer Dampfturbinenanwendung können zwei oder mehr Blattdichtungen nebeneinander angeordnet werden, ohne dass Labyrinthdichtungen erforderlich sind und ohne die bei der Verwendung von Bürstendichtungen unter ähnlichen Umständen angetroffenen nachteiligen Auswirkungen. Die Dichtungsanordnung kann Segmente enthalten, die aus einer Dichtungsposition verschoben werden können, um beim Anfahren der Turbomaschine den Zwischenraum zu vergrößern, wodurch potentiellen Vibrationsproblemen ...

Dichtung zwischen zwei relativ zueinander drehbaren Teilen

Sealing arrangement using flexible seals

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 ...

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.

Composite tubular woven seal for steam turbine diaphragm horizontal joint interfaces

Upper and lower diaphragms 16, 18 of a steam turbine have mating flanges 21 forming a horizontal midline joint interface. Each flange has a groove 40 which registers with a corresponding groove in the opposite flange. A composite woven tubular seal 43 is provided in the mating grooves. The seal comprises an inner woven metal core 46 surrounded by an annular silica fiber layer 48, in turn surrounded by a metal foil 50 with an outer protective covering of a braided stainless steel 52. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.

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 or relating to seals for rotors of turbines and like fluid flow machines

... 649,792. Stuffing-box substitutes. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. March 23, 1948, No. 8581. [Classes 110(iii) and 122(v)] In a seal between a stationary structure 2 and an end face of an adjacent axial flow rotor 1 of a turbine &c. comprising axially opposed annular sealing elements 5, 6, one 5 is secured to the rotor 1 and the other 6 is supported on a plurality of axially extending guide members 8 grouped around the shaft axis and passing through the structure 2 which is one with a fixed housing 3 for a main bearing 4 designed to support only radial loads the axial growth of the shaft being unimpeded, the guides 8 being attached at their ends remote from the seal, to a housing 9 separate from the housing 3, of a thrust bearing 10 mounted on the shaft. The element 6 is biassed by helical springs 14 mounted on the members 8 with their ends abutting the housings 3 and 9 to tend to keep the elements 5, 6 apart. The members 8 are partly located in radially extending guide ways 16 ...

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.

Seal assembly for a gas turbine engine

A seal arrangement 32 is located between turbine shroud seal segments 38 and 40 or alternatively between nozzle guide vanes. Two facing slots 34 and 36 are provided in the segments with radially offset spaces 42 and 44 provided between the segments. A baffle strip member 46 may be cemented into slot 36 or it may be integrally formed with seal segment 40. A flowpath 50 for cooling and sealing air is increased due to the baffle length and offset spaces. The segments, slots, and baffle member may have a generally n-shaped cross-section. More than one baffle member may be provided in the slots.

ROTOR ASSEMBLY E G FOR A GAS TURBINE ENGINE

Rotor assembly e g for a gas turbine engine

A rotor assembly 20 for a gas turbine engine 10 is disclosed. The rotor assembly includes a pair of axially spaced apart rotor disks such as the rotor disks 32 and 34. An inner air seal 50 extends axially between the adjacent rotor disks. A member 56 extends axially between the disks to join the disks together and is attached to the inner air seal at a mid span location to restrain the seal against outward movement.

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

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.

Improvements in and relating to elastic fluid turbines

... 236,962. International General Electric Co., Inc., (Assignees of Allgemeine Elektricitõts Ges.). July 12, 1924, [Convention date]. Void [Published under Sect. 91 of the Act]. Blades.-The shrouding e for the guide blades a overlaps the blades on both sides so that when the turbine is cold a good packing is secured at the blade roots b, d, Fig. 5, on one side of the rotor blades while a clearance f, f<1> is left at the other side, this clearance being transferred to the other side of the rotor blades by the axial expansion of the rotor when hot, as shown in Fig. 6.

Air riding seal arrangement

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 ...

Turbine rotor seal

The seal comprises an axially movable ring 23 of low friction material such as Silicon Carbide or Nitride, which cooperates with a surface of the rotor to form an air bearing and carries a sealing member 31 cooperating with the surface of rotor part 18. The air bearing ensures that the sealing member is maintained at a constant spacing from the rotor. ...

NON-CONTACTING GAS SEAL

TURBINE DIAPHRAGM SEAL STRUCTURE

... 1441855 Seals WESTINGHOUSE ELECTRIC CORP 17 June 1974 [27 June 1973] 26656/74 Heading F2B [Also in Division F1] An axial flow gas turbine including stator blades 17 having shroud segments 19 at their radially inner ends has sealing plates 29 urged by springs 43 into sliding engagement with rib 27 on segments 19 so as to define an annular cooling air chamber 40 between the latter and a seal housing ring 34 supported with freedom for expansion from shroud rib 32. The inner ends of plates 29 locate in circumferential slot 65. Cooling air flows into chamber 40 from the interior of blades 17 via holes 39 and exits through holes 42, a portion then flowing downstream through the labyrinth gap 38 between sealing segments 33 and rotor 12 and the remainder flowing upstream past a flange 41. Seal housing 34 is supported, as described in Specification 1,220,904, by circumferentially spaced pins 45 having square heads 47 slidably engaging slots 44 in shroud rib 32, the pins being carried by eccentric ...

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 ...

SEAL ASSEMBLY

A gas turbine engine

TURBINES

... 1,224,234. Seals. ENGLISH ELECTRIC CO. LTD. 11 July, 1969 [19 July, 1964], No. 34535/68. Heading F2B. A segmental sealing ring 6 in a turbine is urged towards the rotor 3 by the pressure of working fluid, leaf springs 15 being provided having two modes of operation, the first position of the springs being as shown dotted in the space 13 for urging the ring towards the rotor on first assembly of the turbine to enable clearances to be measured and to remove high-spots during testing and the second position shown in full in the spaces 12 for urging the ring away from the rotor to maximum clearance when the turbine is not running at or near full load. During running-up of the turbine, the clearance is progressively reduced. As shown, a segmental gland ring 6 housed in a groove 2 of a steam turbine diaphragm 1 is pressed inwardly against the pressure of leaf springs 15 by the pressure of steam within passages 14, 16. Side thrust is avoided by communicating the passage 16 with a space 17 on the ...

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)

compressor nozzle stage for a turbine engine

A single-piece compressor nozzle stage for a turbine engine, the stage comprising two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing damper means for damping vibration by friction, which damper means are secured to an annular abradable-material support.

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.

Oil mist separation in gas turbine engines

A rotor stage is provided which comprises a shank passage for separating liquid from secondary air system (SAS) air. The shank passage is formed between a radially outer surface of a disc post, a radially inner surface of one or more blade platforms, and the shanks of two neighbouring blades. In use, SAS air is supplied to the shank passage. Any liquid, such as oil, is separated from the SAS air due to the centripetal acceleration of the rotation of the rotor disc. The separated oil can then flow, or seep, past the blade platform and into the working fluid. The remainder of the SAS air passes through a hole in a sealing plate at the downstream end of the rotor stage, thereby providing SAS air with a lower liquid content for use downstream of the rotor stage.

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.

Flow discourager integrated turbine inter-stage u-ring

A gas turbine having rotor discs ( 9 ), a disc cavity ( 13 ) and a stator stage ( 25 ) extending to the disc cavity ( 13 ). Seal housing flanges ( 43, 44 ) extend from a seal housing ( 29 ) of the stator stage ( 25 ). Rotor flanges ( 41 i, 41 o ) extend from a rotor disk ( 9 - 1 ). An inner rotor flange ( 41 i ) and first seal housing flange ( 43 ) are inward from a second seal housing flange ( 44 ). One rotor flange ( 41 o ) is outward from the second seal housing flange ( 44 ). The inner rotor flange ( 41 i ) and first seal housing flange ( 43 ) extend toward one another to limit movement of main gas flow ( 17 ). An inlet ( 47 ) injects air ( 50 ) between the outward rotor flange ( 41 o ) and second seal housing flange ( 44 ).

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 ).

Turbine and method for manufacturing turbine

The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction.

Near flow path seal for a turbomachine

A near flow path seal member for a turbomachine includes a seal body having a seal support member including a first end portion that extends to a second end portion through an intermediate portion. An arm member extends from the first end portion of the seal body. The arm member has a first end that extends to a second end to define an axial dimension of the arm member, a first edge that extends to a second, opposing edge to define a circumferential dimension of the arm member, and a surface having a profile that establishes a thickness variation of the arm member in each of the axial dimension and the circumferential dimension.

METHOD FOR FASTENING A BRUSH SEALING ELEMENT IN A GROOVE OF A HOUSING SEGMENT

A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment. 19.-. (canceled)10. A sealing system , comprising:a brush sealing element; andan accommodating element with an accommodating chamber, wherein the brush sealing element is disposed in the accommodating chamber and wherein a bendable strap is disposed on the accommodating element.11. The sealing system according to claim 10 , wherein the accommodating element includes at least one clamping element and wherein the at least one clamping element is engageable with the brush sealing element.12. The sealing system according to claim 10 , wherein the accommodating element has a U-shaped cross-section at least in a portion of the accommodating element.13. The sealing system according to claim 10 , wherein adjacent walls of the accommodating element have different wall areas and/or wall heights.14. The sealing system according to claim 10 , wherein the accommodating element is comprised of a metal and/or a metal alloy.15. The sealing system according to claim 10 , wherein the accommodating element includes a plurality of clamping elements and wherein the plurality of clamping elements are spaced a distance apart from another.16. The sealing system according to claim 15 , wherein the brush sealing element includes a clamping tube and wherein at least one of the plurality of clamping elements has a geometry that is adapted to a cross- ...

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 ...

Shaped rim cavity wing surface

A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

LEAF SEAL

Described is a leaf seal for sealing between a static component and a relatively rotating component having an axis of rotation, the leaf seal defining axially separated higher pressure upstream and lower pressure downstream areas within the static component when in use, the leaf seal comprising: a plurality of leaf elements having: a root end for attachment to the static component; a free end for wiping contact with the rotating component; an upstream edge extending from the root end to the free end; and, a downstream edge extending from the root end to the free end, wherein the leaf element width between the upstream edge and downstream edge at the root end is a, and width between the upstream edge and the downstream edge at the free end is b, where b<0.5α. 1. A leaf seal for sealing between a static component and a relatively rotating component having an axis of rotation , the leaf seal defining axially separated higher pressure upstream and lower pressure downstream areas within when in use , the leaf seal comprising: a root end for attachment to the static component;', 'a free end for wiping contact with the rotating component;', 'an upstream edge extending from the root end to the free end; and,', 'a downstream edge extending from the root end to the free end,, 'a plurality of leaf elements havingwherein the leaf element is tapered towards the free end, the taper angle of the upstream edge and downstream edge to the normal of the rotational axis are between 2 and 45 degrees in a non-working state.2. A leaf seal as claimed in claim 1 , further comprising an upstream and a downstream cover plate claim 1 , each having an inner wall which faces the leaf element.3. A leaf seal as claimed in claim 2 , wherein the angle of either or both of the upstream inner wall and downstream inner wall relative to the normal of the rotational axis is between 2 and 45 degrees.4. A leaf seal as claimed in claim 2 , wherein either or both of the upstream or downstream cover plate ...

TURBINE ENGINE VARIABLE AREA VANE WITH FEATHER SEAL

An apparatus for sealing a gap between a stator vane platform including a seal slot, and a rotatable stator vane including a shaft connected to a vane end. The apparatus includes a substantially flat, semi-annular seal body, a first tab and a second tab. The seal body extends circumferentially between a first body end and a second body end, and radially between a radial inner body side and a radial outer body side. The inner body side wraps partially around the shaft, and the outer body side mates with the seal slot. The first tab extends axially from the first body end, and the second tab extends axially from the second body end. The first tab and the second tab engage the vane end and cause the seal body to move within the seal slot during rotation of the stator vane. 1. An apparatus for sealing a gap between a stator vane platform comprising a seal slot , and a rotatable stator vane comprising a shaft connected to a vane end , the apparatus comprising:a substantially flat, semi-annular seal body extending circumferentially between a first body end and a second body end, and radially between a radial inner body side and a radial outer body side, wherein the inner body side is configured to wrap partially around the shaft, and the outer body side is configured to mate with the seal slot; anda first tab extending axially from the first body end, and a second tab extending axially from the second body end, wherein the first tab and the second tab are configured to engage the vane end and cause the seal body to move within the seal slot during rotation of the stator vane.2. The apparatus of claim 1 , wherein the seal body claim 1 , the first tab and the second tab are constructed from a sheet of metal.3. The apparatus of claim 1 , wherein the first tab and the second tab are substantially perpendicular to the seal body.4. The apparatus of claim 1 , whereinthe first tab comprises a first base tab segment extending axially from the first body end to a first support tab ...

TURBINE COMPRISING A SEALING DEVICE BETWEEN THE STATOR BLADE CARRIER AND THE HOUSING

The invention relates to a turbine of a power plant, having a stator, which has a housing and in the housing at least one stator blade carrier comprising stator blades. A rotor is provided which has a rotor shaft having rotor blades. At least one sealing device is provided which axially seals the respective stator blade carrier with respect to the housing and separates two regions having different pressures from one another. Improved sealing action is achieved in that the sealing device includes an axially acting primary sealing ring extending in the circumferential direction, and an axially acting additional sealing ring extending in the circumferential direction. The primary sealing ring facing the region has the lower pressure. The additional sealing ring facing the region has the higher pressure. The primary sealing ring is attached axially rigidly on the stator blade carrier. The additional sealing ring is attached axially movably, wherein the additional sealing ring is tensioned axially in the direction of the region having the higher pressure by means of at least one spring element. 2. The turbine as claimed in claim 1 , whereinthe main sealing ring is arranged on an annular shoulder projecting radially from the respective stator blade carrier and extending in the circumferential direction and has an axial sealing contour which cooperates with an axial countersealing contour formed on the housing wherein, the countersealing contour is formed in a reception groove which extends in the circumferential direction and into which the annular shoulder penetrates radially.3. The turbine as claimed in claim 1 , whereinfor the main sealing ring, the stator blade carrier has provided on it fastening screws which run axially and which engage into the main sealing ring on an axial side confronting the additional sealing ring.4. The turbine as claimed in whereinthe main sealing ring is inserted into a main annular groove which is open axially toward the region having the ...

Finned seal assembly for gas turbine engines

A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

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 ...

SEALING OF THE FLOW CHANNEL OF A TURBOMACHINE

A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook. 1. A turbomachine having a flow channel and comprising:a housing radially surrounding the flow channel having at least one housing hook;a plurality of stationary and moving blades situated in the flow channel, the stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook engaging with the housing hook for the purpose of connecting the stationary blades to the housing;at least one sealing and lining element situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, the sealing and lining element having a seal interacting with blade tips of the moving blades;at least one heat protection element being in the area of the sealing and lining element between the sealing and lining element and the housing; anda further seal situated on the heat protection element to create sealing contact with the housing hook.2. The turbomachine as recited in wherein the further seal is situated in a radially clamped manner.3. The turbomachine as recited in wherein the ...

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 ...

SEALING BETWEEN A ROTOR DISC AND A STATOR OF A TURBOMACHINE

Assembly including a rotor disc, an adjacent stator and a plurality of sealing elements secured to the rotor disc, the stator including an inner platform and a root bearing at least one abradable element configured to cooperate with the sealing elements, the sealing elements being placed in an enclosure formed by the abradable element, the enclosure being open to the inside and delimited axially by an upstream abradable edge and a downstream abradable edge, the enclosure being delimited radially by an outer abradable edge, at least one of the sealing elements including a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge, and a second, separate lip configured to cooperate with the outer abradable edge. 1. An assembly for a turbomachine comprising a first mobile wheel extending around an axis and an adjacent bladed turbine stator , said bladed turbine stator being coaxial with said axis and axially offset from said first mobile wheel , said assembly comprising a plurality of sealing elements , each sealing element being secured to said first mobile wheel and projecting radially from said first mobile wheel , said bladed turbine stator comprising an inner platform intended to delimit a gas flow channel in the turbomachine and a root extending radially below the inner platform , said root bearing at a radially inner end at least one abradable element configured to cooperate with the sealing elements , characterised in that the sealing elements are placed in an enclosure formed by said at least one abradable element , said enclosure being open inwards and delimited axially by an upstream abradable edge and a downstream abradable edge , said enclosure being radially delimited by an outer abradable edge , and in that at least one of the sealing elements comprises a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge , and a second lip separate from the first lip and configured ...

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.

KNIFE EDGE WITH INCREASED CRACK PROPAGATION LIFE

A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed. 1. A knife edge seal , comprising:a pedestal;a knife edge including a tip and a base, the base resting on the pedestal; andwherein the base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1.2. The knife edge seal of claim 1 , wherein an angle between the knife edge and the pedestal is in the range of 110 to 160 degrees.3. The knife edge seal of claim 1 , wherein the second width is equivalent to a width of the pedestal.4. The knife edge seal of claim 1 , wherein the seal mates with a mating component.5. The knife edge seal of claim 4 , wherein the mating component rotates relative to the seal.6. The knife edge seal of claim 4 , wherein the mating component is stationary claim 4 , and the seal rotates relative to the mating component.7. The knife edge seal of claim 1 , wherein the seal is comprised of a nickel-chromium alloy.8. The knife edge seal of claim 1 , wherein the seal is mounted on a rotor.9. A gas turbine engine claim 1 , comprising:a rotor including one or more blades; andat least one seal configured to prevent pressurized gases from reaching a radially inner portion of the rotor, wherein the at least one seal includes a pedestal and a knife edge with a tip and a base, the base resting on the pedestal, and wherein the base has a first width and the tip has a second width; andwherein the ratio of the first width to the second width is in the range of 5:1 to 15:1.10. The gas turbine engine of claim 9 , wherein an angle between the knife edge and the pedestal is in the range of 110 to 160 degrees.11. The gas turbine ...

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 ...

TURBINE SEAL SYSTEM AND METHOD

A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal. 1. A system , comprising: a first turbine stage comprising a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel;', 'a second turbine stage comprising a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel; and', a first coverplate coupled to the first turbine stage, wherein the first coverplate comprises a first seal;', 'a second coverplate coupled to the second turbine stage, wherein the second coverplate comprises a second seal; and', 'an interstage seal, wherein the first coverplate, the second coverplate, or both are configured to support the interstage seal., 'a seal assembly extending axially between the first and second turbine stages, comprising], 'a multi-stage turbine, comprising2. The system of claim 1 , wherein the interstage seal comprises one or more seal teeth configured to block interstage axial leakage between the first turbine stage and the second turbine stage.3. The system of claim 1 , comprising a forward sealing element claim 1 , an aft sealing element claim 1 , or both ...

PRETRENCHED ROTOR FOR GAS TURBINE ENGINE

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench. 1. A gas turbine engine , comprising:a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench.2. The gas turbine engine of claim 1 , wherein the rotor is a compressor rotor.3. The gas turbine engine of claim 1 , wherein an outer wall of the rotor extends generally linearly from a base of a rotor blade to the pretrench claim 1 , the rotor blade directly adjacent axially to the stator.4. The gas turbine engine of claim 1 , wherein the stator extends radially from a position radially outside a base of a rotor blade to a position radially inside the base claim 1 , the rotor blade directly adjacent axially to the stator.5. The gas turbine engine of claim 1 , an outer wall section of the rotor extends from a base of a rotor blade upstream the pretrench to a base of a rotor blade downstream the pretrench claim 1 , wherein a floor of the pretrench is closer to a rotational axis of the rotor than any other portion of the outer wall section.6. The gas turbine engine of claim 1 , wherein the stator is a cantilevered stator.7. The gas turbine engine of claim 1 , wherein a maximum radial depth of the pretrench is 50 percent of the thickness of the rotor arm at a forwardmost portion of the pretrench.8. The gas turbine engine of claim 1 , including an upstream side and a downstream side of the pretrench claim 1 , the upstream side and the downstream side both angled relative to a radial axis having an angle up to 90 degrees.9. The gas turbine engine of claim 1 , wherein the rotor is a rotor of a geared gas turbine engine.10. The gas turbine engine of claim 1 , wherein a floor of the pretrench is generally linear.11. The gas turbine engine of claim ...

CANTILEVER STATOR WITH VORTEX INITIATION FEATURE

An axial flow compressor is disclosed with a plurality of rotors. Each rotor includes a disk having an outer rim. Each outer rim is coupled to a radially outwardly extending rotor blade. The case is coupled to a plurality of radially inwardly extending stator vanes, i.e. cantilever-type stator vanes. Each stator vane is disposed between two rotor blades and extends towards one of the outer rims and terminates at a tip disposed in close proximity to one of the outer rims. At least one of the outer rims includes a serrated outer surface that faces the tip of a stator vane which results in a vortex flow causing air that would normally leak through the clearance between the stator vane and the outer rim to engage the stator vane to a greater degree thereby increasing the efficiency of the compressor. 1. An axial flow compressor , comprising:a plurality of rotors coaxially disposed within a case and coupled together, each rotor including a disk having a radially outward end that includes an outer rim, each outer rim is coupled to a radially outwardly extending rotor blade, each radially outwardly extending rotor blade terminating at a tip;the case being coupled to a plurality of radially inwardly extending stator vanes, each stator vane extending towards one of the outer rims and terminating at a tip disposed in close proximity to one of the outer rims;at least one outer rim including a serrated outer surface that faces the tip of one of the stator vanes.2. The compressor of wherein the serrated outer surface includes a plurality of adjacent grooves.3. The compressor of wherein the serrated outer surface includes a plurality of coaxial grooves separated by lands with each land disposed between two grooves claim 1 , the grooves being defined by a bottom surface disposed between two side walls claim 1 , the sidewalls being slanted in a fore direction.4. The compressor of wherein the lands are flat.5. The compressor of wherein that stator vane that faces the serrated outer ...

SHAPED RIM CAVITY WING SURFACE

A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing. 1. A shaped rim cavity wing comprising:a body configured to extend from one of a rotating component and a stationary component of a turbomachine to inhibit airflow through a gas path between the rotating component and the stationary component;an upper surface of the body; a first concave portion;', 'a convex portion adjacent the first concave portion;', 'a first inflection point between the convex portion and the first concave portion;', 'a second concave portion adjacent the convex portion; and', 'a second inflection point between the second concave portion and the convex portion; and, 'a lower surface of the body, the lower surface having a geometric shape to control the separation of airflow as it passes around the lower surface, the geometric shape includinga point of maximum extent that defines a boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that separates airflow from the shaped rim cavity wing and creates flow re-circulation adjacent to the upper surface of the shaped rim cavity wing;wherein the first concave portion is located adjacent the point of maximum extent.2. The shaped rim cavity wing of claim 17 , further including:a flat portion located between the point of maximum extent and the lower surface.3. The shaped rim cavity wing of claim 18 , wherein the flat portion is vertical.4. The shaped rim cavity wing of claim 17 , wherein the body extends from the rotating component of the ...

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 ...

TURBOMACHINE SEALING ELEMENT

The present invention relates to sealing element for sealing a radial gap relative to a counter element of a turbomachine, wherein the sealing element has a number of adjacent cells in the peripheral direction and/or in the axial direction, which are joined to one another by common walls, wherein an extension of a least one, in particular front-side, cross section of at least one cell in a first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against a radial flange of the counter element is smaller than that in a second axial section of the sealing element that adjoins the first axial section upstream and/or in a second axial section that adjoins the first axial section downstream. 1. A sealing element for sealing a radial gap relative to a counter element of a turbomachine , wherein the sealing element has a number of adjacent cells in the peripheral direction and/or in the axial direction , which are joined to one another by common walls , wherein an extension of a least one , in particular front-side , cross section of at least one cell in a first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against a radial flange of the counter element is smaller than that in a second axial section that adjoins the first axial section upstream and/or in a second axial section of the sealing element that adjoins the first axial section downstream.2. The sealing element according to claim 1 , wherein an extension of at least one claim 1 , front-side claim 1 , cross section of at least one cell in another first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against another radial flange of the counter element is smaller than that in a second axial section of the sealing element that adjoins the additional first axial section upstream and/or in a second axial section that adjoins the additional first ...

ROTOR FOR A TURBOMACHINE, AND TURBOMACHINE HAVING SUCH A ROTOR

A rotor () for a turbomachine, in particular for an aircraft engine, having a rotor base body (), on which at least one sealing fin (), which is disposed on a base (), is provided for cooperating with an associated sealing element () of the turbomachine; relative to an axial direction of the rotor (), the base () having a base portion () disposed upstream of the sealing fin () and a base portion () disposed downstream thereof, for supporting masks during the coating of sealing fins; the upstream base portion () and the downstream base portion () having different radial distances (A, A) to a radially outer sealing tip () of the sealing fin (). Also, a turbomachine having at least one such rotor (). 112-. (canceled)13. A rotor for a turbomachine , the rotor comprising:a rotor base body having at least one sealing fin disposed on a base, the sealing fin for cooperating with an associated sealing element of the turbomachine; and, relative to an axial direction of the rotor, the base having a base portion upstream of the sealing fin, and a base portion downstream of the sealing fin, for supporting masks during coating of the sealing fin, wherein the upstream base portion and the downstream base portion have different radial distances to a radially outer sealing tip of the sealing fin.14. The rotor as recited in wherein a ratio between the radial distance of the upstream base portion and the radial distance of the downstream base portion is between 0.25 and 4 claim 13 , the ratio not being 1.15. The rotor as recited in wherein the rotor is a compressor rotor claim 13 , and the upstream base portion has a larger distance to the radially outer sealing tip of the sealing fin than the downstream base portion.16. The rotor as recited in wherein the rotor is a turbine rotor claim 13 , and the upstream base portion has a smaller distance to the radially outer sealing tip of the sealing fin than the downstream base portion.17. The rotor as recited in wherein the upstream base ...

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 ...

GAS TURBINE ENGINE ROTOR DISK-SEAL ARRANGEMENT

A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

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 ...

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 ...

COOLED TURBINE RUNNER FOR AN AIRCRAFT ENGINE

A cooled turbine runner for a gas turbine, in particular an aircraft engine, with turbine blades that are radially arranged at the circumferential surface of a rotor disk, wherein respectively a turbine blade is inserted with a profiled blade root into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk. A cooling device with at least one cooling air supply channel is provided, which extends at least substantially axially and at least over a part of the axial length of the blade root, and which has at least one inlet with an inlet opening at an inflow side of the blade root, wherein the inlet is embodied with a projection. A middle axis of the inlet has, in a direction oriented towards the inlet opening and in the area of the inlet opening, an extension component in the rotational direction of the rotor disk. 1. A cooled turbine runner for a gas turbine , in particular an aircraft engine , with turbine blades that are radially arranged at a circumferential surface of a rotor disk , wherein respectively a turbine blade is inserted with a profiled blade root into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk , and wherein a cooling device is provided with at least one cooling air supply channel which extends at least substantially axially and at least over a part of the axial length of the blade root , and which has at least one inlet with an inlet opening at an inflow side of the blade root , wherein the inlet is embodied with a projection , characterized in that a middle axis of the inlet , in a direction oriented towards the inlet opening and in the area of the inlet opening , has an extension component in the rotational direction of the rotor disk.2. The turbine runner according to claim 1 , wherein the projection is configured at a disk device that is arranged in front of the blade root seen in the flow direction claim 1 , and that is in particular held in abutment at the ...

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 ...

Vane with Sealed Lattice in a Shroud of an Axial Turbomachine Compressor

The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.

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 ...

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 ...

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 ...

ENGINE WITH FACE SEAL

A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal. 1. A turbine engine comprising:a stator having axially spaced first and second structural elements;a rotor;a face seal between the rotor and the stator comprising a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface; andan airflow circuit flowing air in contact with one of the first and second structural elements to operationally equalize a transient thermal response of the first and second structural elements to prevent contact between the rotating and non-rotating bearing surfaces.2. The turbine engine of wherein the airflow circuit passes through the non-rotating gas bearing face.3. The turbine engine of wherein the airflow circuit comprises a conduit formed with one of the first and second structural elements.4. The turbine engine of wherein the conduit is formed on an exterior of the one of the first and second structural elements.5. The turbine engine of wherein the conduit is formed on an interior of the one of the first and second structural elements.6. The turbine engine of wherein the stator comprises a slider and the slider has the first and second structural elements supporting the non-rotating gas bearing face claim 1 , and the airflow circuit passes through the non-rotating gas bearing face to provide gas between the rotating and non-rotating gas bearing faces.7. The turbine engine of wherein the non-rotating gas bearing face is circumferential and first and second structural elements comprise crossbars ...

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 ...

REMOVABLY ATTACHED AIR SEAL FOR ROTATIONAL EQUIPMENT

An assembly is provided for rotational equipment. This assembly includes a rotor disk, an annular arm, an annular air seal and an annular seal land. The rotor disk is rotatable about an axis. The annular arm is connected to the rotor disk. The annular arm projects axially out from the rotor disk to a distal arm end. The annular air seal is removably attached to and substantially completely supported by the annular arm at the distal arm end. The annular seal land is sealingly engaged with the annular air seal. 1. An assembly for rotational equipment , comprising:a rotor disk rotatable about an axis;an annular arm connected to the rotor disk, the annular arm projecting axially out from the rotor disk to a distal arm end;an annular air seal removably attached to and substantially completely supported by the annular arm at the distal arm end; andan annular seal land sealingly engaged with the annular air seal.2. The assembly of claim 1 , whereinthe annular air seal comprises a knife edge seal element; andthe annular seal land comprises an abradable seal land.3. The assembly of claim 2 , wherein the annular air seal further comprises a second knife edge seal element.4. The assembly of claim 1 , whereinthe annular air seal includes a seal element and a mount;the seal element projects radially out from the mount to a tip that sealingly engages the annular seal land; andthe mount is nested with the annular arm.5. The assembly of claim 4 , wherein the mount is nested within the annular arm.6. The assembly of claim 4 , wherein the annular arm is nested within the mount.7. The assembly of claim 4 , wherein the seal element comprises a knife edge seal element.8. The assembly of claim 4 , wherein the seal element is substantially perpendicular to the mount.9. The assembly of claim 4 , wherein the seal element is offset from the base by an acute angle and projects axially out from the mount and towards the rotor disk.10. The assembly of claim 4 , wherein the seal element is ...

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. ...

Gas Turbine Engine with Separable Shaft and Seal Assembly

A gas turbine engine defining a radial direction is provided. The gas turbine engine includes a tie shaft; a compressor section including a last rotor stage, the compressor section assembled to a first portion of the tie shaft; a separable shaft disposed between the compressor section and the tie shaft, the separable shaft having a radial outward portion and a radial inward portion, the radial outward portion of the separable shaft in contact with a portion of the last rotor stage at an interface; and a seal assembly operable with a portion of the separable shaft proximate the radial inward portion. 1. A gas turbine engine defining a radial direction , the gas turbine engine comprising:a tie shaft;a compressor section including a last rotor stage, the compressor section assembled to a first portion of the tie shaft;a separable shaft disposed between the compressor section and the tie shaft, the separable shaft having a radial outward portion and a radial inward portion, the radial outward portion of the separable shaft in contact with a portion of the last rotor stage at an interface; anda seal assembly operable with a portion of the separable shaft proximate the radial inward portion.2. The gas turbine engine of claim 1 , wherein the separable shaft is attached to or formed integrally with a connection shaft at the radial inward portion claim 1 , wherein the connection shaft extends along an axial direction of the gas turbine engine.3. The gas turbine engine of claim 1 , wherein the radial inward portion is located inward from the radial outward portion along the radial direction.4. The gas turbine engine of claim 1 , wherein the separable shaft includes a connection end located at a radially innermost end of the separable shaft claim 1 , and wherein the connection end is coupled to a second portion of the tie shaft.5. The gas turbine engine of claim 4 , wherein the radial inward portion is located proximate the radially innermost end of the separable shaft.6. The ...

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 ...

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 ...

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 ...

SEALING DEVICE BETWEEN TWO AXISYMMETRIC COAXIAL PARTS

A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force. 1. A sealing device between two axisymmetric coaxial parts , said device including:an annular elastic segment with an angular opening;two holding elements located on each side of said annular segment and adapted to hold said segment in position axially while allowing a limited axial displacement; andan annular spacer arranged between said two holding elements and adapted to hold said two holding elements at a given spacing;wherein said annular spacer has a notch around its peripheral rim; andwherein said annular elastic segment has a hooking element means at each of its free ends adapted to cooperate with said notch of said annular spacer, and to hold said elastic segment in a pre-holding position by elastic return force, in which an outside diameter of said elastic segment is less than the outside diameter of said elastic segment when it the elastic segment is in its free state and in which a central axis of said elastic segment is offset from the central axis of said annular spacer.2. The sealing device between two axisymmetric coaxial parts claim 1 , according to claim 1 , wherein said notch is a dovetail.3. The sealing device between two axisymmetric coaxial parts claim 1 , according to claim 1 , wherein said two holding elements have shoulders adapted to hold said annular spacer in the radial direction.4. The sealing device between two axisymmetric coaxial parts claim 1 , according to claim 1 , wherein said annular segment is made of carbon.5. The sealing device between two ...

WOUND RETAINING WIRE

An assembly of a gas turbine engine includes a first component, a second component disposed radially outboard of the first component. The second component includes one or more flange segments circumferentially spaced apart by one or more flange openings. Each flange segment includes a groove extending radially outwardly from a radially inboard surface of each flange segment between the first component and the second component. A retaining wire extends along each groove and is located radially between the first component and the second component to axially retain the second component to the first component. A radial cross-sectional size of the retaining wire is greater than a radial gap between the radially inboard surface of the second component and the first component. 1. An assembly of a gas turbine engine , comprising:a first component;a second component disposed radially outboard of the first component, the second component including one or more flange segments circumferentially spaced apart by one or more flange openings, each flange segment including a groove extending radially outwardly from a radially inboard surface of each flange segment between the first component and the second component; anda retaining wire extending along each groove and disposed radially between the first component and the second component to axially retain the second component to the first component;wherein a radial cross-sectional size of the retaining wire is greater than a radial gap between the radially inboard surface of the second component and the first component.2. The assembly of claim 1 , wherein the retaining wire is configured for installation via a flange opening of the one or more flange openings.3. The assembly of claim 1 , wherein the retaining wire includes a removal feature.4. The assembly of claim 3 , wherein the removal feature is a loop portion formed in the retaining wire.5. The assembly of claim 1 , wherein both of a first wire end of the retaining wire and a ...

ROTOR AND TURBO MACHINE INCLUDING SAME

A sealing assembly for sealing a gap between a first component and a second component is provided. The sealing assembly includes a sealing body disposed between the first component and the second component and a pressing member disposed between the sealing body and the second component, configured to press the sealing body toward the first component, and configured to extend and compress in a circumferential direction of the first component. 1. A sealing assembly for sealing a gap between a first component and a second component , the sealing assembly comprising:a sealing body disposed between the first component and the second component; anda pressing member disposed between the sealing body and the second component, configured to press the sealing body toward the first component, and configured to extend and compress in a circumferential direction of the first component.2. The sealing assembly according to claim 1 , wherein the second component includes a sealing groove on a first-side surface facing the first component claim 1 ,the sealing body is inserted into the sealing groove, andthe pressing member is inserted into the sealing groove and disposed on an opposite side of the first component with the sealing body interposed therebetween.3. The sealing assembly according to claim 1 , wherein the sealing body includes a recess extending in the circumferential direction and formed on a second-side surface facing the second component claim 1 , andthe pressing member is installed in the recess.4. The sealing assembly according to claim 1 , wherein the pressing member comprises:a first pressing portion fixed to the sealing body;a second pressing portion spaced from the first pressing member in the circumferential direction of the first component and installed to move along a surface of the sealing body in the circumferential direction; anda third pressing portion connected to both ends of the first pressing portion and the second pressing portion.5. The sealing ...

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.