ЛОПАТКА И ЛОПАТОЧНЫЙ УЗЕЛ ДЛЯ ГАЗОВОЙ ТУРБИНЫ

Лопатка для газовой турбины содержит хвостовую секцию, выполненную с возможностью установки на диск, перо и уплотнительную полосу. Хвостовая секция содержит полку, на которой расположено перо, а также полость, окруженную радиально внутренней поверхностью полки, стороной первой кромки хвостовой секции и стороной второй кромки хвостовой секции. Стороны первой и второй кромок отстоят друг от друга вдоль осевого направления газовой турбины. Уплотнительная полоса расположена на внутренней поверхности полки и имеет первую концевую секцию, среднюю секцию и вторую концевую секцию. Первая концевая секция отстоит от второй концевой секции вдоль осевого направления, а средняя секция расположена между ними. Сторона первой кромки содержит выемку, в которую первая концевая секция уплотнительной полосы вставлена таким образом, что выемка окружает первую концевую секцию и тем самым крепит первую концевую секцию к внутренней поверхности полки. Хвостовая секция также содержит опорный элемент, проходящий ...

ПРЕДОТВРАЩЕНИЕ ВОЗБУЖДЕНИЯ КРУТИЛЬНЫХ КОЛЕБАНИЙ В УПРАВЛЯЕМЫХ ПРЕОБРАЗОВАТЕЛЕМ ВЕТВЯХ КОМПРЕССОРОВ

Изобретение относится к области электротехники и может быть использовано в машине с управляемым преобразователем приводом. Технический результат - усовершенствование рабочих характеристик машин. Преобразователь (VFG) частоты выполнен таким образом, что на диаграмме Кэмпбелла для рабочей машины (WM) получаются пересечения собственной крутильной частоты ротора (R) машины (М) с V-образными симметричными прямыми межгармонической частоты возбуждения для выходных частот F, F, F, … F. Частоты F, … Fсгруппированы в области G, …, G, … Gконцентрации по частоте вращения машины. В Gобъединены F, таким образом близко расположенные друг относительно друга, что в каждом случае они имеют друг с другом общую исходную точку на оси абсцисс. Верхняя и нижняя граница области G, …, G, … Gконцентрации определены точкой пересечения наиболее низкой и/или второй наиболее низкой, и/или третьей наиболее низкой собственной крутильной частоты ротора с двумя прямыми пары лучей межгармоник первого порядка соответствующей ...

УЗЕЛ СТАТОРА И РОТОРА ТУРБИНЫ И ТУРБИННЫЙ ДВИГАТЕЛЬ

Группа изобретений относится к глубинному приводному буру для вращательного бурения. Узел статора и ротора турбины содержит размещенные соосно статор (1) и ротор (2). Статор (1) содержит корпус, лопатку и обод. Ротор (2) содержит корпус, лопатку и обод. Внутренняя стенка обода статора соосно размещена с внешней стенкой корпуса ротора. Линия пересечения каждой точки на внешнем контуре лопатки статора с меридиональной плоскостью, соответствующей ей, представляет собой первую линию пересечения, которая перпендикулярно пересекается с первой прямой линией проекции, продолжающейся через обод статора. Линия пересечения каждой точки на внешнем контуре лопатки ротора с меридиональной плоскостью, соответствующей ей, представляет собой вторую линию пересечения, которая перпендикулярно пересекается со второй прямой линией проекции, продолжающейся через корпус ротора. Группа изобретений направлена на обеспечение высокой гидравлической эффективности, простой конструкции, высокого крутящего момента и ...

УЗЕЛ ПЕРА ЛОПАТКИ И ПОЛКИ ДЛЯ СВЕРХЗВУКОВОГО ПОТОКА

Узел пера лопатки и полки включает перо и полку, на поверхности которой установлено перо, причем поверхность полки имеет углубление между передней кромкой и задней кромкой пера лопатки. Наиболее глубокий сегмент углубления расположен в половине, выше по потоку, пера лопатки. Скелетная кривая является кривой, представляющей собой вариации скелетного угла пера лопатки в секущей плоскости, параллельной поверхности полки, в зависимости от положения вдоль оси колеса. Линеаризованная скелетная кривая является линеаризованным представлением скелетного угла в зависимости от положения вдоль оси колеса и представляет собой прямую линию, соединяющую точки, характеризующие скелетный угол при 10 и при 90% осевого размера пера лопатки от передней кромки, в непосредственной близости от полки скелетная кривая имеет приподнятый участок, лежащий над линеаризованной скелетной кривой. Плоскость, в которой смещение между скелетной кривой и линеаризованной скелетной кривой является максимальным, расположена ...

РОТОРНЫЙ УЗЕЛ ТУРБИНЫ И РОТОР ДЛЯ РОТОРНОЙ МАШИНЫ

Роторный узел турбины содержит изготовленные отдельно первую и вторую части роторного элемента. Первая часть роторного элемента изготовлена отдельно методом пластической деформации из первого материала, причем первый материал обработан с использованием первого технологического процесса. Вторая часть роторного элемента также изготовлена отдельно методом пластической деформации из второго материала, того же, что и первый материал, при этом второй материал обработан с использованием второго технологического процесса. Вторая часть приварена к первой в осевом положении. Первый и второй материалы содержат сплавы на основе титана. Другое изобретение группы относится к ротору с продольной осью, содержащему две изготовленные отдельно части, выполненные как указано выше. Изобретения позволяют обеспечить оптимальное сопротивление ползучести и оптимальную усталостную прочность ротора турбины. 2 н. и 6 з.п. ф-лы, 3 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 ...

ЛОПАСТЬ РОТОРА ТУРБОМАШИНЫ, ДИСК РОТОРА ТУРБОМАШИНЫ, РОТОР ТУРБОМАШИНЫ И ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ С РАЗНЫМИ УГЛАМИ КОНТАКТНОЙ ПОВЕРХНОСТИ ХВОСТОВИКА И ГНЕЗДА

Лопасть ротора турбомашины имеет хвостовик елочной формы для закрепления на диске ротора. Хвостовик содержит нижнюю часть хвостовика и боковые стороны хвостовика, причем каждая боковая сторона хвостовика имеет первый, второй и третий выступ, содержащие соответственно первую, вторую и третью контактные поверхности, приспособленные для контакта с контактной поверхностью диска ротора. Первый выступ хвостовика, расположенный ближе к нижней части хвостовика, чем второй выступ, а второй выступ хвостовика расположен ближе к нижней части хвостовика, чем третий выступ. Первая, вторая и третья контактные поверхности наклонены относительно радиальной оси нижней части хвостовика на первый, второй и третий угол соответственно. По меньшей мере один из первого, второго и третьего углов хвостовика находится в диапазоне от 1° до 15° от любого из других углов хвостовика. Еще одно изобретение группы относится к диску ротора турбомашины с гнездом елочной формы, выполненным для размещения хвостовика елочной ...

ТУРБОВИНТОВОЙ ДВИГАТЕЛЬ

Настоящее изобретение относится к способам проектирования и изготовления ротора, который является как турбиной, так и рабочим колесом, имеющим лопатки, которые являются полыми по всей длине и ведут в периферийные кольцевые камеры, действующие в качестве двигателя (THRA), который может получать энергию с помощью рабочих сред. Позволяет заметно увеличить осевую тягу. 9 з.п. ф-лы, 3 ил.

ВЫСОКОНАГРУЖЕННЫЙ ДИСК ТУРБИНЫ ИЛИ КОМПРЕССОРА

Изобретение относится к высоконагруженным дискам турбин или компрессоров, применяемых в авиационных и наземных газотурбинных двигателях. Высоконагруженный диск турбины или компрессора содержит ступицу с замкнутой полостью. Замкнутая полость в ступице является незаполненной и выполнена тороидальной, с образующей тора в форме замкнутой плоской кривой - эллипса, с большой и малой осями. Большая ось эллипса расположена в радиальном направлении диска, а соотношение размеров большой и малой осей эллипса составляет 1,3…1,6. Изобретение позволяет снизить напряженность и повысить циклическую долговечность высоконагруженного диска турбины или компрессора. 3 ил., 1 табл.

БАРАБАН РОТОРА ОСЕВОЙ ТУРБОМАШИНЫ И ТУРБОМАШИНА

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

СИСТЕМА ПОДАЧИ ДОБАВКИ К ВЫХЛОПНЫМ ГАЗАМ, ВКЛЮЧАЮЩАЯ УСТРОЙСТВО РАСПРЕДЕЛЕНИЯ ДОБАВКИ К ВЫХЛОПНЫМ ГАЗАМ И УСТРОЙСТВО ДОЗИРОВАНИЯ ДОБАВКИ К ВЫХЛОПНЫМ ГАЗАМ

Настоящее изобретение относится к системе подачи для турбины (6) турбокомпрессора выхлопной системы двигателя (2) внутреннего сгорания, причем система подачи включает распределительное устройство (24) и дозирующее устройство (26). Распределительное устройство (24) включает приемную поверхность (40, 46, 54) и по меньшей мере одну распределительную поверхность(-ти) (42, 48, 56). Приемная поверхность (40, 46, 54) предназначена для приема добавки к выхлопным газам, подаваемой в распределительное устройство (24). Распределительная поверхность (42, 48, 56) находится в сообщении по текучей среде с приемной поверхностью (40, 46, 54) и выполнена для распределения добавки к выхлопным газам в потоке выхлопных газов, проходящем через турбину турбокомпрессора, в результате вращательного движения распределительного устройства (24). Распределительное устройство (24) прочно присоединено к валу (20) или ступице турбины (6) турбокомпрессора. Дозирующее устройство (26) включает подводящий канал (28), дозировочный ...

РАБОЧЕЕ КОЛЕСО АВИАЦИОННОГО ДВИГАТЕЛЯ И СПОСОБ ЕГО ИЗГОТОВЛЕНИЯ ИЗ КОМПОЗИЦИОННОГО МАТЕРИАЛА

Изобретение относится к области турбостроения. Рабочее колесо авиационного газотурбинного двигателя содержит лопатки, неразъемно-соединенные с опорным кольцом, переднем и заднем фланцами. Хвостовик лопатки дополнительно защемлен межлопаточным креплением, монолитно выполненным с опорным кольцом, переднем и заднем фланцами. На входной кромке металлическая накладка защемлена хвостовиком лопатки, переднем фланцем и межлопаточным креплением, которые плотно контактируют со стопором металлической накладки. При изготовлении указанного рабочего колеса осуществляют раскрой слоев материала лопаток и единых заготовок для опорного кольца, переднего и заднего фланцев, в последних выполняют разрез от места касания задней кромки лопатки по диаметру до внешней окружности. Раскрой для лопаток осуществляют с обеспечением выхода материала, предназначенного для межлопаточного крепления, за пределы контура хвостовика. Прессуют лопатки совместно с металлической накладкой на входной кромке. Укладывают в сепаратор ...

РАБОЧЕЕ КОЛЕСО ТУРБИНЫ

Изобретение относится к рабочему колесу турбины газотурбинной установки. Каждая лапка стороны рабочего колеса в рабочем колесе турбины образована таким образом, что донная поверхность второй канавки является непрерывной с донными поверхностями первых канавок, которые примыкают к ней. Форма наружного контура каждой лапки стороны рабочего колеса, если смотреть в осевом направлении, представляет собой форму, в которой участок конкретной формы заменен прямыми участками вдоль предварительно заданных прямых линий. Конкретная форма включает в себя предварительно заданный диапазон формы наружного контура крепежной части, если смотреть в осевом направлении. Участок расположен по меньшей мере на радиально внутренней стороне донной поверхности второй канавки и расположен на наружной стороне в окружном направлении предварительно заданных прямых линий. Предварительно заданные прямые линии проходят через центральную ось и точки в пределах диапазона вдоль конкретной формы от пересечения с донной поверхностью ...

Рабочее колесо вентилятора с обтекателем и способ изготовления из композиционного материала

Изобретение относится к области турбостроения. Рабочее колесо газотурбинного двигателя содержит лопатки, неразъемно соединенные с опорным кольцом, передним и задним фланцами. Хвостовик лопатки дополнительно защемлен межлопаточным креплением, монолитно выполненным с опорным кольцом, передним и задним фланцами. Защитная металлическая накладка на входной кромке защемлена хвостовиком лопатки, передним фланцем и межлопаточным креплением. На переднем фланце неразъемно установлен обтекатель через центрирующий фиксатор, а силовое крепление выполнено композиционным материалом, проходящим по аэродинамическому профилю обтекателя и опорного кольца и уложенным на заднем фланце. Раскрой лопаток осуществляют с обеспечением выхода материала, предназначенного для межлопаточного крепления, за пределы контура хвостика. Прессуют лопатки совместно с металлической накладкой на входной кромке. Укладывают материал для силового крепления обтекателя в гнездо пресс-формы, устанавливают обтекатель с центрирующим фиксатором ...

ЛОПАТКА ТУРБИНЫ, ДИСК ТУРБИНЫ И ТУРБИНА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Лопатка турбины газотурбинного двигателя содержит спинку, корытце, переднюю кромку, заднюю кромку и полость в своей вершине. Полость в вершине лопатки имеет внутреннее ребро, проходящее от точки соединения бортика указанной полости со стороны спинки к точке соединения бортика указанной полости со стороны корытца. Внутреннее ребро содержит участок восприятия нагрузки потоков утечки, который проходит от спинки, и участок, образующий отражатель, который продолжает участок восприятия нагрузки с изгибом и направляет потоки утечки в сторону корытца. Другие изобретения группы относятся к диску турбины и турбине высокого давления турбореактивного двигателя, содержащим указанные выше лопатки. Группа изобретений позволяет снизить утечки через вершину лопаток газотурбинного двигателя. 3 н. и 7 з.п. ф-лы, 8 ил.

Способ изготовления полого диска из жаропрочного сплава

Изобретение относится к способам изготовления полых дисков из жаропрочных сплавов и может найти применение при изготовлении высокотемпературных роторов турбин газотурбинных двигателей. Две осесимметричные половины диска, содержащие ступицу с прорезью, две стенки и обод с обращенными друг к другу контактными поверхностями, образующие полость, соединяют между собой через контактные поверхности сварным швом, расположенным в плоскости симметрии диска. Контактные поверхности выполняют в виде расположенного с внутренней стороны обода замкового соединения, включающего кольцевой паз, и размещают в нем с натягом соответствующий кольцевой выступ. Паз и выступ выполняют со стороны внешней цилиндрической поверхности замкового соединения, смещают относительно плоскости симметрии диска и располагают соответствующие поверхности паза и выступа в плоскости, параллельной плоскости симметрии диска с образованием беззазорного стыкового соединения. Сварку осуществляют со стороны полости диска, причем глубину ...

УСТРОЙСТВО ДЛЯ ЗАКРЕПЛЕНИЯ РАБОЧЕГО КОЛЕСА НА ВАЛУ

... 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 ...

ЛОПАСТНАЯ СИСТЕМА С РЕГУЛИРУЕМЫМ УГЛОМ УСТАНОВКИ

ЛОПАСТЬ РОТОРА ТУРБОМАШИНЫ, ДИСК РОТОРА ТУРБОМАШИНЫ, РОТОР ТУРБОМАШИНЫ И ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ С РАЗНЫМИ УГЛАМИ КОНТАКТНОЙ ПОВЕРХНОСТИ ХВОСТОВИКА И ГНЕЗДА

ТУРБОМАШИНА И ТУРБИННАЯ УСТАНОВКА

... 1. Турбомашина (10, 210, 310), оснащенная ротором (10R, 110R) и статором (10S), содержащая часть (20) для протекания текучей среды, выполненную с обеспечением возможности энергообмена между проходящей через нее текучей средой и ротором (10R, 110R), имеющим, по меньшей мере, одно снабженное лопатками рабочее колесо (22), установленное на валу ротора; электрическую часть (50, 250, 350), выполненную с возможностью преобразования электричества в работу, и наоборот; средства (40, 42; 240, 242; 340, 342) задания радиального положения, служащие для установки положения ротора в радиальном направлении; бесконтактное устройство (38) осевой балансировки, расположенное на снабженном лопатками рабочем колесе, обеспечивающее осевую балансировку ротора (10R, 110R) при высокой скорости, отличающаяся тем, что дополнительно содержит упорный подшипник (36, 136), отличный от средств (40, 42; 140, 142) задания радиального положения, который обеспечивает осевую балансировку ротора при низкой скорости и не имеет ...

СИСТЕМА И УСТРОЙСТВО РОТОРА ТУРБИНЫ

... 1. Сегментированный ротор (28) турбины, имеющий множество рядов (52) лопаток (48) турбины, по меньшей мере один сегмент (30) ротора из множества сегментов (30) ротора сегментированного ротора (28) турбины содержит кольцо (36)(38)(40), расположенное вокруг по периферии и имеющее ось (57), по существу, параллельную центральной оси (56) ротора (28), причем кольцо (36)(38)(40) образует полость (45)(46)(47), расположенную в его центре, и имеет внешнюю поверхность (39), поддерживающую по меньшей мере один ряд (52) из множества рядов (52) лопаток (48) турбины. ! 2. Ротор по п.1, в котором внешняя поверхность (39) кольца (36)(38)(40) поддерживает более одного ряда (52) из множества рядов (52) лопаток (48) турбины. ! 3. Ротор по п.1, в котором по меньшей мере один сегмент (30) ротора из множества рядов (30) ротора содержит участок (144) перегородки, имеющий первый конец (145) и второй конец (147), причем первый конец (145) расположен вблизи центральной оси (56) ротора (28) и фланцевый участок (152 ...

ЦЕНТРОБЕЖНЫЙ НАСОС, В ЧАСТНОСТИ, ДЛЯ ПИТАНИЯ РАКЕТНЫХ ДВИГАТЕЛЕЙ

ТУРБОМАШИНА, СОДЕРЖАЩАЯ КОЖУХ ВАЛА, И СООТВЕТСТВУЮЩАЯ ТРУБА КОЖУХА

КОЛЬЦЕВОЙ МАТЕРИАЛ ДЛЯ ИЗГОТОВЛЕНИЯ КОЛЬЦЕВОГО ФОРМОВАННОГО ИЗДЕЛИЯ

Турбомашинный компонент со средством сигнализации, турбомашина и способ усовершенствования турбомашинного компонента

ДВИГАТЕЛЬ

КРЕПЛЕНИЕ ТУРБИННОЙ ЛОПАТКИ ДЛЯ ТУРБОМАШИНЫ

... 1. Крепление турбинной лопатки, содержащее хвостовик (1) лопатки и перо лопатки, и канавку (18) для лопатки, при этом хвостовик (1) лопатки расположен в канавке (18) для лопатки,при этом хвостовик (1) лопатки содержит, по меньшей мере, два крепежных зубца (5), которые предназначены для введения в соответствующие выемки в роторе,при этом хвостовик (1) лопатки имеет расположенную на стороне конца в направлении оси вращения ротора вершину (12) хвостовика лопатки,при этом хвостовик (1) лопатки имеет, по меньшей мере, два расположенных друг за другом вдоль направленной к вершине (12) хвостовика лопатки длины крепежных зубца (5),отличающееся тем, что высота (Н) крепежных зубцов (5) увеличивается к вершине (12) хвостовика лопатки.2. Крепление турбинной лопатки по п.1, в котором хвостовик (1) лопатки выполнен в виде хвостовика в форме елочки.3. Крепление турбинной лопатки по п.1, в котором крепежные зубцы (5) имеют вершину (7) крепежного зубца, и вершины (7) крепежных зубцов расположены по существу ...

СПОСОБ ОЧИСТКИ И ЗАЧИСТКИ ЛОПАТКИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ ПОСРЕДСТВОМ ИМПУЛЬСНОГО ЛАЗЕРА

... 1. Способ очистки и зачистки лопатки (1) газотурбинного двигателя, содержащей тело (13) из сверхсплава, покрытое покрытием (10), способ, согласно которому покрытие (10) лопатки (1), по меньшей мере, частично обрабатывают посредством импульсного лазера (3), при этом определяют параметры, по меньшей мере, скорости (V) подачи импульсного лазера (3) и частоты (F) импульсов импульсного лазера (3) так, чтобы обработанная поверхность лопатки (1) имела шероховатость от 4 мкм до 10 мкм.2. Способ по п.1, при котором, когда покрытие содержит по меньшей мере один внешний керамический слой (11), определяют параметры импульсного лазера (3) так, чтобы обрабатывать только внешний керамический слой (11).3. Способ по п.1, при котором, когда покрытие содержит по меньшей мере один внешний керамический слой (11) и один металлический слой (12), расположенный между телом (13) из сверхсплава и керамическим слоем (11), определяют параметры импульсного лазера так, чтобы обрабатывать только внешний керамический слой ...

СПОСОБ ИЗГОТОВЛЕНИЯ МОНОБЛОЧНОЙ ДЕТАЛИ ДЛЯ ТУРБОМАШИНЫ ПРИ ПОМОЩИ ДИФФУЗИОННОЙ СВАРКИ

... 1. Способ изготовления диффузионной сваркой моноблочной детали для турбомашины, содержащий этапы, на которых:- выполняют вокруг оправки (12) заготовку (Е) детали, содержащую, по меньшей мере, один слой металлических проволок,- подвергают заготовку горячему изостатическому прессованию для получения моноблочной детали,- и, в случае необходимости, эту деталь подвергают механической обработке,отличающийся тем, что слой металлических проволок заготовки формируют из независимых колец (10), которые надевают и укладывают на оправку.2. Способ по п.1, отличающийся тем, что:- этап выполнения заготовки (Е) включает в себя выполнение нескольких кольцевых коаксиальных и наложенных друг на друга слоев металлических проволок,- каждый слой металлических проволок заготовки формируют из независимых колец (10), которые надевают и укладывают на заготовке.3. Способ по п.1, отличающийся тем, что кольца (10) имеют круглую или не круглую.4. Способ по п.1, отличающийся тем, что предварительно формируют кольца (10 ...

Gasturbinentriebwerk mit Ausgleichscheiben in dem Rotor des Hochdruckverdichter und Verfahren zur Herstellung

VERFAHREN ZUR HERSTELLUNG VON TURBINENRADSCHEIBEN MIT OERTLICH HOHEN DRUCKEIGENSPANNUNGEN IN DER NABENBOHRUNG.

Laufschaufelbaugruppe mit ring- oder scheibenförmigem Schaufelträger und radial innenliegender Versteifungsstruktur

Die Erfindung betrifft insbesondere eine Laufschaufelbaugruppe (2a, 2b) für ein Triebwerk (T), mit einem ring- oder scheibenförmigen Schaufelträger (23, 24) mit mehreren Laufschaufeln (20, 21), die entlang einer Kreislinie um eine Mittelachse (M) der Laufschaufelbaugruppe (2a, 2b) vorgesehen sind, wobei – der Schaufelträger (23, 24) einen sich bezüglich der Laufschaufeln (20, 21) radial nach innen in Richtung der Mittelachse (M) erstreckenden Trägerabschnitt (230, 240) aufweist, – der Trägerabschnitt (230, 240) einen Verbindungsbereich (231, 241) umfasst, an dem eine Versteifungsstruktur (5a, 5b) mit mindestens zwei, ersten und zweiten Versteifungselementen (50, 51) festgelegt ist, und – das erste Versteifungselement (50) an einer ersten Stirnseite des Schaufelträgers (23, 24) angeordnet ist und das zweite Versteifungselemente (51) an einer der ersten Stirnseite abgewandten zweiten Stirnseite angeordnet ist. Gemäß einem ersten Erfindungsaspekt sind die ersten und zweiten Versteifungselemente ...

Verfahren zur Herstellung metallischer Bauteile

Verfahren zum Herstellen von Turbinenwellen für Energiemaschinen

Die Erfindung betrifft ein Verfahren zum Herstellen von Turbinenwellen aus Stahl und Nickel- oder Cobaltbasislegierung für Energiemaschinen für Gas- und Dampfkraftwerke. Hierbei wird ein zylindrischer Einsatz (14) bestimmter Länge aus einer Nickel- oder Cobaltbasislegierung senkrecht ausgerichtet in eine Kokille (10) gehängt und in vorgewärmtem Zustand mit seinem unteren Ende und einem bestimmten Teil seiner Länge in eine in die Kokille (10) eingeleitete Stahlschmelze (16) eingetaucht. Nach dem Erstarren der Stahlschmelze (16) wird der Werkstoffverbund-Rohblock (13) einer Warmumformung durch Freiformschmieden unterzogen, und anschließend wird der den Kern aus Nickel- oder Cobaltbasislegierung umgebende Mantel aus Stahl einschließlich des Mischbereiches der beiden Werkstoffe wenigstens teilweise abgedreht.

Legierung auf Nickelbasis für einen Turbinenrotor einer Dampfturbine und Turbinenrotor einer Dampfturbine

Eine Legierung auf Ni-Basis für einen Turbinenrotor einer Dampfturbine, die in Gew.% enthält: C: 0,01 bis 0,15, Cr: 15 bis 28, Co: 10 bis 15, Mo: 8 bis 12, A1: 1,5 bis 2, Ti: 0,1 bis 0,6, B: 0,001 bis 0,006, Re: 0,5 bis 3 und Rest Ni und unvermeidbare Verunreinigungen.

Geared turbomachine

A geared turbomachine comprises a gear unit 11 with a drive unit 12 such as a steam turbine, and at least two geared compressors 13, 14. There is a large central gear 17 mounted on a main shaft 18, and at least two pinion gears 21, 23 meshing with the main gear 17 and mounted on pinion shafts 22, 24. The drive unit 12 is coupled to a first pinion shaft 22 via a clutch 29, and a main compressor 13 is coupled to the opposite end of the first pinion shaft 22 via a clutch 30. At least one further compressor 14 is fixedly coupled to at least one further pinion shaft 24. The main compressor is therefore coupled to the drive unit without any gearing, which reduces mechanical losses.

Bleed valve

Magnetic sensor system for detecting abnormal movement in a gas turbine shaft

Carriers for turbine components

Gas turbine engine

Gas turbine engine

Connection of rotatable parts

ROTOR STAGE IN A TURBOMACHINE

A rotor stage disposed within an annular fluid flowpath in a turbomachine is disclosed. The rotor stage includes outer and inner rings and a plurality of first and second airfoils. The outer and inner rings define flowpath surfaces for said flowpath. The first and second airfoils extend between the rings for transferring energy between the fluid and the rotor stage. At least one of the first airfoils surrounds means for transmitting energy across the flowpath.

A method of making a fibre reinforced metal component

Ring and channel arrangement for joining components

A retaining arrangement for joining together two components such as a rim coverplate 10 and a rotor disc 12 in a gas turbine engine, comprises a channel 54 formed by respective formations 26, 52 on the disc 12 and coverplate 10. An annular ring member 66 is fed into the channel 54 which prevents separation of the coverplate 10 and disc 12. Engageable abutment formations 18, 46 are provided respectively on the disc 12 and coverplate 10, to prevent separation and preferably, pivotal movement. The ring member 66 may be formed in a plurality of sections and an axial opening 60 may be provided to permit the ring member to be fed into the channel 54. Formations such as holes may be provided on the ends or along the length of the ring member 66 to assist in sliding it through the channel 54.

BLADE CARRYING MEANS OF A CONTRA-ROTATING PROPULSOR

Blade carrying means for variable pitch propulsor blades of a gas turbine engine are disclosed. The blade carrying means comprise dual, axially positioned rings and a plurality of generally cylindrical bearing journals supported between the rings. Each of the journals has a radially outer and inner edge and is adapted to support a single propulsor blade. The blade carrying means also comprise stiffening means, such as a bulkhead attached to the inner edge, for preventing distortion of the journal inner edge.

System for attaching a turbojet engine spinner

Disclosed is an upstream rotor of a turbomachine comprising a spinner 2 which is removably attached to the upstream end of the rotor 1 by attachment means comprising a dog clutch 3, 9, 10 and rotation-preventing means which lock the spinner 2 in place to prevent rotation of the spinner 2 relative to the rotor 1. The rotation-preventing means comprise pegs 13 which are resiliently urged to the locked position by elastically deformable means such as spring 17.

A shroud segment retainer

Electric rotor fit onto a turbomachine shaft

By relieving the shaft of an electronically-controlled turbocharger (ECT) in a central region of where a rotor of an electric machine couples with the shaft eases assembly of the electric machine onto the shaft. On either side of the relieved section, the fit between the shaft and the rotor may be a slip fit or an interference fit. Alternatively, the rotor is relieved in a central section. In some embodiments, the shaft is welded to the rotor. In yet other embodiments, the outside of the shaft and the inside of the rotor are threaded with a nut or a pin to secure the shaft to the rotor or the rotor itself has threads to engage with threads on the shaft. Such arrangements ease assembly and allow adjustment of dynamic characteristics of the rotor system.

Methods and apparatus to optimize steam turbine ramp rates

A gas turbine engine having sequential combustion

Assembly for controlling variable pitch blades

An assembly for the control of variable pitch blades of a turbo-engine of an aircraft. The system comprises a control ring 10 which surrounds a casing 8 of the turbo-engine which is arranged around an axis x of the turbo-engine, the ring being connected by rods 12 to the blades. A device 14 is included for driving the control ring rotationally around the axis x and translationally parallel to the axis x. The device comprises an actuator 30, which is a cylinder having a fixed part 30a and a movable part 30b, the movable part being a grooved rod and moving parallel to the axis x and being engagement with pivot connections 33. The pivot connections rotate about a radial axis 35a and act on the radial shaft 37 which passes through a clevis 39 fixed with the control ring to rotate with is about axis x. The movement of the actuator parallel to axis x acts on the pitch of the blades by actuating pivot connections 33, causing rotation of the radial shaft, causing rotation of the connecting rods ...

Turbine and a controller thereof

Fan disc

Turbine engine rotor shaft comprising an improved heat exchange surface

Undulating stator for reducing the noise produced by interaction with a rotor

Disclosed is an assembly comprising at least one stator placed radially in a flow which passes through one or more rotors which share the same axis of rotation, the stator having a leading edge 11 and a trailing edge 12 connected by a lower face 10 and an upper face 9. At least one of the faces has radial undulations which extend axially from the leading edge to the trailing edge and have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimetre on at least part of the axial length of the stator. In use, pressure fluctuations with oscillations of the temporal phase are created on the at least one undulating surface and the undulations have azimuth maximums and/or minimums in the vicinity of the zero mean dephasing regions for the pressure on the undulating face. Also disclosed is a turbine engine comprising the assembly and a method for reducing noise in an assembly.

A weld stub arrangement and a method of using the arrangement to make an article

ROTOR OF A TURBOMACHINE

Impeller for turbocharger, method for manufacturing same, turbocharger, and turbo unit

An impeller (50) for a turbocharger comprises a hub section (51) and a plurality of fin sections (52, 53). The hub section (51) is roughly in the shape of a truncated cone and is formed such that the hub section diameter increases gradually in the direction of the axis of rotation (ZC). The fin sections (52, 53) are formed on the surface of the hub section (51) and impel, radially outward, a fluid that has flowed in from the direction of the axis of rotation (ZC). A plurality of groove sections are formed in the surface of the hub section (51) and the surfaces of the fin sections (52, 53). The plurality of groove sections formed in the surfaces of the fin sections (52, 53) are formed in the direction in which the fluid that has flowed in from the direction of the axis of rotation (ZC) flows radially outward when the impeller rotates. Ridge sections that project from the groove sections are formed between neighboring groove sections. The ridge sections in the region near the axis of rotation ...

METHOD AND APPARATUS FOR PROVIDING ROTOR DISCS

COMPONENTS AND PROCESSES OF PRODUCING COMPONENTS WITH REGIONS HAVING DIFFERENT GRAIN STRUCTURES

Processes for fabricating components (10) to have two or more regions (14, 12) with different grain structures, and components (10) produced by such processes. The processes entail performing at least one forging step on a preform (20) to produce a profile (24) having at least a first portion (28) corresponding to the first region (14) of the component (10). The preform (20) is formed of a precipitation-strengthened alloy having a solvus temperature, and the at least one forging step comprises a nonfinal forging step performed at a first strain rate and at a first subsolvus temperature that is below the solvus temperature of the alloy. A subsequent forging step is performed on the profile (24) to produce a final profile (26) comprising the first portion (28) and a second portion (32) corresponding to the second region (12) of the component (10). The subsequent forging step is performed at a strain rate and at a subsequent subsolvus temperature, wherein at least one of the subsequent strain ...

SYSTEM AND METHODS FOR SELECTIVE CLEANING OF TURBINE ENGINE COMPONENTS

System for selectively contacting a cleaning composition with a surface of a turbine engine component is presented. The system includes a cleaning apparatus and a manifold assembly. The cleaning apparatus includes an upper portion and a lower portion defining a cleaning chamber configured to allow selective contact between the cleaning composition and a surface of the first portion of the turbine engine component. The upper portion includes a plurality of fill holes in fluid communication with the cleaning chamber, and the lower portion includes a plurality of drain holes in fluid communication with the cleaning chamber. The manifold assembly is configured to selectively circulate the cleaning composition from a reservoir to the cleaning chamber via the plurality of fill holes, and recirculate the cleaning composition from the cleaning chamber to the reservoir via the plurality of drain holes. Methods for selectively cleaning a turbine engine component is also presented ...

A ROTOR FOR AN ELECTRICITY GENERATOR

A rotor (10) for a hydro-powered electricity generator. The rotor (10) includes a hub (12) and a plurality of blades (16). The hub (12) has a circular cross sectional shape and a longitudinal rotational axis (14). The plurality of blades (16) each have a proximal root (16a) and a distal tip (16b). Each of the blade roots (16a) are mounted to the hub (12) at the widest part thereof (D1). The ratio between the diameter of the tips (16b) of the blades to the diameter of the widest part (D1) of the hub (12) is less than about 2:1.

TURBINE ASSEMBLY MAINTENANCE METHODS

The present invention is directed to in situ methods for maintaining turbine assemblies (10). One such method includes: disposing a maintenance apparatus (20) on the rotor (12); positioning the maintenance apparatus proximate to the damaged region (40) by rotating the rotor; and repairing the damaged region by operating a repair tool (22) disposed on the apparatus. Another method includes: disposing a maintenance apparatus on the stator; positioning the damaged region proximate to the maintenance apparatus by rotating the rotor; and repairing the damaged region by operating a repair tool disposed on the apparatus.

FAN DISK FOR A JET ENGINE AND JET ENGINE

L'invention concerne un disque de soufflante (10) pour un turboréacteur (1) dans lequel circule un flux de gaz dans un sens de circulation, caractérisé en ce qu'il présente une section radiale en forme d'épingle comprenant: une première branche (12), adaptée pour être fixée à un arbre d'entraînement (20) du turboréacteur (1), une deuxième branche (16), s'étendant en regard de la première branche (12) et adaptée pour supporter une pluralité d'aubes de soufflante (3a), et une paroi de jonction courbe (14), s'étendant entre la première branche (12) et la deuxième banche (16).

VARIABLE PITCH FAN BLADE RETENTION SYSTEM

A variable pitch fan for a gas turbine engine includes a fan blade (40) defining a pitch axis (P) and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment. A key is positioned at least partially in a key slot (128) defined in a base (126) of the trunnion mechanism, and further positioned adjacent to a support member of the disk segment. The key defines a first contact line (130) between the key and the key slot (128) and a second contact line (132) between the key and the support member. The first and second contact lines (132) respectively define a first contact reference line (134) in a second contact reference line (136). The first and second contact reference lines (134, 136) define an angle with the pitch axis (P) of the fan blade (40) greater than zero degrees and less than ninety degrees.

FULL HOOP BLADE TRACK WITH FLANGED SEGMENTS

A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

INTERSHAFT INTEGRATED SEAL AND LOCK-NUT

An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut.

SHROUD ASSEMBLY AND SHROUD FOR GAS TURBINE ENGINE

Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.

HYDRAULIC POWER RECOVERY TURBINE WITH INTEGRATED BEARING-CLUTCH HOUSING

The hydraulic power recovery turbine comprises a casing and a rotor arranged for rotation in the casing. The rotor comprises a rotor shaft (43) and at least one impeller mounted on the rotor shaft. The rotor shaft is supported by bearings (45) arranged in respective bearing housings (25). The drive-end bearing housing (25) further houses a clutch (51), which connects the rotor shaft (43) to an output shaft (29) of the hydraulic power recovery turbine (23) extending from the drive-end bearing housing.

TURBINE ASSEMBLY OF AN AIRCRAFT TURBINE ENGINE

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

SHROUD HOUSING SUPPORTED BY VANE SEGMENTS

A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.

SHAFT SHEAR DETECTION IN GAS TURBINE ENGINES

There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine. The method comprises determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a shaft of a second spool of the engine different from the first spool, the set of threshold values varying throughout a flight envelope, the detection threshold defining, for each spool speed value, at least one load transfer value beyond which a shaft event is detected. Operation values of the spool speed and the load transfer are obtained during operation of the engine, and the operation values are compared to the detection threshold. The shaft event is detected when the operation values are below the detection threshold.

METHOD FOR PRODUCING CAVITIES FOR A TURBOMACHINE DISK

L'invention concerne un procédé de réalisation d'une pluralité d'alvéoles (50) dans un disque (52) de turbomachine, lesdites alvéoles (50) s'étendant entre une première surface latérale (53) et une deuxième surface latérale (54) d'un disque (52) de turbomachine, lesdites première surface (53) et deuxième surface (54) s'étendant orthogonalement à un axe (X) du disque (52), le procédé comportant des étapes suivantes : - Positionner un anneau (55) en vis-à-vis de la première surface (53) de sorte à centrer l'anneau (55) sur l'axe (X) du disque (52), ledit anneau (55) comportant une périphérie intérieure (57) comprenant une pluralité de saillies (58) de formes complémentaires aux formes des alvéoles (50) à réaliser - Mettre en circulation un électrolyte à proximité des saillies (58) de l'anneau (55) - Activer une première translation de l'anneau (55) le long de l'axe (X) du disque (52) en direction de la deuxième surface - Activer une rotation du disque (52) autour de l'axe (X) du disque (52 ...

TURBOMACHINE WITH AN OUTER SEALING AND USE OF THE TURBOMACHINE

Subject matter of the invention is turbomachine which comprises a stator with at least one stator component and a rotor with at least one rotatable rotor component. The stator component defines at least one wall of a cooling cavity with a high pressure area of the turbomachine and the stator and the rotor defining a working media fluid path, the working media fluid path being in a low pressure area of the turbomachine, whereby a pressure of the low pressure area is lower than a pressure of the high pressure area and the low pressure area and the high pressure area are separated by a sealing ring, the sealing ring being an annular ring with a diaphragm at an inner end of the annular ring. Preferably, the turbomachine is a gas turbine.

TURBINE WHEEL WITH AN AXIAL RETENTION SYSTEM FOR VANES

La roue de turbine comprend : une pluralité d'aubes (20), un rotor (10) avec un disque (12) à la périphérie duquel sont montées les aubes, chaque aube ayant une pale (22) avec un pied solidaire d'une plate-forme (24) portant une attache (26) engagée dans un logement s'ouvrant à la périphérie du disque et s'étendant axialement entre deux faces opposées du disque, les logements étant séparés les uns des autres par des parties du disque formant des dents (16), et un flasque (40) de retenue axiale des aubes sur le disque comprenant un flasque de retenue (40) situé sur un côté du disque. De l'autre côté du disque, les dents du disque présentent des reliefs (18) qui font saillie radialement et forment des butées venant en appui axial sur des reliefs (28) qui sont formés sous les plates-formes des aubes en retrait par rapport aux faces latérales des attaches situées du deuxième côté du disque, et les faces latérales des attaches des aubes et du disque à sa périphérie sont situées sensiblement ...

METHOD FOR REPAIRING A ROTOR SYSTEM OF A TURBOMACHINE, ANNULAR ELEMENT FOR A ROTOR SYSTEM OF A TURBOMACHINE, AND ROTOR SYSTEM FOR A TURBOMACHINE

The present invention provides a method for repairing a rotor system (2) of a turbomachine, having a rotor (4) which has a groove (26) extending in the circumferential direction (58) of the rotor for accommodating an annular section (18; 28). The method has the following steps: chamfering a notch (40) in the groove (26); introducing a recess (44) into the groove (26); and inserting the annular section (18; 28) into the groove (26). At least one engagement element (48; 49) formed on the annular section (18; 28) engages in the recess (44) in order to form a lock against rotation in the circumferential direction (58).

METHOD FOR CLEANING AND STRIPPING A TURBOSHAFT ENGINE BLADE USING A PULSED LASER

Un procédé de nettoyage d'une aube (1) de turbomoteur comportant un corps en superalliage recouvert d'un revêtement, procédé dans lequel on usine au moins partiellement le revêtement de l'aube (1) au moyen d'un laser impulsionnel (3), au moins la vitesse d'avance du laser impulsionnel (3) et la fréquence d'impulsion du laser impulsionnel (3) étant paramétrés pour que la surface usinée de l'aube (1) présente une rugosité comprise entre 4 µm et 10 µm.

REDUCED-STRESS COMPRESSOR BLISK FLOWPATH

A gas turbine engine rotor assembly including a rotor (12) having a radial ly outer rim (18) with an outer surface (204) shaped to reduce circumferential rim stress concentration between each blade (24) and the rim. Additionally, the shape o f the outer surface directs air flow away from an interface between a blade and th e rim to reduce aerodynamic performance losses between the rim and blades. In an exemplary embodiment, the outer surface of the rim has a concave shape (210) between adjacent blades with apexes located at interfaces between the blades and the rim. ...

Schaufelrad für aussen beaufschlagte Turbinen und Pumpen

Verfahren zur Verminderung der Beanspruchung rotierender Scheiben.

Ringturbinengebläse

Magnetische Formvorrichtung

Strömungsmaschine mit im mittleren Bereich des Laufrades radialer und axialer, im äusseren weitgehend angenähert tangentialer Strömungsrichtung

System with a steam turbine, the coverings has a slide-ring seal with locally compliant hydrodynamic.

System, aufweisend eine Dampfturbine mit Gleitringdichtung (100) bestehend aus Rotorring (108) und Statorring (106), der eingerichtet ist, um um einen Rotor einer Turbine angeordnet zu werden, wobei der Statorring (106) mehrere Beläge (200) aufweist, die sich von einer Dichtungsfläche des Statorrings (106) aus erstrecken, wobei jeder der mehreren Beläge (200) eingerichtet ist, um mit dem Rotorring (108) verbunden zu sein.

Procedure for the Rekonditionierung of a rotor of a fluid-flow machine.

Die Erfindung betrifft ein Verfahren zur Rekonditionierung eines Rotors (10) einer Strömungsmaschine, welcher mit umlaufenden Rotornuten (12) zur Aufnahme von Laufschaufeln (13) ausgestattet ist, die in den Rotornuten (12) durch Zwischenstücke voneinander beabstandet gehalten werden. Das Verfahren umfasst die folgenden Schritte: a) Entfernen der Laufschaufeln (13) und Zwischenstücke aus den aufzuarbeitenden Rotornuten (12); b) Ausdrehen der freiliegenden Rotornuten (12) bei gleichzeitiger Verbreiterung der Rotornuten (12), um schadhaftes Material zu entfernen; c) Einbringen von wenigstens jeweils einer umlaufenden seitlichen Nut (21) zur Aufnahme eines Füllstücks in die Rotornuten (12), derart, dass ein Spalt zwischen Laufschaufeln (13) und ausgedrehten Rotornuten (12) durch das Füllstück ausgefüllt wird; d) Bereitstellen von neuen Zwischenstücken (15´), welche an die ausgedrehten Rotornuten (12) angepasst sind und den eingebrachten seitlichen Nuten (21) angepasste Ausnehmungen (17) aufweisen ...

GRADATES AN AXIAL-FLOW STEAM TURBINE.

Procedure for the repair of a run disk for a gas turbine as well as run disk.

Ausführungsformen der Erfindung stellen Verfahren und eine Vorrichtung zur Reparatur einer Laufscheibe für eine Gasturbine bereit. In einer Ausführungsform wird ein Verfahren zur Reparatur einer Laufscheibe für eine Gasturbine bereitgestellt, wobei die Laufscheibe eine Basis und mindestens einen Schwalbenschwanzschlitz zwischen einem Paar Schwalbenschwanzwänden aufweist. Das Verfahren umfasst das Erkennen eines oder mehrerer Risse auf der Basis der Laufscheibe und das Entfernen eines oder mehrerer Risse durch Vorsehen einer oder mehrerer Hohlkehlen auf der Basis der Laufscheibe. Ferner umfasst das Verfahren das Vorsehen eines oder mehrerer konischer Ausschnitte auf der Basis der Laufscheibe zwischen dem Paar Schwalbenschwanzwände mindestens eines Schwalbenschwanzschlitzes.

Procedure for the repair of a run disk for a gas turbine and a run disk.

Die Erfindung betrifft ein Verfahren zur Reparatur einer Laufscheibe wobei die Laufscheibe, eine Basis und mindestens einen Schwalbenschwanzschlitz zwischen einem Paar Schwalbenschwanzwänden aufweist. Das Verfahren umfasst das Erkennen (502) eines oder mehrerer Risse auf der Basis der Laufscheibe und das Entfernen eines oder mehrerer Risse durch Vorsehen (504) einer oder mehrerer Hohlkehlen auf der Basis der Laufscheibe. Ferner umfasst das Verfahren das Vorsehen (506) eines oder mehrerer konischer Ausschnitte auf der Basis der Laufscheibe zwischen dem Paar Schwalbenschwanzwände mindestens eines Schwalbenschwanzschlitzes.

Arrangement for fastening turbine blades.

Die Erfindung betrifft eine Anordnung (10) zum Befestigen von Turbinenschaufeln an einer Turbinenscheibe einer Turbine, insbesondere einer Gasturbine, bei der für eine Turbinenschaufel (14) an der Turbinenscheibe (12) eine zumindest annähernd parallel zur Rotationsachse der Turbine verlaufende axiale Profilnut (16) vorgesehen ist, in welche ein im Querschnitt an den Profilquerschnitt der Profilnut (16) angepasster Fuss (18) der jeweiligen Turbinenschaufel (14) einzuführen ist, und bei der für die Turbinenschaufel (14) ein Befestigungselement (32) vorgesehen ist, mit welchem der in die Profilnut (16) eingeführte Fuss (18) der Turbinenschaufel (14) in axialer Richtung gesichert ist. Erfindungsgemäss ist das Befestigungselement (32) durch Verrasten an der Turbinenscheibe (12) befestigt und den Fuss (18) axial sichert. Des Weiteren betrifft die Erfindung ein Befestigungselement für eine derartige Anordnung.

Arrangement for fastening a turbine blade.

Die Erfindung betrifft eine Anordnung (10) zum Befestigen einer Turbinenschaufel an einer Turbinenscheibe einer Turbine, insbesondere einer Gasturbine, bei der für eine Turbinenschaufel (14) an der Turbinenscheibe (12) eine zumindest annähernd parallel zur Rotationsachse der Turbine verlaufende axiale Profilnut (16) vorgesehen ist, in welche ein im Querschnitt an den Profilquerschnitt der Profilnut (16) angepasster Fuss (18) der jeweiligen Turbinenschaufel (14) einzuführen ist, und bei der für die Turbinenschaufel (14) ein Befestigungselement (32) vorgesehen ist, mit welchem der in die Profilnut (16) eingeführte Fuss (18) der Turbinenschaufel (14) in axialer Richtung gesichert ist. Erfindungsgemäss ist das Befestigungselement (32) durch Verrasten an der Turbinenscheibe (12) befestigt und sichert den Fuss (18) axial. Des Weiteren betrifft die Erfindung ein Befestigungselement für eine derartige Anordnung.

Transmission turbomachine.

Getriebeturbomaschine (10), die ein Getriebe (11), mindestens ein Antriebsaggregat (12) und mindestens zwei Abtriebsaggregate (13) aufweist, die zu einem Maschinenstrang integriert sind; wobei das Getriebe (11) ein zentrales Grossrad mit einer Grossradwelle (18) und mindestens zwei in das Grossrad kämmende Ritzel mit Ritzelwellen (22, 24) umfasst; wobei das Antriebsaggregat (12) mit einer ersten Ritzelwelle (22) der Ritzelwellen des Getriebes (11) auf einer Seite desselben über eine erste Kupplung (29) gekoppelt ist; wobei ein erstes der Abtriebsaggregate (13) als Hauptkompressor ausgebildet ist, in welchem unter Nutzung der vom Antriebsaggregat (12) bereitgestellten mechanischen Antriebsleistung ein erstes Prozessgas verdichtbar ist, wobei das erste Abtriebsaggregat (13) mit der ersten Ritzelwelle (22) des Getriebes (11) auf der gegenüberliegenden Seite desselben über eine zweite Kupplung (30) derart gekoppelt ist, dass das erste Abtriebsaggregat (13) bei geschlossener erster Kupplung ...

transmission turbomachine.

Getriebeturbomaschine (10), die ein Getriebe (11), mindestens ein Antriebsaggregat (12), und mindestens zwei Abtriebsaggregate (13, 14) aufweist, die zu einem Maschinenstrang integriert sind; wobei das Getriebe (11) ein zentrales Grossrad mit einer Grossradwelle (18) und mindestens zwei in das Grossrad kämmende Ritzel mit mindestens zwei Ritzelwellen (22, 24) umfasst; wobei die Getriebeturbomaschine (10) ein Antriebsaggregat (12) umfasst, wobei das Antriebsaggregat (12) mit einer ersten Ritzelwelle (22) des Getriebes (11) auf einer Seite desselben über eine erste Kupplung (29) gekoppelt ist; wobei ein erstes Abtriebsaggregat (13) als Hauptkompressor ausgebildet ist, in welchem unter Nutzung der vom Antriebsaggregat (12) bereitgestellten mechanischen Antriebsleistung ein erstes Prozessgas verdichtet wird, wobei das erste Abtriebsaggregat (13) mit der ersten Ritzelwelle (22) des Getriebes (11) auf der gegenüberliegenden Seite desselben über eine zweite Kupplung (30) derart gekoppelt ist, ...

AIRCRAFT VERTICAL TAKEOFF AND LANDING

Rotor of turbine

The rotor of the steam turbine for manufacturing method

Retaining ring arrangement for a rotary assembly

A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

Steam turbine rotor, method of manufacturing the same, and steam turbine

In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates.

Thermally insulating turbine coupling

A rotor assembly, including at least one driven member, e.g., a compressor rotor, and at least one driving member, e.g., a turbine. At least one rotating thermal insulator rigidly attached to either the driven member or the driving member. A coupling feature that includes mating geometric surfaces on the driven member and the driving member, wherein the geometric surfaces are configured to allow radial sliding, relative centering, torque transmission, and axial constraint between the driven member and the driving member.

Drive mechanism for a pair of contra-rotating propellers through an epicyclic gear train

A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

Method For Balancing A Propulsive System Having Non-Hull Contra-Rotating Propellers

According to the invention, at least one of the counterweights ( 40, 40.1, 40.2, 40.3, 40.4 ) is mobile mounted on a guiding slot ( 24, 34 ) coaxial to the hub envelope ( 22, 32 ) that surrounds the hub ( 21, 31 ) of the corresponding propeller ( 2, 3 ), the movement of said mobile counterweight ( 40, 40.1, 40.2, 40., 40.4 ) along said guiding slot ( 24, 34 ) being controlled on the basis of an estimation of the possible unbalance of said propulsive system ( 1 ).

ROTOR WITH IMPROVED BALANCING FEATURES

A rotor assembly for a gas turbine engine including a circumferential array of regularly spaced apart features provided on the disk which are each configured for receiving a balancing weight. The circumferential array of features has an angular orientation relative to the circumferential array of blades such that the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent blade. 1. A rotor assembly for a gas turbine engine , the rotor assembly comprising a disk , a circumferential array of regularly spaced apart blades extending from the disk , a circumferential array of regularly spaced apart features provided on the disk and at least one balancing weight , each of the features being configured for receiving one of the at least one balancing weight , the circumferential array of features having an angular orientation relative to the circumferential array of blades such that all the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent one of the blades.2. The rotor as defined in claim 1 , wherein the features extend axially relative to the disk and are generally scallop shaped.3. The rotor as defined in claim 1 , wherein the disk includes a hub claim 1 , a radial member extending radially from the hub and connected to a platform supporting the blades claim 1 , and a flange extending radially inwardly from the platform spaced apart from the radial member claim 1 , each of the features being located on the flange.4. The rotor assembly for a gas turbine engine claim 1 , wherein the at least one balancing weight includes a plurality of balancing weights claim 1 , the balancing weights being all engaged to a respective one of the features.5. A method of locating features on a rotor assembly of a gas turbine engine claim 1 , the rotor including a rotor disk and a circumferential array of regularly spaced apart blades extending from the disk ...

ROTOR DISC AND METHOD OF BALANCING

A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life. 1. A method of manufacturing a turbomachine rotor disc , the method comprising:providing the turbomachine rotor disc with at least one generally annular appendage coaxially disposed with reference to a central rotation axis of the turbomachine rotor disc; andmachining a plurality of spaced-apart and substantially radially-extending slots in a free end of the appendage, the slots delimiting a plurality of sacrificial protrusions from which material can be removed during balancing.2. The method as defined in claim 1 , wherein the spaced-apart slots are circumferentially equally spaced on the free end of the appendage.3. The method as defined in claim 1 , wherein the turbomachine rotor disc comprises a plurality of blade receiving slots on an outer periphery thereof.4. A method for gas turbine rotor disc balancing comprising the steps of:providing a rotor disc having at least one balancing assembly provided substantially coaxially with reference a rotation axis of the rotor disc, the balancing assembly having a plurality of spaced-apart sacrificial protrusions extending between adjacent stress-relieving slots, bottoms of said adjacent slots defining a base end of the protrusions, each protrusion extending from its base end to a free end, the slots provided with a shape providing a stress concentration below a crack propagation threshold in a region of the slot bottoms;determining an imbalance to the rotor disc; and thenremedying the imbalance by ...

TURBINE

A turbine includes a rotor having at least two rotor members for rotating in a plane, the rotor members being substantially diametrically arranged and attached to an axis situated substantially transversely to the plane, and drive unit coupled to the axis, wherein the rotor members include a fluid contact member, that is hingingly connected to an arm which is attached to the axis, characterized in that the fluid contact members are adapted to hinge between a fluid-active position in which the members project transversely to the plane and a fluid-transparent position in which the members extend mainly parallel to the plane. 112711812913101453547891011121314378910. Turbine () comprising a rotor () having at least two rotor members ( ,; ,; ,; ,) for rotating in a plane () , the rotor members being substantially diametrically arranged and attached to an axis () situated substantially transversely to the plane () , and drive unit () coupled to the axis , wherein the rotor members comprise a fluid contact member ( , , ,) that is hingingly connected to an arm ( , , ,) which is attached to the axis () , characterized in that the fluid contact members ( , , , ,) are adapted to hinge between a fluid-active position in which the members project transversely to the plane and a fluid-transparent position in which the members extend mainly parallel to the plane.2789101819533. Turbine according to claim 1 , wherein the fluid contact members ( claim 1 , claim 1 , claim 1 ,) comprise a flexible material claim 1 , the contact members being with one side connected to the arms and having a free end ( claim 1 ,) claim 1 , the free end in the fluid-active position being bent away from the plane () by a fluid force having a component situated parallel to the plane claim 1 , in a first angular position of the axis () claim 1 , and being lifted away from the fluid active position to the fluid-transparent position at a second angular position of the axis ().311121314. Turbine according to ...

POWER RECOVERY DEVICE OF LIQUID PROCESSING APPARATUS

According to one embodiment, a power recovery device is used in an apparatus in which firstly pressurized raw water (FPRW) is supplied to a reverse osmosis membrane unit to extract fresh water and condensed and depressurized raw water (HPB) remains. The device recovers the energy of HPB, rises a pressure of raw water (LPF) by using the recovered energy, and adds such secondly pressurized raw water (HPF) to the FPRW. The device accommodates a fixed center shaft and a rotary member on the shaft in a housing. LPF flows into one paired chambers of the housing and radial channels of the member to push and rotate the member, and HPB is introduced into the channels through paired openings of the shaft to push out LPF as HPF from the channels and another paired chambers of the housing. 1. A power recovery device which is used in a liquid processing apparatus in which raw water as externally supplied water containing a plurality of components is supplied to a reverse osmosis membrane through a pressure raising unit and extracts a part of fresh water from the pressure raised raw water by the reverse osmosis membrane , and which supplies raw water a pressure of which is raised by using a pressure of remaining raw water from which the part of the fresh water is extracted by the reverse osmosis membrane to the reverse osmosis membrane , in addition to the pressure raised raw water from the pressure raising unit ,the power recovery device comprising:a housing having an internal space; a center shaft fixed in the internal space of the housing and having an outer circumferential surface and at least one end portion protruding outside the housing; and a rotary member accommodated in the internal space of the housing such that the rotary member is rotatable on the outer circumferential surface of the center shaft, having an inner circumferential surface opposing the outer circumferential surface of the center shaft and an outer circumferential surface positioned outside the center ...

Compressor wheel shaft with recessed portion

A turbocharger assembly includes a compressor wheel with a base surface, a nose surface, a z-plane disposed between the base surface and the nose surface and a bore extending from the base surface to the nose surface and a shaft that includes a first pilot surface disposed in the bore of the compressor wheel at a position between the z-plane and the nose surface, a second pilot surface disposed in the bore of the compressor wheel at a position between the z-plane and the base surface, and a recessed surface disposed between the first pilot surface and the second pilot surface. A nut adjustably disposed on the shaft adjacent to the nose surface can tension the shaft to apply a compressive load between the base surface and the nose surface of the compressor wheel. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

VACUUM PUMP

Provided is a vacuum pump in which no finish processing has to be carried out after shaping of a cylindrical rotor even in use of a cylindrical rotor obtained by shaping a fiber-reinforced plastic material into a cylindrical shape. The vacuum pump has a turbo-molecular pump section and a thread groove pump section. The upper end section of a cylindrical rotor, which is obtained by shaping a fiber-reinforced plastic material into a cylindrical shape, of the thread groove pump section, is joined to the lower end section of a rotor of the turbo-molecular pump section. A joining portion of the rotor of the turbo-molecular pump section and the cylindrical rotor of the thread groove pump section is disposed upstream of an exhaust passage. As a result, finish processing does not have to be carried out after shaping of the cylindrical rotor. If finish processing is performed after shaping of the cylindrical rotor a resin may be coated onto a rugged portion of the cylindrical rotor, or fibers may be helically wound at a winding angle not greater than 45 degrees. 1. A vacuum pump having a rotor such that a cylindrical rotor formed in a substantially cylindrical shape out of a fiber-reinforced composite material is joined to a rotor of another material and forming a thread groove pump or a Goethe pump , etc. ,wherein said cylindrical rotor is formed as a multilayer structure that includes hoop layers in which fibers are oriented in less than 45 degrees with respect to a circumferential direction, anda protective countermeasure is provided at an outer periphery of an outermost layer, from among said hoop layers, so as to prevent shredding fibers in the layer that constitutes said outermost layer at least at a joining portion of said cylindrical rotor.2. The vacuum pump according to claim 1 ,wherein at least at said joining portion in said cylindrical rotor, a resin layer is provided outside of said hoop layers so as to reduce irregularities in the surface of said cylindrical ...

DEVICE FOR REDUCING THE DRIVE POWER REQUIREMENTS OF A WATERCRAFT

A device is provided for reducing the drive power requirement of a watercraft includes a fore-nozzle, wherein at least one outer fin projects outwards from the fore-nozzle. 1. A device for reducing the drive power requirement of a watercraft comprising: a fore-nozzle , characterized in that at least one outer fin projects outwards from the fore-nozzle.2. The device according to claim 1 , characterized in that a first end of the at least one outer fin is fastened to the fore-nozzle and a second end of the at least one outer fin is configured as a free end.3. The device according to claim 1 , characterized in that at least one inner fin is disposed inside the fore-nozzle claim 1 , wherein a first end of the inner fin is fastened to an inner wall surface of the fore-nozzle.4. The device according to claim 3 , characterized in that the at least one inner fin is fastened with a second end to a shaft bearing configured for mounting of a propeller shaft of a propeller of the watercraft.54. The device according to any one of - claims 1 , characterized in claims 1 , that the at least one outer fin or the at least one inner fin is disposed radially to a longitudinal axis of the fore-nozzle or radially to a propeller axis of a propeller of the watercraft.64. The device according to any one of - claims 1 , characterized in claims 1 , that a plurality of outer fins are provided claims 1 , wherein on the propeller upwards-turning side of the fore-nozzle more outer fins are provided than on the propeller downwards-turning side of the fore-nozzle or that the outer fins are arranged in such a manner that they form an asymmetric outer fin system.7. The device according to claim 3 , characterized in that a plurality of inner fins are provided claim 3 , wherein on the propeller upwards-turning side of the fore-nozzle more inner fins are provided than on the propeller downwards-turning side of the fore-nozzle or that the inner fins are arranged in such a manner that they form an ...

Runner for Direct-connected Low-speed Small Mixed Flow Type Water Turbine Applied in Hydrodynamic Energy-saving Cooling Tower

The invention relates to a runner for a direct-connected low-speed small mixed flow type water turbine applied in a hydrodynamic energy-saving cooling tower, which comprises an upper crown ( 1 ), a lower ring ( 3 ) and curved surface blades ( 2 ) mounted between the upper crown ( 1 ) and the lower ring ( 3 ), and is characterized in that the ratio of the height h of water inlet edge ( 4 ) of each blade ( 2 ) to the diameter D 1 corresponding to the water inlet edge ( 4 ) is 0.18-0.22, the ratio of the overall height H of the blades ( 2 ) to the diameter D 1 is 0.35-0.42, the ratio of the diameter D 2 corresponding to the intersection point A of each water outlet edge ( 4 ) and the lower ring ( 3 ) to the diameter D 1 is 0.4-0.6, the ratio of the diameter D 3 corresponding to the intersection point B of each water outlet edge ( 4 ) and the upper crown to the diameter D 1 is 0.3-0.45, the ratio of the diameter D 4 in the position of a water drain round platform on the upper crown ( 1 ) to the diameter D 1 is 0.1-0.2, and the relationship between the diameter D1 and the rotational speed of cooling fan blades is D 1= n11×√{square root over (H)}/n. The invention has the advantages of simple structure, convenience in design and mounting and high energy conversion efficiency.

AVOIDANCE OF TORSIONAL EXCITATIONS IN CONVERTER-CONTROLLED COMPRESSOR RUNS

A machine has a rotor and includes a converter-controlled drive and a working machine, wherein the drive and the working machine are connected such that a torque is transmitted. A frequency converter is electrically connected to the drive. The frequency converter is embodied such that in a Campbell diagram intersection points are based on the natural torsional frequency of the rotor and V-shaped symmetrical straight lines of the inter-harmonic exciter frequency for output frequencies. The output frequencies are grouped into a plurality of concentration ranges based upon a rotational speed of the machine, wherein each concentration range comprises output frequencies which are close to one another and which respectively have a common output point on the abscissa of the Campbell diagram. Each concentration range defines a blocking range, wherein the machine has an operating rotational speed range which lies outside the blocking ranges. 112.-. (canceled)13. A machine , comprising:a rotor,a converter-controlled drive with a variable rotational frequency,a working machine, wherein the drive and the working machine are connected to one another such that a torque is transmitted,a frequency converter which is electrically connected to the drive and converts input frequencies to output frequencies, the natural torsional frequency of the rotor and', 'V-shaped symmetrical straight lines of the inter-harmonic exciter frequency for the output frequencies,, 'wherein the frequency converter is embodied such that in a Campbell diagram, relating to the machine, intersection points result from'}wherein the output frequencies are grouped into a plurality of concentration ranges based upon a rotational speed of the machine,wherein each concentration range comprises output frequencies which are close to one another and which respectively have a common output point on the abscissa of the Campbell diagram, a lowest and/or second lowest and/or third lowest natural torsional frequency of the ...

GAS TURBINE ROTOR COMPRISING AN AXIALLY DISPLACEABLE TURBINE ROTOR SHAFT

A gas turbine rotor for a gas turbine is provided. The gas turbine rotor includes a compressor rotor shaft, a turbine rotor shaft and a coupling device frictionally connecting the two rotor shafts, wherein the coupling device is designed in such a way that the friction connection also exists when the two rotor shafts are displaced relative to one another. In this case, the turbine rotor shaft is lengthened at the end facing the compressor rotor shaft in such a way that said turbine rotor shaft overlaps with the compressor rotor shaft in the axial direction and the coupling device connects this lengthened end of the turbine shaft to the compressor rotor shaft in the radial direction. 18-. (canceled)9. A gas turbine rotor for a gas turbine , comprising:a compressor rotor shaft;a turbine rotor shaft displaced axially in relation to the compressor rotor shaft; anda coupling device which constantly connects the compressor rotor shaft with the turbine rotor shaftwherein the compressor rotor shaft is a hollow shaft through which the turbine rotor shaft is guided, such that it completely overlaps the compressor rotor shaft10. The gas turbine rotor as claimed in claim 9 ,wherein the coupling device is a splined shaft connection, one splined shaft rim of which extends in the circumferential direction over an inner face of the compressor rotor shaft formed as a hollow shaft, and the second splined shaft rim of which, corresponding to the first splined shaft rim, extends in the circumferential direction over the outer face of the lengthened end of the turbine rotor shaft.11. The gas turbine rotor as claimed inwherein the coupling device comprises two regions for connecting the compressor rotor shaft and the turbine rotor shaft in a force-fitting manner, andwherein the first region is located at one end of the compressor rotor shaft and the second region is located at the second end of the compressor rotor shaft.12. The gas turbine rotor as claimed inwherein the coupling device ...

PROPELLER/IMPELLER BLADE APPARATUS

A medium mover/reactionary surface can be used a propeller, impeller, wind generator blade, mixer and the like. The blade design has a shape that pulls against itself under load to maintain its intended shape. The blade design includes one or more generally flat or contoured strip-like sections. These strip-like sections can be attached at their centers to a hub and at the tips to create rake and pitch. 1. A blade apparatus comprising:at least one blade strip;blade tips of adjacent ones of the at least one blade strip connected together; anda central region of each of the at least one blade strip connected to a shaft.2. The blade apparatus of claim 1 , wherein the at least one blade strip includes two blade strips disposed alongside of each other claim 1 , the blade tips of the two blade strips being connected together.3. The blade apparatus of claim 1 , further comprising a hub interconnecting the central region of each of the at least one blade strip with the shaft.4. The blade apparatus of claim 1 , wherein the shaft has a shaft axis generally perpendicular to an axis of the at least one blade strip.5. The blade apparatus of claim 1 , wherein the shaft has a shaft axis generally parallel to an axis of the at least one blade strip.6. The blade apparatus of claim 1 , wherein the at least one blade strip includes a first set of blade strips and at least one additional set of blade strips claim 1 , the first set of blade strips woven with at least one additional set of blade strips.7. A blade apparatus comprising:at least a first and second blade strip;blade tips of adjacent ones of the first and second blade strips connected together;a central region of each of the first and second blade strips connected to a shaft; anda hub interconnecting the central region of each of the first and second blade strips with the shaft.8. The blade apparatus of claim 7 , wherein the shaft has a shaft axis generally perpendicular to an axis of the first and at least one additional ...

TANK SLOSHING ENERGY RECOVERY SYSTEM

A hydrodynamic energy recovery system for effecting mixing of gases within a headspace of a liquid-containment vessel containing a liquid enables mixing of the gases by converting energy of moving or sloshing liquid in a liquid-filled lower portion of the vessel into energy for moving the gases. The system includes (1) a hydro-driven actuator that is movably driven in response to the movement of the liquid in the vessel, (2) a mixing device driven by the actuator such that motion of the mixing device effects mixing of the gases contained in the headspace above the liquid, and (3) a motion converter for converting motion of the actuator into motion for driving the mixing device. The mixing device can be driven without the need to run electrical power within the vessel and without the transfer of motion through an external wall of the vessel. 1. A hydrodynamic energy recovery system for an aircraft fuel tank containing fuel in a liquid-filled portion during aircraft operation to effect movement of gases in an ullage-space above the fuel contained in the aircraft fuel tank , the system comprising:a hydroturbine device mounted in fluid communication with fuel in the liquid-filled portion of the aircraft fuel tank and having an input portion of the hydroturbine device movable in response to movement of fuel within the aircraft fuel tank during operation of the aircraft so as to generate a motion at an output portion of the hydroturbine device;a mixer mounted in fluid communication with the ullage-space of the aircraft fuel tank, the mixer having an output portion that is movable for mechanical interaction with gases in the ullage-space above the fuel to effect mixing of the gases; anda drive train connected between the output portion of the hydroturbine device and an input portion of the mixer, the drive train converting motion at the output portion of the hydroturbine device into motion for driving the output portion of the mixer as the fuel moves in the aircraft fuel ...

NICKEL-BASED ALLOY

Adding silicon, in a defined range of weight percentage, to the composition of a known nickel-based alloy improves oxidation, hot corrosion and dwell crack growth resistance without the detrimental effects on the thermal stability of the microstructure and on other material properties that have been found with known alloys. In a particular preferred embodiment the alloy has the following composition (in weight percent): chromium 14.6-15.4%; cobalt 18-19%; molybdenum 4.75-5.25%; aluminium 2.8-3.2 titanium 3.4-3.8%; tantalum 1.8-2.2%; hafnium 0.4-0.6%; carbon 0.020-0.034%; boron 0.005-0.025%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities. 1. A nickel-based alloy including between 0.2 wt % and 0.6 wt % silicon to improve oxidation resistance , dwell crack growth resistance and hot corrosion resistance without detrimental effect on other mechanical properties of the alloy.2. An alloy as claimed in claim 1 , further including at least one of the following:hafnium <=0.75 wt %;zirconium <=0.1 wt %;magnesium <=0.03 wt %;sulphur <=5 ppm;phosphorous <10 ppm.3. An alloy as claimed in having the following composition in weight percent:chromium 14.6-15.4%;cobalt 18-19%;molybdenum 4.75-5.25%;aluminium 2.8-12%;titanium 3.4-3.8%;tantalum 1.8-2.2%;hafnium 0.4-0.6%;carbon 0.020-0.034%;boron 0.005-0.025%;silicon 0.2-0.6%;the remainder being nickel and incidental impurities.4. An alloy as claimed in claim 1 , having the following composition in weight percent:chromium 15%;cobalt 18.5%;molybdenum 5%;aluminium 3%;titanium 3.6%;tantalum 2%;hafnium 0.5%;carbon 0.027%;boron 0.015%;silicon 0.2-0.6%;the remainder being nickel and incidental impurities.5. An alloy as claimed in claim 1 , having the following composition in weight percent:chromium 15%;cobalt 18.5%;molybdenum 5%;aluminium 3%;titanium 3.6%;tantalum 2%;hafnium 0.5%;carbon 0.027%;boron 0.015%;silicon 0.2%;the remainder being nickel and incidental impurities.6. An alloy as claimed in claim 1 , having the ...

Gas turbine engine with fan variable area nozzle for low fan pressure ratio

A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

Dual frequency hub mounted vibration suppressor system

A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system.

Rotor, a steam turbine and a method for producing a rotor

A rotor, a steam turbine having a rotor, and a method of producing a rotor are disclosed. The rotor disclosed includes a shaft high pressure section. The high pressure section includes a first high pressure section, a second high pressure section, the second high pressure section being joined to the first pressure section, and a third high pressure section, the third high pressure section being joined to the second high pressure section. At least a portion of the second high pressure section is formed of a high-chromium alloy steel comprising 0.1-1.2 wt % of Mn, up to 1.5 wt % of Ni, 8.0-15.0 wt % of Cr, up to 4.0 wt % of Co, 0.5-3.0 wt % of Mo, 0.05-1.0 wt % of V, 0.02-0.5 wt % of Cb, 0.005-0.15 wt % of N, up to 0.04 wt % of B, up to 3.0 wt % of W, and balance Fe and incidental impurities.

ROTOR FOR A PUMP, PRODUCED WITH A FIRST ELASTIC MATERIAL

The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state. 127-. (canceled)28. A rotor for a pump comprising: the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction , the rotor being able to be deformed reversibly elastically in the radial direction between a first , radially compressed state and a second , radially expanded state which the rotor adopts without the effect of external forces , and at least one third state of the rotor being provided in which , in pumping operation under fluid loading , the rotor is deformed from the first state to beyond the second state.29. The rotor according to claim 28 , wherein the rotor is at least partially made of a first claim 28 , elastic material selected from the group consisting of a foam polyurethane claim 28 , a solid polyurethane claim 28 , a thermoplastic elastomer claim 28 , a rubber claim 28 , a superelastic material claim 28 , and superelastic polymer.30. The rotor according to claim 29 , wherein the first material comprises a polyurethane based on a diisocyanate.31. The rotor according to claim 30 , wherein the first material is produced with a polyether polyol.32. The rotor according to claim 31 , wherein the first material is produced with an organically filled polyol claim 31 , selected from the group consisting of a graft- claim 31 , SAN- or polymer polyol and a PHD polyol.33. The rotor according to ...

METHOD AND SYSTEM FOR CONTROLLING THE CLEARANCE AT THE BLADES TIPS OF A TURBINE ROTOR

A system and method for controlling clearance between tips of moving blades of an aeroplane gas-turbine engine and a turbine shroud of an outer casing surrounding the blades. The method includes controlling, according to an operating speed of the engine, a valve positioned in an air duct opening at a stage of the compressor of the engine and leading into a control housing positioned around the outer surface of the turbine shroud and supplied with air coming only from the compressor stage. The valve is opened to cool the turbine shroud during a high-speed phase corresponding to takeoff and climb phases of an aeroplane propelled by the engine and during a nominal-speed phase following the high-speed phase and corresponding to a cruise phase of the aeroplane. 110-. (canceled)11. A method for controlling clearance between tips of moving blades of a turbine rotor of an aeroplane gas-turbine engine and a turbine shroud of an outer casing surrounding the blades , the method comprising:controlling, according to an operating speed of the engine, a valve positioned in an air duct opening into a compressor stage of the engine and leading into a control housing positioned around an outer surface of the turbine shroud, the control housing being supplied with air coming only from the compressor stage; andopening the valve for cooling the turbine shroud of the outer casing during a high-speed operating phase corresponding to takeoff and climb phases of an aeroplane propelled by the engine and during a nominal-speed phase following the high-speed phase and corresponding to a cruise phase of the aeroplane.12. The method according to claim 11 , wherein the valve is closed during a flight idle-speed phase following the nominal-speed phase and corresponding to an approach phase of an aeroplane prior to landing.13. The method according to claim 11 , wherein the valve is closed during a ground idle-speed phase preceding the nominal-speed phase and corresponding to a taxi phase of the ...

THIN AIRFOIL CEILING FAN BLADE

A fan blade comprising a root end, a blade region, and a transition region. Wherein each of the root end and blade region comprise a unique profile, and wherein the transition region comprises a profile which transitions the root end profile to the blade region profile. The root end profile comprises a substantially convex top surface, a substantially concave domed sector, and reliefs to allow for the root end to be coupled with a similarly shaped fan hub extrusion. The blade region profile comprises a substantially convex top surface and bottom surface which terminate at a leading edge and trailing edge. The blade region slopes upward along a length of the blade region and terminates at a curved tip. 1. A fan blade configured to mount to a rotating fan hub , the fan blade comprising:a. a root end configured to couple with the rotating fan hub, wherein a profile of the root end comprises a substantially convex top surface and a substantially concave domed sector;b. a blade region, wherein a profile of the blade region comprises a substantially convex top surface and bottom surface;c. a transition region extending between the root end and the blade region, wherein the transition region comprises a profile which transitions the root end profile to the blade region profile;d. a leading edge;e. a trailing edge; andf. a tip, wherein the leading edge and trailing edge terminate into the tip.2. The fan blade of claim 1 , wherein the root end comprises an arcuate cutout.3. The fan blade of claim 2 , wherein the domed sector is configured to terminate into a region which is parallel to a plane of rotation of the fan blade at a position proximal to the arcuate cutout.4. The fan blade of claim 3 , wherein the transition portion comprises a first potion claim 3 , an inflection portion claim 3 , and a second potion.5. The fan blade of claim 4 , wherein the first portion comprises an extension of the concave domed sector of the root end which terminates at the inflection portion. ...

ROTOR FOR A WIND TURBINE

A rotor for a wind turbine, having a diameter of 50 metres or more, has a blade with at least two blade sections in the lengthwise direction of the blade, where at least one blade section has a curvature along the blade and relative to a second blade section, where said curvature results in the tip end of said blade being offset (x) relative to the axis of the blade root. A ratio (x/L) of the offset (x) relative to a distance (L) from the tip end of the blade to the blade root is between 0 and 0.1. 2. The rotor for a wind turbine according to claim 1 , wherein a blade of said rotor has a combined radius specific solidity Solat:{'sub': 'r', 'blade radius r=30% of the rotor radius R, where Sol≦0.0345;'}{'sub': 'r', 'blade radius r=40% of the rotor radius R, where Sol≦0.028;'}{'sub': 'r', 'blade radius r=50% of the rotor radius R, where Sol≦0.023;'}{'sub': 'r', 'blade radius r=60% of the rotor radius R, where Sol≦0.019;'}{'sub': 'r', 'blade radius r=70% of the rotor radius R, where Sol≦0.016;'}{'sub': 'r', 'blade radius r=80% of the rotor radius R, where Sol≦0.0125;'}{'sub': 'r', 'blade radius r=90% of the rotor radius R, where Sol≦0.01; and'}{'sub': 'r', 'blade radius r=96% of the rotor radius R, where Sol≦0.008,'}{'sub': 'r', 'and where Solhas a level below a linear interpolation between any of the given blade radii.'}3. The rotor for a wind turbine according to claim 1 , wherein a blade of said rotor has a combined radius specific solidity Solat:{'sub': 'r', 'blade radius r=30% of the rotor radius R, where Sol≦0.033;'}{'sub': 'r', 'blade radius r=40% of the rotor radius R, where Sol≦0.0255;'}{'sub': 'r', 'blade radius r=50% of the rotor radius R, where Sol≦0.021;'}{'sub': 'r', 'blade radius r=60% of the rotor radius R, where Sol≦0.017;'}{'sub': 'r', 'blade radius r=70% of the rotor radius R, where Sol≦0.0135;'}{'sub': 'r', 'blade radius r=80% of the rotor radius R, where Sol≦0.011;'}{'sub': 'r', 'blade radius r=90% of the rotor radius R, where Sol≦0.008; and'}{'sub ...

Turbine engine shaft coupling

A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediate tie shaft segment connected axially between a first tie shaft segment and a second tie shaft segment. The first tie shaft segment includes a first threaded tie shaft surface that is mated with a first threaded shaft surface of the first sub-shaft. The second tie shaft segment includes a second threaded tie shaft surface that is mated with a second threaded shaft surface of the second sub-shaft. The tie shaft also includes a sub-shaft bumper stop extending radially from the intermediate tie shaft segment to a bumper stop distal end, which has a radius that is greater than a radius the first and/or second threaded shaft surfaces.

Method and Device for variable motion and applications using Interchangeable Heads

A machine for automating manual labor has a motor portion, transmission portion, and a head portion which may all be interchanged with alternates for different applications. The machine is driven by an electric motor that can perform different motions and actions, one at a time or simultaneously, depending on the transmission and head portions. Two such motions are rotary and linear reciprocating motion. Applications include cleaning surfaces, cleaning vessels, mixer, blender, chopper, slicer, shredder, vibrator, massager, semi and fully automatic milk cream maker. 1. An apparatus for achieving a variety of rotary motion , linear motion and simultaneously rotary and linear motions via two axes used for cleaning dirty , singed and oily surfaces of kitchen utensils and for preparing whipped milk , said apparatus comprising ,a. a motor portion operatively producing a rotational force;b. a transmission mechanism configured to convert said of rotational force of said motor into a preconfigured operational motionc. an interchangeable head-piece having a housing, a distal end and a proximal endd. wherein said preconfigured operational motion is selected for the group consisting of linear motion, rotary motion and a combination of linear and rotary motions;e. wherein said head-piece, coupled with a said respective transmission mechanism, is adopted to receive either a linear motion, or a rotary motion, or a combination of linear and rotary motions;f. wherein said proximal end of said head-piece is securely attached to the housing of said motor;g. wherein said distal end of said head-piece is a functionary portion; and whereinh. the said preconfigured operational motion activates said functionary portioni. head section, said modified motion being selected from the group consisting of: rotational motion; eccentric rotation; linear reciprocating motion; and combinations thereof;j. wherein said motor, head, and transmission portions are replaceable allowing for a variety of ...

LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE

A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed. 1. A gas turbine engine comprising:a fan and a turbine having a fan drive rotor; a gear reduction effecting a reduction in the speed of said fan relative to an input speed from said fan drive rotor; {'br': None, '(number of blades×speed)/60≧5500 Hz; and'}, 'said fan drive rotor having a number of turbine blades in at least one of a plurality of rows of said fan drive rotor, and said turbine blades operating at least some of the time at a rotational speed, and said number of turbine blades in said at least one row and said rotational speed being such that the following formula holds true for said at least one row of the fan drive turbine'}said rotational speed being in revolutions per minute.2. The gas turbine engine as set forth in claim 1 , wherein the formula results in a number greater than or equal to 6000 Hz.3. The gas turbine engine as set forth in claim 2 , wherein said gas turbine engine is rated to produce 15 claim 2 ,000 pounds of thrust or more.4. The gas turbine engine as set forth in claim 1 , wherein the formula holds true for the majority of blade rows of the fan drive rotor.57.-. (canceled)8. A method of designing a gas turbine engine comprising the steps of: {'br': None, '(number of blades×speed)/60≧5500 Hz; and'}, 'including a gear reduction between a fan drive turbine rotor and a fan, and selecting a number of blades in at least one row of the fan drive turbine rotor, in combination with a rotational speed of the fan drive turbine rotor, such that the following formula holds true for said at least one row of the fan drive turbine rotorsaid ...

AXISYMMETRIC PART FOR AN AVIATION TURBINE ENGINE ROTOR

A link part for a turbine engine, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform, the annular wall being made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform. 1. A link part for a turbine engine , the link part being mounted between a fan cone and a fan disk supporting fan blades , said link part comprising an annular wall pierced by a plurality of orifices , each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface providing an aerodynamic extension of said fan between an outer surface of said fan cone and an outer surface of a fan blade platform , wherein said annular wall is made of a first material that is composite and is provided on an inner surface of said rim with a ring made of a second material , said second material being different from the first and suitable for radially retaining said fan blade platform.2. A link part according to claim 1 , wherein said second material is a long-fiber composite material including winding a yarn claim 1 , a tape claim 1 , or a woven or stitched preform of carbon claim 1 , glass claim 1 , or aramid fibers.3. A link part according to claim 1 , wherein said second material is a metal material including titanium or a metal alloy based on titanium or aluminum.4. A link part according to claim 2 , wherein said orifices are provided with metal inserts made of titanium or of metal alloy based on titanium.5. A link ...

BLADE GROUP ARRANGEMENT AS WELL AS TURBOMACHINE

A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade. 1. A blade group arrangement for a turbomachine in order to form a blade-row group , comprising:{'sub': min,1', 'min,2, 'a front blade and a rear blade arranged offset from each other in the axial and circumferential directions and forming an overlapping area running between a pressure side of the front blade and a suction side of the rear blade, the front and rear blades in the overlapping area converging with a contraction ratio KV of KV≧1.2 between an inlet surface Dand an outlet surface D.'}2. The blade group arrangement as recited in wherein the contraction ratio KV is ≦2.8.3. The blade group arrangement as recited in wherein the contraction ratio KV=1.7.4. The blade group arrangement as recited in wherein the suction side of the rear blade has a greater curvature downstream from the outlet surface Dthan upstream from the outlet surface D.5. The blade group arrangement as recited in wherein the curvature has a maximum ranging from 1.6 to 1.7 times a mean curvature of the suction side of the rear blade.6. The blade group arrangement as recited in wherein the curvature maximum amounts to approximately 5% to 25% of the relative skeleton line length behind the outlet surface D.7. A turbomachine comprising at least one blade-row group having a plurality of blade group arrangements as recited in . This claims the benefit of European Patent Application EP 12154944.8, filed Feb. 10, 2012 and hereby incorporated by reference herein.The invention relates to a blade group arrangement as well as to a turbomachine.The maximum deflection of a row of blades of a turbomachine and thus its aerodynamic load capacity are limited, for one thing, by a separation of the flow along ...

ROTOR

A rotor of a charging device may include at least two parts fastened to each other and configured to enclose a hollow space. The two parts may be fastened to each other via a negative pressure within the hollow space. 1. A rotor of a charging device , comprising: at least two parts fastened to each other , and configured to enclose a hollow space ,whereinthe two parts are fastened to each other via a negative pressure, within the hollow space.2. The rotor according to claim 1 , wherein the two parts engage at least one of a compressor wheel claim 1 , turbine wheel claim 1 , heat shield claim 1 , and rotor shaft.3. The rotor according to claim 1 , wherein the two parts tightly bear against each other via axial end faces claim 1 , wherein the end faces are formed at least one of straight claim 1 , curved and conically claim 1 , andwherein the end faces are surface-finished.4. The rotor according to claim 1 , wherein at least one of the two parts is formed of titanium or has a titanium coating.5. The rotor according to claim 1 , wherein at least one of the two parts is formed of ceramic.6. The rotor according to claim claim 1 , wherein the two parts are connected to each other at contact surfaces claim 1 , and further comprising a compressor wheel configured to lie at a maximum diameter of the two parts.7. A rotor of a charging device claim 1 , comprising: at least two parts fastened to each other claim 1 , wherein at least one of the two parts is formed of titanium a contact surface to the other part and is connected to the other part via a cold-fusion-connection under pressure.8. The rotor according to claim 7 , wherein at least one of the two parts is formed of ceramic.9. The rotor according to claim 7 , wherein the two parts engage at least one of a compressor wheel claim 7 , turbine wheel claim 7 , heat shield claim 7 , and rotor shaft.10. A rotor of a charging device claim 7 , comprising: at least two parts fastened to each other claim 7 , via a thermally active ...

Bladeless Turbine

The bladeless turbine includes a case, three or more turbine discs disposed within the case. Each turbine disc has a center opening, and two or more of the turbine discs have a set of exhaust ports positioned annularly around the center opening. A drive shaft passes through the center openings of the turbine discs and is attached to the three or more turbine discs, wherein the drive shaft is positioned within the case along the centerline, free to rotate within the case, and extends through the case for connection to a generator. The one or more fluid/vapor inlets are attached to the main housing such that a fluid/vapor is directed at a specified angle onto the three or more turbine discs. The fluid/vapor outlet is aligned with the centerline. A set of exhaust holes proximate to and connected to the fluid/vapor outlet that are positioned annularly around the drive shaft.

COMBINED SEALING AND BALANCING ARRANGEMENT FOR A TURBINE DISC

A turbine disc for a turbine is provided with a first protrusion and a second protrusion. The first protrusion and the second protrusion are formed in such a way that a balancing weight is coupleable between the first protrusion and the second protrusion. The first protrusion has a sealing section that is capable of sealing a fluid passage between the turbine disc and a further turbine part of the turbine. 114-. (canceled)15. A turbine disc for a turbine , comprisinga first protrusion and a second protrusion,wherein the first protrusion and the second protrusion are formed in such a way that a balancing weight is coupleable between the first protrusion and the second protrusion, andwherein the first protrusion comprises a sealing section that is capable of sealing a fluid passage between the turbine disc and a further turbine part of the turbine.16. The turbine disc of claim 15 , further comprisinga first surface and a second surface,wherein the first protrusion and the second protrusion are formed on at least one of the first surface or second surface.17. The turbine disc of claim 16 ,wherein the turbine disc is coupleable to the turbine in such a way that the first surface and the second surface are opposed surfaces in an axial direction of a shaft of the turbine.18. The turbine disc of claim 17 ,wherein the turbine disc is coupleable to the turbine in such a way that the first surface is orientated upstream with respect to a fluid flow of the turbine and the second surface is orientated downstream with respect to the fluid flow.19. The turbine disc of claim 15 ,wherein the sealing section comprises a single seal lip.20. The turbine disc of claim 15 ,wherein the sealing section comprises a labyrinth seal.21. The turbine disc of claim 15 ,wherein the first protrusion and the second protrusion are formed and/or arranged in such a way that a recess between the first protrusion and the second protrusion is formed, andwherein the recess is formed in such a way that the ...

Method for the production of a one-piece rotor area and one-piece rotor area

The present invention describes a method for the production of a one-piece rotor area, preferably of a jet engine. The rotor area includes an annular base body and several, circumferentially distributed blade elements extending essentially radially from the base body. Residual stresses are imparted to the blade elements in surface-near areas by way of roller compression using a rolling tool introduced between the blade elements. During roller compression, one each area of a blade element is arranged between areas of the rolling tool, with longitudinal sides of the blade element being simultaneously roller-compressed. According to the present invention, the rolling tool is radially introduced between the blade elements and the surfaces of the blade elements are roller-compressed, thus at least the blade elements having a roller-compressed surface.

Blade ring segment having an annular space delimiting surface having a wavy height profile and a method for manufacturing same

A method for machining a workpiece. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. The electrode is moved at least partially with the electrode surface parallel to the surface, so that during the approach to the workpiece, areas of the workpiece having an irregular edge machined at a different intensity are formed, the difference in intensity of machining on the edge of the surface to be machined being compensated in that the surface to be machined is provided with a height profile adapted to the shape of the end of the surface to be machined. A blade ring segment and blade ring is also disclosed.

Method for welding steel material to ni-based superalloy and welding joint

When a turbine impeller ( 4 ) formed from an Ni-based superalloy and a rotor shaft ( 2 ) formed from a steel material are joined by being fused together via welding in a boundary portion, a mixing ratio of a welding metal ( 6 ) that is formed in the boundary portion by fusing together the Ni-based superalloy forming the turbine impeller ( 4 ) and the steel material forming the rotor shaft ( 2 ) is between 0.5 and 0.8. As a result, it is possible to obtain a sound welding joint in which there are no cracks in the boundary between the welding metal ( 6 ) and the Ni-based superalloy ( 4 ).

BYPASS FOIL

An apparatus for providing electrical power includes a foil having a leading inlet, at least rotor internal to the foil and downstream from the inlet and a trailing flow separator partially within a trailing chamber. The apparatus also includes leading and trailing edges configured such that fluid flowing through the foil experiences decreased pressure and increased velocity at the trailing edges relative to the leading edges. In a method utilizing the disclosed apparatus within a fluid flow, a first quantity of a high-pressure fluid is passed, at a low velocity, into the leading inlet of the bypass foil. One or more rotors are rotated by the flow and the rotational energy is translated into electrical power with a generator. After turning the rotors, quantity of fluid is ejected, at a high velocity, to the trailing edges of the bypass foil at an area of low fluid pressure. 1. A system comprising:a foil including a leading inlet, a forward chamber downstream of the leading inlet, a rearward chamber downstream of the forward chamber and a constriction between the forward and rearward chambers;at least one rotor within the forward chamber; anda trailing flow separator partially within the trailing chamber and including a leading edge and a trailing edge;wherein fluid flowing through the foil experiences decreased pressure and increased velocity at the rearward chamber relative to the forward chamber.2. The system of claim 1 , further comprising a leading flow separator within the forward chamber including a leading edge and a trailing edge.3. The system of claim 2 , wherein the at least one rotor comprises at least two rotors located on opposite sides of the first flow separator trailing edge.4. The system of claim 1 , wherein the foil further comprises upper and lower portions each having exterior surfaces and leading and trailing edges.5. The system of claim 4 , wherein the upper and lower portions each include cambers of equal curvature on the exterior surfaces ...

Axially-split radial turbine

An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.

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.

METHOD AND APPARATUS FOR CONNECTING TURBINE ROTORS

Connecting rotors in rotary machines, particularly turbines, is generally described. Some aspects of the invention provide for a simplified attachment rotors to each other and/or other components of a turbine assembly, such as, drive shaft, using friction fit. 1. A turbine assembly including:a first turbine rotor having a disc and at least one blade attached to the disc; anda second turbine rotor having a disc and at least one blade attached to the disc,wherein the first and second turbine rotors are attached to each other via only a friction fit.2. The assembly of claim 1 , wherein the first and/or second turbine rotor is boreless.3. The assembly of claim 1 , wherein a self-locking tapered fit joint provides the friction fit between the rotors.4. The assembly of claim 1 , wherein the discs of the first and second rotors are free of any holes or openings arranged in an axial direction.5. The assembly of claim 1 , wherein the discs of the first and second turbine rotors include complementary annular engagement surfaces that engage with each other via a friction fit.6. The assembly of claim 5 , wherein the annular engagement surfaces are tapered.7. The assembly of claim 6 , wherein the annular engagement surface of the first turbine rotor tapers so that a circumference of the engagement surface decreases with distance away from the disc.8. The assembly of claim 7 , wherein the annular engagement surface of the second turbine rotor tapers so that a circumference of the engagement surface increases with distance away from the disc.9. The assembly of claim 5 , wherein the annular engagement surfaces extend in a generally axial direction relative to a respective disc.10. The assembly of claim 5 , wherein the annular engagement surface of the first turbine rotor is on a first side of the disc claim 5 , the first turbine rotor further including a second annular engagement surface on a second side of the disc opposite the first side claim 5 , the second annular engagement ...

Rotor assembly for an axial turbine

A rotor assembly includes a drive shaft; a rotor having rotor blades, which each comprise a profiled rotor blade section and a blade fastening section; wherein each blade fastening section comprises a first contact region and a second contact region, the first contact region being at least indirectly supported on the blade fastening section of a first adjacent rotor blade, the second contact region being at least indirectly supported on the blade fastening section of a second adjacent rotor blade; the blade fastening sections are fastened in a formfitting manner and/or by a screw connection on the drive shaft, so that there is a connection between rotor blade and drive shaft on an axial end face of the blade fastening section. Intermediate elements having an elastic intermediate layer are between the blade fastening sections of adjacent rotor blades.

Fan Oscillating Mechanism and Ceiling Fan Using the Same

A ceiling fan with oscillating mechanism includes a clutch member for adjusting the angle of oscillation according to user's need. When the motor is actuated, the rotating torque induced by the motor and the transmission mechanism is smaller than the rotational resistance of the clutch member such that the motor may drive the fan to oscillate. Further, when the user applies an external rotational force greater than the rotational resistance of the clutch member, the user can swing the fan to any angle as desired without rotating or shifting other members except the fan and the fan suspension tube. In this manner, undesired damage of the mechanism or motor due to inappropriately applied external force can be avoided efficiently. 1. A fan oscillating mechanism , comprising:a motor having a driving shaft;a crank plate having one end connected pivotally to said driving shaft;a connecting rod having a first end connected pivotally to the other end of said crank plate, and a second end;a spindle link having a head end connected pivotally to said second end of said connecting rod, and a tail end;a fan suspension tube having a top end connected to said tail end of said spindle link, and a bottom end connected to a fan device; anda clutch member having at least one wave washer disposed between said spindle link and said fan suspension tube;wherein said clutch member provides a rotational resistance such that when said motor is actuated, said driving shaft rotates said crank plate to move said connecting rod to rotate said spindle link, whereby said spindle link induces a rotating torque that is smaller than said rotational resistance of said clutch member, and thus the spindle link moves said fan suspension tube to rotate; and when said fan suspension tube is subjected to an external rotational force greater than said rotational resistance of said clutch member, said fan suspension tube runs free.2. The fan oscillating mechanism as claimed in claim 1 , wherein said clutch ...

AIRFOIL AND PLATFORM ASSEMBLY FOR SUPERSONIC FLOW

An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve. 110-. (canceled)11. An assembly comprising:an airfoil for a turbine engine bladed wheel and a platform on which the airfoil is configured to be mounted:a plurality of the airfoils configured to be fastened to the platform or to a plurality of the platforms assembled together so as to form a bladed wheel including a wheel axis and defining upstream and downstream directions along that axis, the airfoils being arranged radially in the wheel;in the wheel, the platform or the assembled-together platforms present a platform surface between the airfoils and that radially defines an inside of gas-passing passages formed between the airfoils; andthe platform surface presenting a circumferential depression extending axially substantially between a leading edge and a trailing edge of an airfoil, a deepest section of the depression being situated axially in the upstream half of the airfoil;wherein:a skeleton curve is a curve representing variations of a skeleton angle of the airfoil in a section plane substantially parallel to the platform surface, as a function of position along the axis of the wheel;a linearized ...

Airfoil and platform assembly for subsonic flow

An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.

Friction welded turbine disk and shaft

An assembly for use in a turbine of a gas turbine engine includes a turbine disk and a shaft. The turbine disk comprises a superalloy. The shaft is friction welded to the turbine disk at a shaft interface substantially adjacent the turbine disk.

TURBOMACHINERY

In a turbomachinery (S) that is provided with an impeller () and a shaft () that are to be fastened, the impeller () and the shaft () are fastened by a two-way screw () of which the turning direction of the screw thread that is formed on the impeller () side and the turning direction of the screw thread that is formed on the shaft () side are opposite directions. As a result, it is possible to fasten the impeller () to the shaft () without the need for a complicated and large equipment, and the amount of work during fastening is reduced. 1. A turbomachinery comprising an impeller that is rotatively driven and a shaft that transmits rotational power to the impeller ,wherein the turbomachinery comprises a two-way screw of which a first end side serves as an impeller screwing region that is screwed together with the impeller and a second end side serves as a shaft screwing region that is screwed together with the shaft, with the turning direction of the screw thread that is formed at the impeller screwing region and the turning direction of the screw thread that is formed at the shaft screwing region made to be opposite directions, andthe impeller and the shaft are fastened by the two-way screw.2. The turbomachinery according to claim 1 , wherein the two-way screw is formed with a material having a higher thermal conductivity than the impeller.3. The turbomachinery according to claim 2 , wherein the two-way screw is formed with a steel material in the case of the impeller being formed with a titanium alloy.4. The turbomachinery according to claim 1 , comprising a rotation inhibiting member that inhibits rotational movement of the impeller with respect to the shaft.5. The turbomachinery according to claim 4 , wherein the rotation inhibiting member claim 4 , with the rotation axis direction of the impeller serving as the lengthwise direction claim 4 , is a fitting hole that is provided at a position offset from the rotation axis of the impeller and a pin member that is ...

SPIRAL SCREW FLUID TURBINE HAVING AXIAL VOID

A spiral turbine includes an axle configured to rotate and one or more spiral blades coupled to the axle by one or more support connections. Each spiral blade is formed around and outside of a conical inner space which is coaxial with the axle. 1. A spiral turbine comprising:an axle configured to rotate;one or more spiral blades coupled to the axle by one or more support connections, each spiral blade being formed around and outside of a conical inner space which is coaxial with the axle.2. The spiral turbine of claim 1 , wherein the one or more spiral blades comprises at least two of the spiral blades claim 1 , the blades being symmetrically disposed around the axle.3. The spiral turbine of claim 1 , wherein each spiral blade converges on and couples to the axle at a narrow end of the conical inner space.4. The spiral turbine of claim 1 , wherein each spiral blade is segmented.5. The spiral turbine of claim 1 , wherein the one or more spiral blades are weight balanced around the axle.6. The spiral turbine of claim 1 , wherein each spiral blade is wider at a wide end of the conical inner space than at a narrow end of the conical inner space.7. The spiral turbine of claim 1 , wherein each spiral blade has a leading edge spaced apart from a perimeter of the conical inner space.8. The spiral turbine of claim 1 , wherein each spiral blade has one of a flat profile or a curved profile.9. The spiral turbine of claim 1 , further comprising an electricity generator operatively coupled to the axle.10. The spiral turbine of claim 9 , wherein the axle is operatively coupled to the electricity generator through a rotatable universal joint.11. An electricity generating system comprising:at least one electricity generator having a rotational input; an axle operatively coupled to the rotational input;', 'one or more spiral blades coupled to the axle by one or more support connections, each spiral blade being formed around and outside of a conical inner space which is coaxial with ...

PROPFAN ENGINE

The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section. 1. A propfan engine comprising:one or more rotor stages comprising a plurality of rotors; andan outer wall comprising an outer profile, at least a portion of the outer profile comprising a substantially circular cross-section, whereinthe diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section.2. The propfan engine of claim 1 , wherein the diameter increases at an increasing rate in a first part of the portion of the outer profile claim 1 , and the diameter increases at a decreasing rate in a second part of the portion of the outer profile.3. The propfan engine of claim 2 , wherein the second part is downstream of the first part of the portion of the outer profile and there is a point of inflection in the outer profile between the first and second parts of the portion of the outer profile.4. The propfan engine of wherein the radius of the curvature in the first part of the portion of the outer profile is substantially 20% of a maximum diameter of the propfan outer wall.5. The propfan engine of claim 1 , wherein in a third part of the portion of the outer profile the diameter of the substantially circular cross-section reduces in the direction of flow over the outer wall.6. The propfan engine of claim 2 ...

TURBINE ROTOR AND PRODUCTION METHOD THEREOF

A turbine rotor related to the present invention includes a first member, and a second member joined to the first member, wherein the first and the second members are extended in an axial direction of the turbine rotor, a groove portion for welding is formed at a border between the first and the second members and penetrates the bottom portion of the groove portion, and a gas-introducing hole for introducing inert gas inside the turbine rotor is covered by welding. 1. A turbine rotor comprises:a first member, anda second member joined to the first member,wherein the first and the second members are extended in an axial direction of the turbine rotor,a groove portion for welding is formed at a border between the first and the second members and penetrates the bottom portion of the groove portion, anda gas-introducing hole for introducing inert gas inside the turbine rotor is covered by welding.2. The turbine rotor according to claim 1 , whereinthe material of the first member is different with that of the second member, andthe border between the first and the second members in the groove portion is close to either one of the first and second members.3. The turbine rotor according to claim 2 , whereinthe material of the first member is different with that of the second member, andthe border between the first and the second members is close to the member higher in hardness of either one of the first and second members.4. The turbine rotor according to claim 1 , whereineach of connecting surfaces of the first and the second members is formed in a shape fitted into each other.5. The production method of a turbine rotor welded a first member and a second member having different thermal conductivity with the first member claim 1 , the method comprises the steps of:disposing one member at the upper side of the other member, the one member being one of the first and the second members and being higher in thermal conductivity than the other member, and the other member being ...

REDUCED PRESSURE BALANCING OF A TURBINE ROTOR

The present invention relates to a device for inserting a balancing weight into a rotor of a turbine, that includes an external component and an internal component. The internal component is connected in a helical manner to the external component. The internal component delimits a chamber which has a first and a second opening, a lower surface which is provided with a sealing joint and a cap in order to close in a tight manner the first opening of the chamber. The connection between the external component and the internal component is helical, that is to say, the result of a threading operation. Therefore, the internal component can thus move in a coaxial manner with respect to the external component. 1. A device for inserting a balancing weight into a rotor of a turbine , comprisingan external component,an internal component which is connected in a helical manner to the external component,wherein the internal component delimits a chamber which has a first and a second opening and comprises a lower surface which is provided with a sealing joint, and a cap in order to close in a tight manner the first opening of the chamber.2. The device according to claim 1 , wherein the joint is planar and covers at least a portion of the lower surface around the second opening of the internal component.3. The device according to claim 1 , wherein the cap is retained on the first opening of the chamber by at least two screws.4. The device according to claim 1 , further comprising at least one guiding member claim 1 , configured to guide the internal component relative to the external component.5. The device according to claim 1 , wherein the helical connection constitutes a nut.6. A turbine comprising:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'at least one rotor which has at least one balancing hole, further comprising a device for inserting a balancing weight according to .'}7. The turbine according to claim 6 , wherein the device is fixed to an external housing of the ...

Blower wheel with improved wheel hub to blade interface

A blower wheel for use in a blower assembly includes a hub, a concentrically arranged outer ring, an array of spaced apart blades extending between the hub and the outer ring. The hub includes an outer first surface and an inner second surface. An interface between an outer edge of a first end of each of the blades and an outer peripheral edge of the outer first surface of the hub is minimized, increasing an effective blade exit height of the blower wheel. As such, an effective open area for airflow between the blades of the blower wheel is increased over that of the prior art blower wheels. Further, a substantially planar lower face of the hub provides additional structural integrity to the hub, and thereby the blades.

Gas turbine rotor assembly method

Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Fluid stream driven wobble plate motor

Several embodiments of a wobble plate motor include a disc mounted on a bent shaft. Driving the wobble plate so it revolves on a flat base causes the bent shaft to rotate and drive a generator or other work consumer. The wobble plate may be driven by a fluid stream impinging on the plate or by a blade assembly in a path of fluid movement. In one embodiment of a bladed motor, a shroud may direct the fluid stream so it more efficiently cooperates with the blade assembly. 1. A wobble plate motor comprisinga shaft having a first section mounted for rotation about an axis and a bent shaft end rigid with the first section and inclined to the rotational axis;a circular disc journalled on the bent shaft end for movement therewith; anda planar base abutting the circular disc and surrounding the axis, the base being inclined to the disc;the disc being mounted to nutate on the base so that application of an eccentric force to the disc causes the disc to nutate on the base and rotatably drive the first shaft section about the axis.2. The wobble plate motor of further comprising a blade assembly on the bent shaft end providing a force to the disc claim 1 , the blade assembly being configured to provide a force offset relative to the axis claim 1 , the blade assembly nutating with the disc.3. The wobble plate motor of further comprising a housing having a passage claim 2 , the circular disc and planar base being in the passage and a member claim 2 , upstream of the circular disc and partially blocking the passage claim 2 , the member having an opening therethrough offset relative to the axis and allowing a fluid stream to pass through the opening and striking the blade assembly offset relative to the rotational axis claim 2 , the member being mounted for rotation contemporaneously with nutation of the blade assembly.4. The wobble plate motor of wherein the flow director rotates at the same rate as the circular disc nutates.5. The wobble plate motor of wherein the blade assembly ...

FIXTURE FOR CONNECTING ROTORS OF ROTARY MACHINE AND METHOD OF CONNECTING ROTORS

A fixture for connecting rotors of a rotary machine includes: an axial member provided with a column-like fitting portion which is disposed inside of a first bolt hole and fits the first bolt hole; and a sleeve provided with a cylindrical fitting portion which is disposed inside of a second bolt hole and fits the second bolt hole. The axial member further includes a tapered portion which is formed on an end portion of the column-like fitting portion, and is gradually reduced in diameter from the first bolt hole toward the second bolt hole. The cylindrical fitting portion of the sleeve is formed with a tapered hole which is gradually expanded in diameter from the second bolt hole toward the first bolt hole around an axis of the sleeve. 1. A fixture for connecting rotors of a rotary machine , which is used to connect a first rotor and a second rotor to each other by butting a first flange portion provided on an end portion of the first rotor and a second flange portion provided on an end portion of the second rotor to each other , and inserting a bolt through a first bolt hole which is formed in the first flange portion and a second bolt hole which is formed in the second flange portion , the fixture comprising:an axial member provided with a column-like fitting portion which is disposed inside of the first bolt hole, and fits the first bolt hole; anda sleeve provided with a cylindrical fitting portion which is disposed inside of the second bolt hole, and fits the second bolt hole, whereinthe axial member further includes a tapered portion which is formed on an end portion of the column-like fitting portion, and is gradually reduced in diameter from the first bolt hole toward the second bolt hole, andthe cylindrical fitting portion of the sleeve is formed with a tapered hole which is gradually expanded in diameter from the second bolt hole toward the first bolt hole around an axis of the sleeve and is capable of fitting the tapered portion.2. The fixture for ...

BLADED ROTOR FOR A TURBOMACHINE

A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2). 1. A bladed rotor for a turbomachine , comprisinga plurality of blades distributed around a circumference of the bladed rotor; wherein a blade distribution of the plurality of blades is a natural-number sector count (Z) of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count, wherein the natural number sector count is odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).2. The rotor as recited in claim 1 , wherein the first blades in the first angular sectors and the second blades in the second angular sectors are at least substantially identical.3. The rotor as recited in claim 1 , wherein the first blades in the first angular sectors and/or the second blades in the second angular sectors are distributed at least substantially equidistantly from each other.4. The rotor as recited in claim 2 , wherein the first blades in the first angular sectors and/or the second blades in the second angular sectors are distributed at least substantially equidistantly from each other.5. The rotor as recited in claim 1 , wherein a distance between a first blade adjacent to a second angular sector and a second blade adjacent to this first blade is at least ...

ROTOR KEYHOLE FILLET FOR A GAS TURBINE ENGINE

A rotor for a gas turbine engine includes an annular structure having a blade slot. A hub engagement feature is provided on the annular structure. The hub engagement feature includes first and second surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second surfaces. A method of manufacturing a rotor includes the steps of machining an annular hub engagement feature into a rotor. The hub engagement feature includes first and second surfaces transverse to one another and is joined by a fillet that is recessed with respect to the first and second surfaces. The method includes the step of peening the fillet, and grinding the first and second surfaces. 1. A rotor for a gas turbine engine comprising:an annular structure having a blade slot; anda hub engagement feature provided on the annular structure, the hub engagement feature including first and second surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second surfaces.2. The rotor according to claim 1 , wherein the first and second surfaces are normal to one another.3. The rotor according to claim 1 , wherein the fillet includes a peened surface.4. The rotor according to claim 3 , wherein the annular structure is constructed from a nickel alloy.5. The rotor according to claim 3 , wherein the first and second surfaces are provided by ground surfaces.6. The rotor according to claim 1 , wherein the first and second surfaces are non-tangential to the fillet.7. A rotor assembly for a gas turbine engine comprising:a shaft;a rotor supporting a blade and including a hub engagement feature, the hub engagement feature including first and second rotor surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second rotor surfaces; anda hub supported on the shaft and engaging the hub engagement feature.8. The rotor assembly according to claim 7 , comprising a nut secured to the ...

ROTOR ASSEMBLY AND REFIT METHOD

A method of coupling at least two sections of a rotor designed to carry the rotating parts of a turbine for the generation of electrical power for a public grid and a modified rotor is described with a coupling of increased diameter exceeding the nominal diameter of the rotor, with the step of removing mass from an volume lying exclusively within the interior of the sections when coupled such that the lateral critical speed of the coupling is moved away from the normal operating speed of the rotor 1. A method for shifting a critical vibrational mode of a rotor further away from the normal operating speed of the rotor comprising:providing the rotor with a coupling that couples contact faces of two rotor sections; andremoving mass from a volume lying exclusively within the interior of the rotor sections when coupled.2. The method of wherein the removing mass comprises removing mass from a contact face of the coupling thereby creating a cavity at a coupling end of at least one rotor section.3. A rotor for carrying the rotating parts of a turbine for the generation of electrical power for a public grid with the rotor comprising at least two rotor sections coupled with a coupling of diameter exceeding the nominal diameter of the rotor sections claim 1 , wherein at least one of the rotor sections includes one or more cavities at the end of the at least one rotor section and in the vicinity of the coupling such that the boundaries of the one or more cavities are all interior surfaces when the rotor sections are coupled.4. The rotor of wherein the one or more cavities at the end of at least one rotor sections and in the vicinity of the coupling extend from the wall of the rotor into a part of the coupling exceeding the nominal diameter of the rotor sections or are placed in a volume extending from the wall of the rotor sections into a part of the coupling exceeding the nominal diameter of the rotor sections.5. The rotor of wherein the at least one of the rotor sections ...

HYDROELECTRIC POWER GENERATING DEVICE AND SYSTEM

A fluid conduit has a constant diameter and a chamber in the conduit has a larger diameter than the diameter of the conduit. Within the chamber, an impeller is rotatable by fluid moving through the conduit and the chamber. The impeller includes blades extending spirally along an impeller shaft. When rotated, the impeller blades define a cylinder having a diameter greater than the conduit diameter and less than the chamber diameter. 1. A system comprising:a fluid conduit having a first diameter;a cylindrical chamber coaxially mounted in the fluid conduit, the chamber having a second diameter greater than the first diameter;an inlet at a first end of the chamber, the inlet having the first diameter and being connected to the fluid conduit;an outlet at a second end of the chamber opposite the first end, the outlet having the first diameter and being connected to the fluid conduit; andan impeller having a shaft coaxially and rotatably mounted in the chamber, the impeller having a plurality of impeller blades mounted on the shaft, rotation of the blades defining a diameter greater than the first diameter and less than the second diameter.2. The system of wherein the impeller includes a single set of multiple blades.3. The system of wherein the impeller includes a plurality of adjacent sets of multiple blades.4. The system of wherein each set of multiple blades is offset from each adjacent set of multiple blades.5. The system of claim 1 , further comprising:pump means for moving fluid through the conduit and the chamber.6. The system of claim 1 , further comprising:a generator connected to receive energy from the rotatable impe7. A system comprising:a fluid conduit having a first diameter;a cylindrical chamber coaxially mounted in the fluid conduit, the chamber having a second diameter greater than the first diameter;an inlet at a first end of the chamber, the inlet having the first diameter and being connected to the fluid conduit;an outlet at a second end of the chamber ...

METHOD FOR BALANCING THE OUT-OF-BALANCE OF A SHAFT/WHEEL ASSEMBLY

Disclosed is a method for balancing the out-of-balance of a shaft/wheel assembly. The balancing method involves a step of measuring the value of the out-of-balance of a wheel/shaft assembly with respect to a longitudinal axis of the mechanical shaft, and then measuring the position of at least two different target zones present on the surface of the wheel. The method involves removing material from the surface of the vaned wheel in order to reduce the value of the out-of-balance of the shaft/wheel assembly depending on the measurements taken in steps a) and b). In this way, the balancing method is much more precise compared with the prior art. 1. A method for balancing the out-of-balance of a shaft-wheel assembly , comprising a bladed wheel held at the end of a mechanical shaft , implementing the following steps:a) measuring the out-of-balance value of the shaft-wheel assembly with respect to a longitudinal axis of the mechanical shaft;b) measuring the position of at least two distinct target areas, present at the surface of the bladed wheel, with respect to a longitudinal axis of the mechanical shaft; thenc) removing a quantity of material at the surface of the bladed wheel, to reduce the out-of-balance value of the shaft-wheel assembly, as a function of the measurements made at steps a) and b).2. The balancing method according to claim 1 , wherein the target areas are present on one or several faces of the turbine wheel claim 1 , extending radially or substantially radially with respect to the mechanical shaft.3. The balancing method according to claim 1 , wherein the target areas are present on a same face of the bladed wheel.4. The balancing method according to claim 1 , wherein the target areas are spaced from the mechanical shaft by an identical or substantially identical distance.5. The balancing method according to claim 1 , wherein the target areas are spaced from the mechanical shaft by a distance between 0.7 and 0.99 times the value of the largest radius ...

METHOD AND DEVICE FOR SECURING A THREADED ELEMENT SCREWED INTO A THREADED SEAT, METHOD FOR MOUNTING AT LEAST ONE BALANCING WEIGHT OF A TURBINE, AND A TURBINE

A method for securing a threaded element screwed into a threaded seat wherein the threaded element is at least partially plastically deformed by a deformation element of a tool such that the threaded element is subsequently arranged secured against rotation in the threaded seat. The tool is thereby placed axially in front of the threaded element in that a guide element of the tool is inserted axially in a drive mount of the threaded element, wherein the deformation element thus placed axially in front of the threaded element is accelerated in the direction of the threaded element, and wherein the deformation element shifts relatively with respect to the guide element inserted in the drive mount such that at least the first thread of the threaded element and/or the threaded seat facing the tool is deformed by the deformation element in order to secure the threaded element in the threaded seat. 1. A method for securing a threaded element that is screwed into a threaded balancing weight seat of a turbine arrangement and that is configured as a mounting screw , the method comprising:at least partially plastically deforming at least the threaded element screwed into the threaded balancing weight seat by means of deforming means of a tool such that it is then arranged in a rotationally secure manner in the threaded balancing weight seat,placing the tool axially in front of the threaded element, in that a guide element of the tool is plugged axially into a drive recess of the threaded element,accelerating the deforming means placed axially in front of the threaded element in the direction of the threaded element, andmoving the deforming means move relative to the guide element plugged into the drive recess such that at least the first thread turn, oriented toward the tool, of the threaded element and/or of the threaded balancing weight seat is deformed by the deforming means in order to secure the threaded element in the threaded balancing weight seat.2. A method for ...

Turbine wheels, turbine engines including the same, and methods of fabricating turbine wheels with improved bond line geometry

Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.

High temperature low friction coating layer and the method of the same

Disclosed are a coating layer having excellent low-friction ability at a high temperature and a method of forming the coating layer. The high-temperature low-fiction coating layer may improve heat resistance, fatigue resistance, low-friction ability, and seizure resistance of the turbine wheel of a turbocharger and the parts sliding at a high temperature in the exhaust system of an engine, improve turbo-lag, and improve durability of the high-temperature parts in the exhaust system of an engine. The high-temperature low-friction coating layer includes: a CrN bonding layer 110 disposed on a nitrified base material 100; a TiAlCrYN nano-multi-support layer 120 disposed on the CrN bonding layer 110 to achieve heat resistance, fatigue resistance, wear resistance, and toughness of the coating layer; and a TiAlCrYCN nano-multi-function layer 130 disposed on the TiAlCrYN nano-multi-support layer 120 to achieve heat resistance, oxidation resistance, seizure resistance, toughness, and low-friction ability of the coating layer.

TURBINE SHROUD WITH MOVABLE ATTACHMENT FEATURES

A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity. 1. A segmented turbine shroud that extends around a central axis , the segmented turbine shroud comprisinga carrier segment that extends partway around the central axis and that forms a radially inwardly-opening cavity,a blade track segment comprising ceramic-containing materials, the blade track segment formed to include a runner that extends partway around the central axis and a positioner attachment post that extends radially outward from the runner into the radially inwardly-opening cavity of the carrier segment, the positioner attachment post formed to include a track-positioning surface that extends both radially and axially, anda track attachment system adapted to couple the blade track segment to the carrier segment, and the track attachment system including a positioner coupled to the carrier segment to move axially from a disengaged position out of contact with the positioner attachment post to an engaged position contacting the positioner attachment post to engage the track-positioning surface of the positioner attachment post with a position-setting surface that extends both radially and axially at an angle corresponding to that of the track-positioning surface.2. The segmented turbine shroud of claim 1 , wherein the position-setting surface is formed by the positioner.3. The segmented turbine shroud of claim 2 , wherein the positioner is formed to include positioner threads that engage corresponding threads formed in the carrier segment.4. The segmented turbine shroud of claim 1 , wherein the position-setting surface is formed by the carrier segment.5. The segmented turbine shroud of claim 1 , wherein the blade track segment ...

LINEAR MOTION MECHANISM, GOVERNING VALVE DRIVE DEVICE, AND STEAM TURBINE

A linear motion mechanism () is provided with: a cylinder rod () into which a ball screw () can be inserted, said cylinder rod () comprising a base end section that is connected to a nut () within a piston casing () and a tip section () that is exposed on the outside of the piston casing (); a nut-side grease supply hole () that is formed in the nut () and that comprises a discharge port () that opens toward the outer circumferential surface of the ball screw (); and a cylinder rod-side grease supply hole () that is formed in the cylinder rod (), that comprises on one end thereof an inlet () that opens at a position that is exposed to the outer section of the piston casing (), and that comprises another end () that is connected to the nut-side grease supply hole (). 1. A linear motion mechanism , comprising:an electric motor;a ball screw which is rotationally driven around an axis by the electric motor;a nut which is screwed into the ball screw, and advances and retreats relative to the ball screw in an axial direction of the ball screw according to rotation of the ball screw;a casing which surrounds the ball screw and the nut;a tubular cylinder rod which includes a base end section which is connected to the nut inside the casing and a tip section which is exposed to the outside of the casing, and into which the ball screw can be inserted;a nut-side grease supply hole which is formed in the nut and includes a discharge port which opens toward an outer circumferential surface of the ball screw; anda cylinder rod-side grease supply hole which is formed in the cylinder rod, and includes an inlet which opens at a position exposed to the outside of the casing on one end of the cylinder rod-side grease supply hole, and the other end thereof which communicates with the nut-side grease supply hole.2. The linear motion mechanism according to claim 1 , further comprising:a grease supply pipe which is connected to the inlet of the cylinder rod-side grease supply hole and has ...

Airfoil with Thickened Root and Fan and Engine Incorporating Same

In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater. 1. An airfoil , comprising:a platform; anda blade extending from the platform, where the blade has a root proximate the platform and a tip radially outward from the platform, the root having a greater thickness than a cross-section at about a quarter-span of the blade or greater.2. The airfoil of claim 1 , wherein the root of the blade has a thickness about twenty percent greater than a cross-section at about a quarter-span of the blade or greater.3. The airfoil of claim 1 , wherein the root of the blade includes about twenty-five percent of a radial height of the blade.4. The airfoil of claim 1 , further including a transition zone between the tip and the root of the blade claim 1 , the transition zone being aerodynamically smooth.5. The airfoil of claim 1 , further including a fillet joining the blade with the platform of the airfoil.6. The airfoil of claim 5 , wherein the fillet has a width that varies along an axial length of the blade.7. The airfoil of claim 6 , wherein the blade includes a leading edge claim 6 , a central portion claim 6 , and a trailing edge; the leading edge interacting with incoming airflow before other surfaces of the blade claim 6 , the trailing edge interacting with outgoing airflow claim 6 , and the central portion extending between the leading and trailing edges; and the leading and trailing edges of the blade have a steeper fillet than that of the central edge of the blade.8. A fan of a gas turbine engine claim 6 , comprising:a hub; anda plurality of airfoils radially extending from the hub, each airfoil having a platform and a blade radially extending from the platform, the blade having ...

VARIABLE SPAN SPLITTER BLADE

The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade. 1. A compressor for a gas turbine engine , the compressor comprising:a flow passage shroud; anda splitter blade disposed adjacent the flow passage shroud, wherein the splitter blade includes a leading edge, a trailing edge, and a chord length;wherein a clearance between the splitter blade and the flow passage shroud is variable along the chord length of the splitter blade.2. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly.3. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies nonlinearly.4. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly in at least one segment and nonlinearly in at least another segment.5. The compressor of claim 1 , further comprising:a flow passage hub;wherein the clearance at the leading edge is approximately 50% of a first span between the flow passage hub and the flow passage shroud at the leading edge; andwherein the clearance at the trailing edge is approximately less than 1.5% of a second span between the flow passage hub and the flow passage shroud at the trailing edge.6. ...

ROTOR AND GAS TURBINE ENGINE INCLUDING SAME

A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, adjacent ones of the plurality of blades are joined by a flexible web. 1. A rotor for a gas turbine engine comprising:a rotor disk defined along an axis of rotation; anda plurality of blades which extend from said rotor disk; anda plurality of flexible webs, each of said plurality of flexible webs joining two of said plurality of blades.2. The rotor of claim 1 , wherein each of said plurality of flexible webs comprises:a first arm including a first arm proximal end operatively coupled to a first one of the plurality of blades, the first arm further including a first arm distal end; anda second arm including a second arm proximal end operatively coupled to a second one of the plurality of blades, the second arm further including a second arm distal end operatively coupled to the first arm distal end.3. The rotor of claim 2 , further comprising a radiused joint operatively coupling the first arm distal end to the second arm distal end.4. The rotor of claim 2 , wherein the first arm and the second arm each extend radially inboard.5. The rotor of claim 1 , wherein each of said plurality of blades includes a platform section.6. The rotor of claim 5 , wherein each of said plurality of flexible webs comprises:a first arm including a first arm proximal end operatively coupled to a first platform section of a first one of the plurality of blades, the first arm further including a first arm distal end; anda second arm including a second arm proximal end operatively coupled to a second platform section of a second one of the plurality of blades, the second arm further including a second arm distal end operatively coupled to the first arm distal end.7. The rotor of claim 6 , further comprising a radiused joint operatively coupling the first arm distal end to the second arm distal end.8. The rotor of claim 6 , wherein the first arm and the second arm each extend radially inboard.9. ...

Hollow Fan Blade with Extended Wing Sheath

A fan blade for a turbomachinery fan and methods for fabricating a fan blade for a turbomachinery fan are disclosed. The fan blade for a turbomachinery fan includes an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side. The fan blade includes a sheath including a solid portion that covers the leading edge of the airfoil, a first wing attached to the suction side of the airfoil, and a second wing attached to the pressure side of the airfoil. Construction of the fan blade includes one or more hollow cavities between the suction side and the pressure side of the airfoil. 1. A gas turbine engine fan blade , the fan blade comprising:an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side;a sheath comprising a solid portion that covers the leading edge of the airfoil; anda blade body between the suction side and the pressure side of the airfoil, wherein the blade body defines a cavity.2. The fan blade of claim 1 , wherein the cavity is filled with a material having a lighter density than the airfoil.3. The fan blade of claim 2 , wherein the material having a lighter density than the airfoil is a hybrid metallic substance.4. The fan blade of claim 1 , wherein the airfoil is constructed from aluminum.5. The fan blade of claim 4 , wherein the cavity are filled with a hybrid metallic substance having a lower density than aluminum.6. The fan blade of claim 1 , wherein at least one of the first wing and the second wing of the sheath extends over at least about 35% of the airfoil in a chordwise direction.7. The fan blade of claim 6 , wherein the at least one of the first wing and the second wing extends over at least about 35% of the airfoil in a chordwise direction in a region of the airfoil near the tip of the airfoil.8. The fan blade of claim 1 , wherein the cavity is located ...

Aluminum Fan Blades with Root Wear Mitigation

A fan blade assembly with wear mitigation characteristics is disclosed. In a titanium hub, dovetail shaped slots are used for accommodating dovetail shaped roots of fan blades. At least the inwardly facing walls of the dovetail shaped slots are coated with a dry film lubricant. The inwardly directed pressure faces of the dovetail shaped root of the fan blades are covered with polymeric wear mitigation pads. The combination of wear mitigation pads on the pressure faces of the root of the fan blade in combination with a dry film lubricant coating on the inwardly directed walls of the dovetail shaped slots in the hub provide excellent wear mitigation characteristics and prolong the life of the fan blades. 1. A fan blade assembly comprising:a disk shaped hub including an outer periphery including a plurality of circumferentially spaced dovetail shaped slots extending radially inwardly through the outer periphery of the hub;each slot including an inner surface disposed between and connected to a pair of slanted walls that extend towards each other as they extend radially outwardly from the inner surface of the slot towards the outer periphery of the hub, the slanted walls being coated with a lubricant;a plurality of fan blades, each fan blade including a dovetail shaped root received within one of the slots of the hub, each dovetail shaped root including an inner face disposed between and connected to a pair of slanted pressure faces that extend towards each other as they extend radially outwardly from the inner face, the inwardly slanted pressure faces being at least partially covered with at least one wear mitigation pad.2. The assembly of wherein the fan blade is fabricated from an aluminum alloy.3. The assembly of wherein the fan blade is fabricated from a titanium alloy.4. The assembly of wherein the hub is fabricated from a titanium alloy.5. The assembly of wherein the fan blade is fabricated from an aluminum alloy and the hub is fabricated from a titanium alloy.6. ...

Turbocharger

A turbocharger includes: an annular diffuser flow passage formed by two opposed surfaces of a compressor housing and a bearing housing; and a seal plate located inside of the diffuser flow passage in a radial direction, and disposed to be opposed to a back surface of a compressor wheel. A gap in the radial direction is formed between a radially inside end of the opposed surface of the bearing housing that forms the diffuser flow passage and an outer peripheral edge of the compressor wheel. The seal plate has a larger diameter than that of the compressor wheel. A protrusion, which extends more to the compressor housing side than does a region opposed to a back surface of the compressor wheel, is provided in a region of the seal plate facing the gap.

Turbocharger Having Improved Rupture Containment

A turbocharger for a powered machine including a turbine is disclosed. The turbocharger may include a turbine wheel including a disk section, the disk section including a disk body, the disk body including a length extending between a longitudinal axis and a blade platform. The disk section may further include a shoulder section positioned radially outward the longitudinal axis, a neck section positioned radially outward the shoulder section and a throat section positioned radially outward the neck section, an upstream axial plane coextensive with an upstream side of the blade platform, a downstream axial plane coextensive with a downstream side of the blade platform. Further, the turbine burst shield section may have a geometry that peaks in depth in the burst plane which prevents ejection of secondary mass in the event of a turbine burst.

THERMALLY CONFORMABLE LINER FOR REDUCING SYSTEM LEVEL FAN BLADE OUT LOADS

A fan case for a gas turbine engine includes a fan case surrounding a fan with fan blades. A liner is disposed between the fan case and the fan and is spaced a radial distance from the fan case. A torque stop is arranged between the fan case and the liner. A method for reducing fan case liner loads is also disclosed. 1. A fan section for a gas turbine engine , comprising:a fan case surrounding a fan with fan blades;a liner disposed between the fan case and the fan, spaced a radial distance from the fan case; andat least one torque stop arranged between the fan case and the liner.2. The fan section of claim 1 , wherein the ratio of the radial distance to a radius of the fan blades is 0.25:40.3. The fan section of claim 1 , wherein at least one of a radially inner surface of the fan case and a radially outer surface of the liner includes a low-friction coating.4. The fan section of claim 3 , wherein the low-friction coating is a Teflon® spray.5. The fan section of claim 1 , wherein the at least one torque stop is frangible.6. The fan section of claim 1 , wherein the at least one torque stop prevents rotation of the liner relative to the fan case.7. The fan section of claim 1 , wherein at least a portion of the liner is bonded to the fan case with an adhesive.8. The fan section of claim 7 , wherein the at least one torque stop and the adhesive can withstand a tangential load given by the equation (1+S)*T/R/Nwhere S is a safety factor claim 7 , Tis a rub torque generated by a 2.5 lb (1.3 kg) bird strike claim 7 , Ris a radius of the fan case claim 7 , and Nis the number of torque stops.9. The fan section of claim 8 , wherein S is 0.35.10. The fan section of claim 1 , wherein the liner includes one or more rails which contact the fan case.11. The fan section of claim 1 , wherein the liner includes an abradable rubstrip adjacent to tips of the fan blades.12. The fan section of claim 11 , wherein the abradable rubstrip is arranged radially inward from the at least one ...

FAN DRIVE GEAR SYSTEM SPLINE OIL LUBRICATION SCHEME

An input coupling for a fan drive gear system includes features for maintaining lubricant within a splined interface. The fan drive gear system includes a gear rotatable about an axis that includes an inner spline. The input coupling includes an outer spline engaged to the inner spline of the gear. The input coupling includes an aft oil dam for maintaining lubricant within an interface between the outer spline and the inner spline. 1. A fan drive gear system comprising:a gear rotatable about an axis, the gear including an inner spline; andan input coupling including an outer spline engaged to the inner spline of the gear, the input coupling including an aft oil dam for maintaining lubricant within an interface between the outer spline and the inner spline.2. The fan drive gear system as recited in claim 1 , wherein the gear includes a forward tab extending radially inward from an inner surface of the gear forward of the inner spline.3. The fan drive gear system as recited in claim 1 , wherein the gear includes an aft tab extending radially inward from an inner surface of the gear aft of the inner spline and forward of the aft oil dam.4. The fan drive gear system as recited in claim 1 , wherein the aft oil dam includes a retaining ring supported within an annular channel of the input coupling.5. The fan drive gear system as recited in claim 4 , wherein the retaining ring extends radially outward into contact with an inner surface of the gear.6. The fan drive gear system as recited in claim 1 , wherein the gear comprises a sun gear.7. The fan drive gear system as recited in claim 1 , wherein the input coupling includes at least one U-shaped portion for accommodating relative movement and misalignment with the gear.8. A geared turbofan engine comprising:a fan rotatable about an engine axis;a core engine including a turbine section driving a turbine shaft;a gearbox including a sun gear driven by the turbine shaft; andan input coupling transferring power between the ...

Fan Axial Containment System

A gas turbine engine () and method for containing a fan inside an engine after a fan thrust bearing assembly failure. The engine () may comprise a fan (), a housing () including a compartment (), a fan shaft () inside the compartment () and comprising a bowl (), a support structure () inside the compartment (), a speed sensor pickup () mounted on the outer surface () of the bowl (), a speed sensor () mounted on the support structure (), and a fan thrust bearing assembly () disposed forward of the bowl (). The fan thrust bearing assembly () including a bearing (). The speed sensor () and the sensor pickup () define a defining a sensor gap (). The bearing () and the outer surface () defining a fan thrust bearing gap (), wherein the sensor gap () is less than the fan thrust bearing gap. 1. A gas turbine engine disposed about a longitudinal engine axis (A) , the engine comprising:a fan;an exterior housing including an interior compartment disposed adjacent to the fan;a fan shaft disposed inside the compartment, the fan shaft configured to drive the fan, the fan shaft comprising an elongated pole and a bowl, the bowl including an outer surface and an inner surface;a fan bearing support structure disposed inside the compartment;a speed sensor pickup mounted on the outer surface of the bowl;a speed sensor mounted on the fan bearing support structure, the speed sensor and the sensor pickup defining a sensor gap in the axial direction; anda fan thrust bearing assembly disposed forward of the bowl, the fan thrust bearing assembly including a bearing, the bearing and the outer surface of the bowl defining in the axial direction a fan thrust bearing gap, wherein the sensor gap is less than the fan thrust bearing gap.2. The gas turbine engine of claim 1 , in which the fan thrust bearing assembly includes mounting hardware claim 1 , wherein the fan thrust bearing assembly is disposed adjacent to the pole and is mounted below the speed sensor to the fan bearing support structure ...

UNDULATING STATOR FOR REDUCING THE NOISE PRODUCED BY INTERACTION WITH A ROTOR

A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided. 1. Assembly comprising one or more rotors which share the same axis of rotation , and at least one stator which is designed to be placed radially in a flow which passes through said rotor(s) upstream or downstream thereof , said stator having a leading edge and a trailing edge , said leading edge and trailing edge being connected by a lower face and an upper face , wherein at least one of the faces of said stator has radial undulations which extend axially from the leading edge to the trailing edge , said radial undulations having at least two bosses in the same azimuth direction , the amplitude of which is at least one centimeter on at least part of the axial length of the stator , and in that , with the assembly being designed such that the crossing of said flow by the stator creates on said undulating surface pressure fluctuations with oscillations of the temporal phase according to the radial position , the radial undulations of said face have azimuth maximums and/or minimums in the vicinity of the zero mean dephasing regions for the pressure on the undulating face.2. Assembly according to claim 1 , wherein the radial undulations have a wavelength which is substantially constant along the radial extension of the stator.3. Assembly according to claim 1 , wherein the amplitude ...

INTERLOCKING ROTOR ASSEMBLY WITH THERMAL SHIELD

A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with. 1. A rotor assembly comprising:a first rotor;a second rotor mounted on the first rotor and co-rotatable there with; anda thermal shield interlocked with the second rotor for co-rotation there with.2. The rotor assembly as recited in claim 1 , wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter.3. The rotor assembly as recited in claim 1 , wherein the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor.4. The rotor assembly as recited in claim 3 , wherein the at least one radially-extending tab of the second rotor includes a step.5. The rotor assembly as recited in claim 1 , wherein the second rotor includes a plurality of radially-extending circumferentially-spaced tabs and the thermal shield includes a plurality of radially-extending circumferentially-spaced tabs circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the second rotor.6. The rotor assembly as recited in claim 5 , wherein the first rotor includes a plurality of radially-extending circumferentially-spaced tabs and the plurality of radially-extending circumferentially-spaced tabs of the second rotor are circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the first rotor.7. The rotor assembly as recited in claim 6 , wherein the plurality of radially-extending circumferentially-spaced tabs of the thermal shield are circumferentially aligned with the plurality of radially-extending circumferentially-spaced tabs of the first rotor.8. The rotor assembly as ...

Compartment Shielding

A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer. 1. A gas turbine engine having an engine axis , the engine comprising:a gas generator that includes a core flow path;a propulsor that includes a fan and geared architecture for driving the fan; anda housing defining a first compartment that separates the geared architecture and the core flow path, the housing including a shielded axial mid-section that includes an outer layer and an insulator adjacent to the outer layer, the mid-section in thermal communication with the core flow path of the gas generator.2. The gas turbine engine of claim 1 , wherein the insulator is a foam insulator.3. The gas turbine engine of claim 1 , wherein the insulator is ceramic.4. The gas turbine engine of claim 1 , in which the mid-section further includes an inner layer claim 1 , wherein the insulator is disposed between the outer layer and the inner layer.5. The gas turbine engine of claim 4 , wherein the insulator is air.6. The gas turbine engine of claim 4 , wherein the insulator is air under vacuum pressure.7. The gas turbine engine of claim 1 , in which the mid-section further includes an inner layer and a second insulator claim 1 , wherein the first and second insulators are disposed between the ...

Multi-stage turbocharger system

A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger ( 1 ) and a second relatively large low pressure (LP) turbocharger ( 2 ). The turbine ( 6 ) of the LP turbocharger ( 2 ) is connected in series downstream of the turbine ( 4 ) of the HP turbocharger ( 1 ) in a first exhaust gas passage ( 11 ). An exhaust bypass flow passage ( 12 ) provides a bypass flow path around the HP turbine ( 4 ). A rotary valve ( 8 ) is located at a junction of the bypass flow passage ( 12 ) and a first exhaust gas flow passage ( 11 ). The rotary valve ( 8 ) comprises a valve rotor ( 19 ) which is rotatable to selectively permit or block flow to the LP turbine ( 6 ) from either the first exhaust gas passage ( 11 ) or the bypass gas passage ( 12 ).

ELECTRIC ROTOR FIT ONTO A TURBOMACHINE SHAFT

By relieving the shaft of an electronically-controlled turbocharger (ECT) in a central region of where a rotor of an electric machine couples with the shaft eases assembly of the electric machine onto the shaft. On either side of the relieved section, the fit between the shaft and the rotor may be a slip fit or an interference fit. Alternatively, the rotor is relieved in a central section. In some embodiments, the shaft is welded to the rotor. In yet other embodiments, the outside of the shaft and the inside of the rotor are threaded with a nut or a pin to secure the shaft to the rotor or the rotor itself has threads to engage with threads on the shaft. Such arrangements ease assembly and allow adjustment of dynamic characteristics of the rotor system. 1. An electronically-controlled turbomachine , comprising:a shaft having a turbine wheel coupled to a first end of the shaft;a turbine housing section disposed over the turbine wheel;a compressor wheel secured to a second end of the shaft;a compressor housing section disposed over the compressor wheel; andan electric machine disposed on the shaft and located between the turbine and the compressor sections, wherein: the electric machine comprises a rotor and a stator; the rotor is fixed onto a portion of the shaft; the portion of the shaft has first, second, and third axial sections; the inside diameter of the rotor is greater than a diameter of the second axial section; and the second axial section is located between the first and third axial sections.2. The turbomachine of wherein the inside diameter of the rotor is substantially equal to an outside diameter of the shaft along the first and third axial sections.3. The turbomachine of wherein an end of the rotor proximate the first section of the shaft is welded to the shaft and the weld is by one of electron beam welding claim 2 , laser welding claim 2 , and tungsten inert gas welding.4. The turbomachine of wherein the shaft and rotor are welded by one of ultrasonic ...

GAS TURBINE ENGINE INLET

A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5. 1. A gas turbine engine comprising:a fan nacelle and a core nacelle providing a bypass flow path radially between, the fan nacelle having an inlet including a throat, the inlet having an inlet forward-most point;a fan arranged in the bypass flow path and rotatable about an axis, the fan having a leading edge recessed from the inlet forward-most point an inlet length in an axial direction;a spinner having a spinner length from a spinner forward-most point to the leading edge; anda ratio of the spinner length to inlet length is equal to or greater than about 0.5.2. The gas turbine engine according to claim 1 , comprising a plane at the throat and a fan hub supporting the fan claim 1 , and a spinner mounted on the fan hub forward of the fan claim 1 , at least a portion of the spinner arranged forward of the plane.3. The gas turbine engine according to claim 2 , wherein a spinner forward-most point is arranged forward of the plane and aft of a forward-most point of the inlet.4. The gas turbine engine according to claim 1 , wherein the ratio is about 0.655. The gas turbine engine according to claim 1 , wherein the length extends from a fan blade leading edge forward-most point to the inlet forward-most point.6. The gas turbine engine according to claim 1 , wherein the fan includes a diameter claim 1 , and a ratio of the inlet length to diameter is equal to or less than about 0.4.7. The gas turbine engine according to ...

METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS

A gas turbine engine is provided comprising a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said compressor section. 1. A gas turbine engine comprising:a compressor section;a combustor section;a diffuser case module with a multiple of struts within an annular flow path from said compressor section to said combustor section, at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path; anda manifold in communication with said mid-span pre-diffuser inlet and said compressor section.2. The gas turbine engine as recited in claim 1 , wherein said manifold communicates a temperature tailored airflow.3. The gas turbine engine as recited in claim 1 , wherein said manifold communicates a temperature tailored airflow thru a heat exchanger.4. The gas turbine engine as recited in claim 3 , wherein said manifold communicates said temperature tailored airflow from said heat exchanger as buffer air.5. The gas turbine engine as recited in claim 4 , wherein said buffer air is communicated thru a buffer passage to one or more bearing compartments.6. The gas turbine engine as recited in claim 1 , wherein said mid-span pre-diffuser inlet supplies a temperature tailored airflow into said manifold.7. The gas turbine engine as recited in claim 1 , wherein said manifold communicates with a high pressure turbine of said compressor section.8. The gas turbine engine as recited in claim 1 , wherein said manifold is generally annular.9. The gas turbine engine as recited in claim 1 , wherein said manifold communicates with a row of rotor blade attachments in ...

TURBINE ASSEMBLY MAINTENANCE METHODS

The present invention is directed to in situ methods for maintaining turbine assemblies. One such method includes: disposing a maintenance apparatus on the rotor; positioning the maintenance apparatus proximate to the damaged region by rotating the rotor; and repairing the damaged region by operating a repair tool disposed on the apparatus. Another method includes: disposing a maintenance apparatus on the stator; positioning the damaged region proximate to the maintenance apparatus by rotating the rotor; and repairing the damaged region by operating a repair tool disposed on the apparatus. 1. A method for maintenance of a turbine assembly , the turbine assembly comprising a rotor and a stator , the stator comprising a damaged region , the method comprising:disposing a remotely controllable maintenance apparatus on the rotor;positioning the maintenance apparatus proximate to the damaged region by rotating the rotor; andrepairing the damaged region by operating a repair tool disposed on the apparatus.2. The method of claim 1 , wherein a camera is disposed on the apparatus claim 1 , wherein the camera is operable to remotely transmit visual data to a receiver.3. The method of claim 2 , wherein the camera is operable to wirelessly transmit visual data to a receiver.4. The method of claim 1 , further comprising anchoring the apparatus subsequent to disposing of the apparatus.5. The method of claim 1 , wherein operating the repair tool comprises remotely transmitting a control signal to the apparatus.6. The method of claim 5 , wherein operating the repair tool comprises wirelessly transmitting a control signal to the apparatus.7. The method of claim 1 , wherein operating the repair tool comprises removing material from the damaged region.8. The method of claim 1 , wherein operating the repair tool comprises disposing a repair material on the damaged region.9. The method of claim 1 , wherein operating the repair tool comprises moving the repair tool relative to the damaged ...

SEGMENTED FACE SEAL ASSEMBLY AND AN ASSOCIATED METHOD THEREOF

A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. 1. A turbomachine comprising:a stator;a rotor comprising a rotor bearing face; and a first segmented seal ring comprising a plurality of joints and a first flat-contact surface; and', 'a second segmented seal ring comprising a plurality of segment ends and a second flat-contact surface,, 'a face seal assembly comprisingwherein one of the first segmented seal ring and the second segmented seal ring comprises a seal bearing face, wherein the second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface, wherein the plurality of segment ends is circumferentially offset from the plurality of joints, and wherein the first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor bearing face and the seal bearing face.2. The turbomachine of claim 1 , wherein the first segmented seal ring further comprises a circumferential slot extending inwards from a first peripheral side towards a second peripheral side of the first ...

TURBINE ENGINE WHEEL

The invention relates to a wheel of a turbine engine comprising a plurality of radially extending vanes, one radially internal or external end of which is connected to an annular platform carrying annular lips () extending from said platform in a direction opposite the vane in order to sealingly cooperate with a radially facing abradable material (). According to the invention, the wheel comprises at least one lip () having a concave curved upstream face and a convex curved downstream face or having a convex curved upstream face and a concave curved downstream face. 1. A wheel of a turbine engine comprising a plurality of radially extending vanes , one radially internal or external end of which is connected to an annular platform carrying annular lips extending from said platform in a direction opposite the vane in order to sealingly cooperate with a radially facing ring , characterized in that it comprises at least one lip having a concave curved upstream face and a convex curved downstream face or having a convex curved upstream face and a concave curved downstream face.2. A wheel according to claim 1 , wherein each lip has a first radial end connected to the platform and a second radial end opposed to said first end claim 1 , with said first end being arranged downstream from the second end.3. A wheel according to claim 2 , wherein the generatrix of the cone of revolution going through the first end and the second end is inclined relative to a plane perpendicular to the axis of the wheel by a value strictly greater than 0° and smaller than or equal to 60° claim 2 , preferably between 15° and 45° and more preferably of the order of 30°.4. A wheel according to claim 2 , wherein the upstream and downstream faces of a lip have a substantially constant radius of curvature between the first end and the second end of a lip.5. A wheel according to claim 1 , wherein the lips radially extend outwards from an external annular platform.6. A wheel according to claim 1 , ...

FACE SEAL ASSEMBLY AND AN ASSOCIATED METHOD THEREOF

A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities. 1. A turbomachine comprising:a stator;a rotor comprising a rotor bearing face;a face seal assembly comprising a seal ring comprising a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face and wherein the face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor bearing face and the seal bearing face; anda second pressure cavity and a third pressure cavity defined by the stator, the rotor, and the face seal assembly, wherein the third pressure cavity is disposed downstream of the second pressure cavity with reference to a flow of a process fluid along the stator and the rotor, and wherein the first pressure cavity is isolated from the second and third pressure cavities.2. The turbomachine of claim 1 , further comprising:a fluid supply tube coupled to the first pressure cavity;a pressure-control device coupled to the fluid supply tube; anda control unit coupled to a pressure-control device and configured to control the pressure- ...

TURBOCHARGER BEARING ASSEMBLY AND METHOD FOR PROVIDING THE SAME

An integrated bearing assembly includes a thrust bearing disposed along a face of a turbocharger casing in a turbocharger and extending circumferentially around an axis of rotation of a rotor of the turbocharger, and a dual film journal bearing radially disposed between the rotor and the turbocharger casing. The journal bearing includes a shoulder step radially extending away from the rotor. The shoulder step of the journal bearing engages one or more of the thrust bearing or the turbocharger casing to prevent axial movement of the journal bearing relative to the one or more of the thrust bearing or the turbocharger casing. 1. An integrated bearing assembly comprising:a thrust bearing disposed along a face of a turbocharger casing in a turbocharger and extending circumferentially around an axis of rotation of a rotor of the turbocharger; anda dual film journal bearing radially disposed between the rotor and the turbocharger casing, wherein the journal bearing includes a shoulder step radially extending away from the rotor, wherein the shoulder step of the journal bearing engages one or more of the thrust bearing or the turbocharger casing to prevent axial movement of the journal bearing relative to the one or more of the thrust bearing or the turbocharger casing.2. The bearing assembly of claim 1 , wherein the thrust bearing includes a recess radially extending into the thrust bearing away from the rotor claim 1 , and wherein the shoulder step of the journal bearing extends into the recess.3. The bearing assembly of claim 2 , wherein the recess in the thrust bearing and the shoulder step in the journal bearing both circumferentially extend around the axis of rotation of the rotor claim 2 , wherein the shoulder step in the journal bearing and the recess in the thrust bearing include flat segments that mate with each other to prevent rotation of the journal bearing relative to the thrust bearing.4. The bearing assembly of claim 1 , wherein the shoulder step of the ...

Bearing device for load reduction

A bearing assembly for a gas turbine engine comprises a bearing; a bearing bracket, which holds the bearing and is secured by a predetermined breaking device on a connecting element, which can be connected or is connected to a support structure of the gas turbine engine; and a clutch for transmitting a torque from a first clutch element connected in a fixed manner to the rotor of the bearing to a second clutch element supported on the bearing bracket, wherein the clutch elements are spaced apart when the predetermined breaking device is intact and can be brought into contact with one another by destruction of the predetermined breaking device. A gas turbine engine and a method are furthermore provided.

Gas turbine

A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a part on the input shaft on the input side of the gearbox device.

Rotor Balance Weight System

A rotor has a rotor body having: a flange with a circumferential array of discontiguous apertures; and a surface spaced apart from the flange. One or more rotor balance weight assemblies each have a weight and a fastener. The weight has: a passageway having a first end and a second end; an internal thread along the passageway; and a boss at the first end of the passageway. The boss is in a respective one of the apertures. The fastener has: a shank having a first end and a second end and an external thread engaged to the passageway internal thread; an engagement feature at the shank first end for engagement by a tool to turn the fastener; and a head at the second end contacts the surface. 119.-. (canceled)20. A rotor body having:an axis;a flange with a circumferential array of apertures; anda surface spaced radially apart from the flange and having a plurality of recesses, each aligned with a respective associated one of the apertures.21. The rotor body of further comprising:a radial flange, the axial flange extending from a junction with the radial flange.22. The rotor body of further comprising:a shaft portion of the rotor body, the radial flange extending radially outward from the shaft portion.23. The rotor body of wherein:the circumferential array of apertures is 8-100 apertures.24. The rotor body of wherein:the circumferential array of apertures is 12-36 apertures.25. The rotor body of wherein:each said recess is blind.26. The rotor body of wherein:each said recess is doubly concave27. The rotor body of wherein:the circumferential array of apertures is 8-100 apertures.28. The rotor body of wherein:the circumferential array of apertures is 12-36 apertures.29. The rotor body of wherein:each said recess is blind.30. The rotor body of wherein:each said recess is doubly concave31. A rotor including the rotor body of and further comprising:a plurality of stages of blades. This is a continuation of U.S. patent application Ser. No. 15/841,882, filed Dec. 14, 2017, and ...

BALANCING OF A ROTATIONALLY SYMMETRICAL COMPONENT, PARTICULARLY A ROTOR COMPONENT

The invention relates to a method for determining a balancing removal process for a balancing device for balancing a rotationally symmetrical component, particularly a rotor component, particularly of a turbomachine, a combination of machining lengths and depths being calculated, taking into account a pre-defined maximum machining length and minimum machining depth, in such a way that, with reliable combinations for compensating the same unbalance, the machining length of the calculated combination is longer than the machining length of at least one other permissible combination and, at the same time, the machining depth of the calculated combination is shallower than the machining depth of said other combination.

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.

BALANCE CORRECTION DEVICE FOR ROTOR

An imbalance correction position of a turbine wheel head is irradiated with a laser beam so that an outer peripheral portion of the turbine wheel head is left, and a groove provided by the laser irradiation is provided so that a depth of the groove is shallower toward a side closer to an outer periphery of the turbine wheel head. This makes it possible to secure a strength of a base part of an outer peripheral portion (an outer wall) of the groove, thereby making it possible to restrain deformation of the outer peripheral portion of the groove due to a centrifugal force acting by rotation of the turbine wheel head. 1. A balance correction device for a rotor , the balance correction device correcting balance of the rotor , the balance correction device comprising:a rotary drive device configured to rotate the rotor around a rotation axis of the rotor;a laser irradiation device configured to remove a part of the rotor by irradiating the rotor with a laser beam from a rotation-axis direction of the rotor;a rotation angle sensor configured to detect a rotation angle of the rotor;an irradiation position setting device configured to set a laser irradiation position in a radial direction of the rotor; anda controller configured to:(i) control the rotary drive device, the laser irradiation device, and the irradiation position setting device;(ii) irradiate an imbalance correction position of the rotor with the laser beam based on an output of the rotation angle sensor so as to leave an outer peripheral portion of the rotor; and(iii) control a radial position of the laser irradiation position, a rotation speed of the rotor, and a laser output of the laser irradiation device so as to make a groove depth, in the rotation-axis direction, of a groove provided by the laser irradiation shallower toward a side closer to an outer periphery of the rotor.2. The balance correction device for the rotor claim 1 , according to claim 1 , wherein (i) control the rotation speed of the rotor ...

BALANCE CORRECTION DEVICE FOR ROTOR

A single-body balance correction range in which a weight has been removed by single-body balance correction performed on a turbine wheel (a rotor) as a single body is calculated, an assembly balance correction range is calculated in an assembled state of the turbine wheel, and assembly balance correction is performed in a case where the single-body balance correction range and the assembly balance correction range overlap each other, such that an outermost diameter of an arc-shaped assembly-balance correction groove provided by removal of an inner part of a turbine wheel head is smaller than a remaining height a of the single-body balance correction range. By such a correction process, it is possible to perform weight removal for assembly balance correction by excluding a range in which the weight has been removed by the single-body balance correction, thereby making it possible to restrain an indicated value of a weight removal amount from deviating from an actual weight removal amount. 1. A balance correction device comprising: (i) calculate a single-body balance correction range in which a weight has been removed by single-body balance correction performed on a rotor as a single body;', '(ii) calculate an assembly balance correction range in an assembled state of the rotor;', '(iii) calculate a remaining height of the single-body balance correction range from a rotation center of the rotor;', '(iv) perform assembly balance correction such that an inner part of the rotor relative to an outer peripheral edge of the rotor is removed in an arc shape around the rotation center of the rotor; and', '(v) perform assembly balance correction in a case where the single-body balance correction range and the assembly balance correction range overlap each other, such that an outermost diameter of an arc-shaped assembly-balance correction groove provided by the removal of the inner part of the rotor is smaller than the remaining height of the single-body balance correction ...

TOGGLE SEAL FOR A RIM SEAL

A toggle seal, for use with a rim seal, including: a seal body, a proximal end and a distal end, a first end seal extending in a first axial direction from the proximal end of the seal body, a second end seal extending in the first axial direction from the distal end of the seal body, a first protruding portion extending in a second axial direction from the proximal end, opposite of the first end seal, and a second protruding portion extending in the second axial direction from the distal end, opposite of the second end seal, wherein the first end seal is configured to operatively engage the wheel disk and the second end seal is configured to operatively engage the at least one blade. 1. A toggle seal for use with a wheel disk , the wheel disk carrying a plurality of blades and configured to rotate about a rotational axis , the toggle seal comprising:a seal body including a proximal end, a distal end, and a seal body axis extending substantially perpendicular to the rotational axis to define a first axial direction extending from a first side of the seal body axis and a second axial direction extending from a second side of the seal body axis;a first end seal extending in the first axial direction from the proximal end of the seal body;a second end seal extending in the first axial direction from the distal end of the seal body;a first protruding portion extending in the second axial direction from the proximal end, opposite of the first end seal; anda second protruding portion extending in the second axial direction from the distal end, opposite of the second end seal;wherein the first end seal is configured to operatively engage the wheel disk and the second end seal is configured to operatively engage the at least one blade.2. The seal of claim 1 , wherein at least one aperture is disposed in the seal body.3. The seal of claim 1 , wherein the first protruding portion is substantially rounded.4. The seal of claim 1 , wherein at least a portion of the first seal ...

Fbo torque reducing feature in fan shaft

A fan shaft includes a first end, a second end, and an axis, the fan shaft and configured to be coupled to a gear assembly of a gas turbine engine at the first end and to a fan more proximal to the second end than the first end such that in response to being coupled, the fan shaft can transfer torque from the gear assembly to the fan. At least one axial portion of the fan shaft satisfies the relationship 0.55 ≤ T * C J * τ ≤ 0.95 , where T represents peak torque during fan blade off, C represents a distance from a centerline of the gas turbine engine to an outer fiber of the fan shaft, J represents a polar moment of inertia of the fan shaft, and τ represents yield stress in shear of the fan shaft.

TURBINE WHEEL OF AN EXHAUST GAS TURBOCHARGER AND ASSOCIATED PRODUCTION METHOD

A turbine wheel for an exhaust gas turbocharger may include a body composed of a TiAl alloy via at least one of metal injection moulding, selective laser melting and electron beam melting. The body may include a plurality of blades each having an outlet blade root and an outlet blade tip disposed radially away from a rotation axis with respect to the outlet blade root. The body may have a quotient Q of a diameter ddefined by each of the outlet blade tips to a diameter ddefined by each of the oulet blade roots corresponding to the following relationship: Q=d/d 1. A turbine wheel for an exhaust gas turbocharger , comprising: a body composed of a TiAl alloy via at least one of metal injection moulding , selective laser melting and electron beam melting , the body including a plurality of blades each having an outlet blade root and an outlet blade tip disposed radially away from a rotation axis with respect to the outlet blade root , wherein the body has a quotient Q of a diameter ddefined by each of the outlet blade tips to a diameter ddefined by each of the outlet blade roots corresponding to the following relationship:{'br': None, 'i': Q=d', '/d, 'sub': S', 'N, '>3.85.'}2. An exhaust gas turbocharger , comprising: a turbine wheel composed of a TiAl alloy , the turbine wheel including a plurality of blades each having an outlet blade root and an outlet blade tip disposed radially away from a rotation axis with respect to the outlet blade root;{'sub': S', 'N, 'claim-text': {'br': None, 'i': Q=d', '/d, 'sub': S', 'N, '>3.85.'}, 'wherein the turbine wheel has a quotient Q of a diameter ddefined by each of the blade tips to a diameter ddefined by each of the outlet blade roots corresponding to the following relationship4. The method according to claim 3 , wherein the powdered metallurgy process is metal injection moulding claim 3 , and further comprising the steps of debinding and sintering the component.5. The method according to claim 3 , wherein the component is a ...

Full ring curvic seal

A shaft coupling between a first shaft and a second shaft includes a seal assembly to minimize leakage. The seal assembly includes a ring press fit against an inner surface of the first shaft and a clearance fit with an inner surface of the second shaft. A seal is supported between the ring and the inner surface of the second shaft.

Frangible Sheath for a Fan Blade of a Gas Turbine Engine

In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a blade extending radially outward from the rotor disk. The blade may have a leading edge and a sheath may extend along the leading edge of the blade. The sheath may be formed from a brittle material. 1. A rotor for a gas turbine engine , comprising:a rotor disk; anda blade extending radially outward from the rotor disk, the blade having a leading edge; anda sheath extending along the leading edge of the blade, the sheath being formed from a brittle material.2. The rotor of claim 1 , wherein an adhesive joins the sheath to the leading edge of the blade.3. The rotor of claim 1 , wherein the brittle material is an aluminum alloy.4. The rotor of claim 1 , wherein the brittle material is a fiber-reinforced composite.5. The rotor of claim 1 , wherein the rotor is a fan of the gas turbine engine.6. The rotor of claim 1 , where the blade is made of aluminum.7. A gas turbine engine claim 1 , comprising:a fan section having a disk and a plurality of blades extending radially outward from the disk, each blade having a leading edge and a sheath extending along the leading edge of the blade, the sheath being formed from a brittle material;a compressor section downstream of the fan section;a combustor downstream of the compressor section; anda turbine section downstream of the combustor.8. The gas turbine engine of claim 7 , wherein an adhesive joins the sheath to the leading edge of the blade.9. The gas turbine engine of claim 7 , wherein the brittle material is an aluminum alloy.10. The gas turbine engine of claim 7 , wherein the brittle material is a fiber-reinforced composite.11. The gas turbine engine of claim 6 , wherein the blade is made of aluminum.12. A method of protecting a rotor of a gas turbine engine claim 6 , comprising:providing a rotor having a rotor disk and a plurality of blades extending radially outward from the rotor disk, ...

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 ...