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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Применить Всего найдено 1213. Отображено 100.
10-04-2003 дата публикации

Корпус цилиндра низкого давления паровой турбины

Номер: RU0000028732U1
Автор: Адамчук А.А., Егоров Н.П., Лисянский А.С., Рыбкин Н.С., Спиридонов А.Ф., Шкляров М.И., Юрьев Ю.Н.
Принадлежит: Открытое акционерное общество "Ленинградский Металлический завод"

Корпус цилиндра низкого давления паровой турбины, имеющий опоры и состоящий из частей, выполненных в виде половин, соединенных разъемом, нижние из которых имеют также встроенные в корпус цилиндра опоры ротора, соединенные с торцевой стенкой корпуса ЦНД жесткой связью, выполненной с усилением в виде металлической фермы, отличающийся тем, что корпус ЦНД дополнительно включает среднюю часть, при этом половины всех частей корпуса соединяют между собой горизонтальным разъемом, а нижние части, имеющие встроенные опоры ротора, жестко соединяют с левой и правой торцевыми стенками корпуса усилением, выполненным в виде продольно-поперечной металлоконструкции, включающей внутренние симметричные наклонные поперечные ребра жесткости, а также систему наружных симметричных продольных и поперечных ребер жесткости, выполненных в нижней и верхней половинах средней части корпуса цилиндра. (19) RU (11) 28 732 (13) U1 (51) МПК F01D 3/00 (2000.01) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К СВИДЕТЕЛЬСТВУ (21), (22) Заявка: 2002134295/20 , 23.12.2002 (24) Дата начала отсчета срока действия патента: 23.12.2002 (46) Опубликовано: 10.04.2003 (73) Патентообладатель(и): Открытое акционерное общество "Ленинградский Металлический завод" 2 8 7 3 2 R U (57) Формула полезной модели Корпус цилиндра низкого давления паровой турбины, имеющий опоры и состоящий из частей, выполненных в виде половин, соединенных разъемом, нижние из которых имеют также встроенные в корпус цилиндра опоры ротора, соединенные с торцевой стенкой корпуса ЦНД жесткой связью, выполненной с усилением в виде металлической фермы, отличающийся тем, что корпус ЦНД дополнительно включает среднюю часть, при этом половины всех частей корпуса соединяют между собой горизонтальным разъемом, а нижние части, имеющие встроенные опоры ротора, жестко соединяют с левой и правой торцевыми стенками корпуса усилением, выполненным в виде продольно-поперечной металлоконструкции, включающей внутренние ...

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Номер записи: 1
10-08-2008 дата публикации

РАБОЧЕЕ КОЛЕСО ВЕТРОДВИГАТЕЛЯ

Номер: RU0000075428U1
Автор: Пискунов Николай Иванович
Принадлежит: Общество с ограниченной ответственностью "Национальная инновационная компания "Новые энергетические проекты" (ООО "Национальная инновационная компания "НЭП")

1. Рабочее колесо ветродвигателя, состоящее из чашек-полусфер, радиальных горизонтальных траверс, прикрепленных к ступице, установленной на вертикальном валу, шарикоподшипников вертикального вала, отличающееся тем, что каждая чашка-полусфера снабжена стержнем, один из концов которого прикреплен к ободу чашки-полусферы, а другой конец стержня закреплен на корпусе пары подшипников, к которому присоединен вертикальный стержень, имеющий многократно превышающий вес чашки-полусферы груз, устанавливаемый в определенном месте на вертикальном стержне, причем стержни расположены под углом друг к другу, а чашка-полусфера при этом удалена от вертикального вала на большее расстояние, чем корпус пары подшипников, а сами подшипники расположены на горизонтальной оси, установленной на конце радиальной горизонтальной траверсы перпендикулярно к ее оси. 2. Рабочее колесо ветродвигателя, отличающееся тем, что вертикальный стержень на нижнем конце снабжен ограничительным элементом. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 75 428 (13) U1 (51) МПК F01D 3/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21), (22) Заявка: 2008112971/22 , 04.04.2008 (24) Дата начала отсчета срока действия патента: 04.04.2008 (45) Опубликовано: 10.08.2008 (73) Патентообладатель(и): Общество с ограниченной ответственностью "Национальная инновационная компания "Новые энергетические проекты" (ООО "Национальная инновационная компания "НЭП") (RU) U 1 7 5 4 2 8 R U Ñòðàíèöà: 1 U 1 Формула полезной модели 1. Рабочее колесо ветродвигателя, состоящее из чашек-полусфер, радиальных горизонтальных траверс, прикрепленных к ступице, установленной на вертикальном валу, шарикоподшипников вертикального вала, отличающееся тем, что каждая чашка-полусфера снабжена стержнем, один из концов которого прикреплен к ободу чашки-полусферы, а другой конец стержня закреплен на корпусе пары подшипников, к которому присоединен вертикальный стержень, имеющий ...

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Номер записи: 2
20-04-2010 дата публикации

НАСОС ПОГРУЖНОГО ТИПА ДЛЯ ПЕРЕКАЧКИ ЖИДКИХ МЕТАЛЛОВ

Номер: RU0000093121U1
Автор: Антоненков Максим Александрович, Баранова Валентина Сергеевна, Безносов Александр Викторович, Бокова Татьяна Александровна, Кузнецов Дмитрий Валерьевич
Принадлежит: Государственное образовательное учреждение высшего профессионального образования Нижегородский государственный технический университет им. Р.Е. Алексеева (НГТУ)

1. Насос погружного типа для перекачки жидких металлов, содержащий корпус, в котором установлен вал на верхнем подшипнике качения и нижнем подшипнике скольжения, выполненном из сопряженных и расположенных концентрично втулки вала и втулки подшипника с криволинейными каналами на их цилиндрических поверхностях, имеющими различное направление закрутки, отличающийся тем, что на внутренней и наружной поверхностях втулок вала и подшипника соответственно выполнена центральная проточка, сообщенная дросселирующими отверстиями с камерами, образованными поверхностью вала и втулки подшипника, не доходящими до ее верхнего и нижнего торцов в местах сопряжения втулок в нижней и верхней частях выполнены входные щели, сообщенные с объемом жидкого металла вне подшипника скольжения. 2. Насос по п.1, отличающийся тем, что направление закрутки каналов одной из поверхностей втулки вала совпадает с направлением вращения вала, а второй - противоположно ему, а направление закрутки каналов втулки подшипника противоположно направлению закрутки каналов на сопряженных поверхностях втулки вала. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 93 121 (13) U1 (51) МПК F01D 3/02 (2006.01) G21D 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21), (22) Заявка: 2009142228/22, 16.11.2009 (24) Дата начала отсчета срока действия патента: 16.11.2009 (45) Опубликовано: 20.04.2010 9 3 1 2 1 R U Формула полезной модели 1. Насос погружного типа для перекачки жидких металлов, содержащий корпус, в котором установлен вал на верхнем подшипнике качения и нижнем подшипнике скольжения, выполненном из сопряженных и расположенных концентрично втулки вала и втулки подшипника с криволинейными каналами на их цилиндрических поверхностях, имеющими различное направление закрутки, отличающийся тем, что на внутренней и наружной поверхностях втулок вала и подшипника соответственно выполнена центральная проточка, сообщенная дросселирующими отверстиями с ...

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Номер записи: 3
06-09-2017 дата публикации

ОПОРА РОТОРА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Номер: RU0000173697U1
Автор: Добриневский Анатолий Антонович, Назаренко Юрий Борисович, Никитин Александр Сергеевич
Принадлежит: Назаренко Юрий Борисович

Полезная модель относится к роторным газотурбинным машинам и может быть использована в конструкциях опор роторов, позволяющих регулировать осевые силы на радиально-упорном подшипнике. Применение опоры ротора позволяет регулировать осевые силы на одной из опор роторов с роликовым радиальным подшипником за счет гидродинамических сил радиального потока масла, проходящего с определенной скоростью в щелевом зазоре между кольцом, связанным со статором и торцом внутреннего кольца подшипника, и позволяет увеличить ресурс радиально-упорного подшипника, находящегося на другой опоре, за счет уменьшения осевой силы, действующей на него без изменения тяговых характеристик двигателя. Реализуемый конструкцией опоры метод компенсации осевых сил существенно упрощает монтаж опоры, не требует дополнительных энергетических затрат и сложных конструктивных решений, а использует кинетическую энергию масла, применяемого для смазывания и охлаждения подшипников, и позволяет отказаться от забора воздуха из газодинамического тракта и уплотнений между вращающимися частями ротора и статором при пневматическом или гидравлическом подходе компенсации сил, что повышает коэффициент полезного действия двигателя. 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 173 697 U1 (51) МПК F01D 3/04 (2006.01) F02C 7/06 (2006.01) F01D 25/16 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21)(22) Заявка: 2016148892, 13.12.2016 (24) Дата начала отсчета срока действия патента: 13.12.2016 Дата регистрации: Приоритет(ы): (22) Дата подачи заявки: 13.12.2016 (56) Список документов, цитированных в отчете о поиске: RU 159639 U1, 20.02.2016. SU (45) Опубликовано: 06.09.2017 Бюл. № 25 U 1 R U Стр.: 1 U 1 (54) ОПОРА РОТОРА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (57) Реферат: Полезная модель относится к роторным действующей на него без изменения тяговых газотурбинным машинам и может быть характеристик двигателя. Реализуемый использована в конструкциях опор роторов, конструкцией опоры ...

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Номер записи: 4
06-04-2018 дата публикации

Опора ротора газотурбинного двигателя

Номер: RU0000178526U1
Автор: Александр Сергеевич Никитин, Анатолий Антонович Добриневский, Юрий Борисович Назаренко
Принадлежит: Юрий Борисович Назаренко

Полезная модель относится к области машиностроения и может быть использована в конструкциях опор роторов высокооборотных газотурбинных двигателей (ГТД), в том числе авиационных.Опора ротора содержит корпус, в корпусе наружным кольцом смонтирован подшипник, внутреннее кольцо которого предназначено для монтажа полого вала ротора двигателя, на валу размещены маслоподводящие элементы, связанные гидравлическими каналами с полостью вала. На валу имеется фланец, к одному торцу которого поджато внутреннее кольцо подшипника, а со стороны другого торца размещено установленное на корпусе и поджатое к наружному кольцу подшипника кольцо, имеющее в зоне отверстия кольцевую отбортовку, внутренняя поверхность которой имеет коническую форму с расширением в сторону подшипника, коническая поверхность отбортовки, наружная поверхность вала и торцевая поверхность фланца образуют осевую масляную полость, выход маслоподводящих элементов размещен в зоне осевой масляной полости, причем между обращенными друг к другу торцами кольца и фланца образован радиальный кольцевой зазор, ширина которого уменьшается от оси подшипника к периферии, соединенный с осевой масляной полостью. 4 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 178 526 U1 (51) МПК F01D 3/04 (2006.01) F02C 7/06 (2006.01) F01D 25/16 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F01D 3/04 (2018.01); F02C 7/06 (2018.01); F01D 25/16 (2018.01) (21)(22) Заявка: 2017130832, 31.08.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): Назаренко Юрий Борисович (RU) 06.04.2018 (56) Список документов, цитированных в отчете о поиске: RU 134992 U1, 27.11.2013. RU 2613964 C1, 22.03.2017. RU 159639 U1, 20.02.2016. US 4578018 A1, 25.03.1986. (45) Опубликовано: 06.04.2018 Бюл. № 10 1 7 8 5 2 6 R U (54) ОПОРА РОТОРА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (57) Реферат: Полезная модель относится к области к наружному кольцу подшипника кольцо, машиностроения и ...

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Номер записи: 5
26-01-2012 дата публикации

Steam turbine and method for adjusting thrust forces thereof

Номер: US20120017592A1
Автор: Asaharu Matsuo, Takashi Maruyama
Принадлежит: Mitsubishi Heavy Industries Ltd

A steam turbine having at least a HP blade cascade, an IP blade cascade and a plurality of dummy members that are attached to a common rotor shaft, is provided with, but not limited to, a detection unit that detects a steam flow into an IP chamber, a pressure reducing unit that reduces a pressure difference between both sides of a target dummy member of said plurality of the dummy members when the steam flow into the IP chamber stops, the target dummy member having one side communicating with a part of the IP chamber, and a control unit that controls the pressure reducing unit based on a detection result obtained by the detection unit.

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Номер записи: 6
13-09-2012 дата публикации

Temperature reducing flange for steam turbine inlets

Номер: US20120228862A1
Автор: Christopher Walter Sullivan, David Welch, Edward Kudlacik
Принадлежит: General Electric Co

An intermediate, temperature reducing flange is inserted between an external steam (process) connection flange and first pressure vessel, or outer shell of a turbine or a second pressure vessel, or inner shell of the turbine. The temperature reducing flange has an integral portion that is exposed to an internal turbine area that is at a lower temperature than the steam in the steam inlet port of the turbine. This portion provides for a cooling effect, thus isolating the outer shell of the turbine from the high temperature of the steam pipe. Isolating the highest temperature connections from the remainder of the outer shell allows use of lower cost alloys for the outer shell.

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Номер записи: 7
13-06-2013 дата публикации

REDUCED LEAKAGE BALANCE PISTON SEAL

Номер: US20130149101A1
Автор: Clute Stephen G., Grosso Glenn R., Kuzdzal Mark J., Peer David J.
Принадлежит: DRESSER-RAND COMPANY

Balance piston assembly, apparatus, and methods are provided. The assembly includes a balance piston coupled to a rotatable shaft and configured to rotate therewith, the balance piston including a first shelf and a second shelf, the first and second shelves being axially-overlapping and radially-offset. The assembly also includes a seal including a first sealing surface configured to seal with the first shelf and a second sealing surface configured to seal with the second shelf. 1. A balance piston assembly , comprising:a balance piston coupled to a rotatable shaft and configured to rotate therewith, the balance piston including a first shelf and a second shelf, the first and second shelves being axially-overlapping and radially-offset; anda seal including a first sealing surface configured to seal with the first shelf and a second sealing surface configured to seal with the second shelf.2. The balance piston of claim 1 , wherein the seal has a substantially J-shape.3. The balance piston assembly of claim 1 , wherein the first shelf includes a plurality of teeth configured to seal with the first sealing surface.4. The balance piston assembly of claim 1 , wherein the seal further includes a third sealing surface disposed radially between the first and second sealing surfaces.5. The balance piston assembly of claim 4 , wherein the seal and the balance piston define a continuous flowpath between the first claim 4 , second claim 4 , and third sealing surfaces.6. The balance piston assembly of claim 4 , wherein the first shelf of the balance piston includes a radially-outer surface configured to seal with the first sealing surface and a radially-inner surface configured to seal with the third sealing surface.7. The balance piston assembly of claim 6 , wherein at least one of the radially-outer surface and the radially-inner surface includes a plurality of teeth.8. The balance piston assembly of claim 1 , wherein at least one of the first and second sealing surfaces ...

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Номер записи: 8
25-07-2013 дата публикации

Turbine

Номер: US20130189078A1
Автор: REINHOLD Björn, Schaake Thomas
Принадлежит: MAN Diesel & Turbo SE

A turbine includes a stator () and a rotor (); a plurality of turbine stages () through which a flow path of an operating fluid extends; an axial thrust balancing piston () arranged at the rotor and a first piston chamber () connected to one of the turbine stages () so that the operating fluid can be conveyed into the first piston chamber with a first fluid pressure, and a second piston chamber () has a counterpressure so that an axial thrust opposed to a flow direction of the operating fluid can be exerted on the rotor; and a pressure control device () connected to the second piston chamber. The pressure control device constructed to vary the counterpressure by controlled removal of fluid from the second piston chamber so that the axial thrust of the axial thrust balancing piston can be varied. 1. A turbine comprising:{'b': '10', 'a stator ();'}{'b': 20', '10, 'a rotor () rotatably bearing-supported in said stator ();'}{'b': 30', '20', '10', '20, 'a plurality of turbine stages () formed by said rotor () and said stator () and arranged successively along a longitudinal direction (LR) of said turbine and through which a flow path of an operating fluid extends for driving said rotor () in rotation;'}{'b': 40', '20', '40', '41', '30', '1', '51', '30', '1', '41', '42', '30', '20', '40, 'an axial thrust balancing piston () arranged at said rotor (), said axial thrust balancing piston () comprising on a first axial piston side a first piston chamber () connected to one of said turbine stages (.) via a first fluid line () so that the operating fluid can be conveyed from one turbine stage (.) into said first piston chamber () with a first fluid pressure and, on a second axial piston side remote of the first piston side, a second piston chamber () having a counterpressure that is lower than the first fluid pressure so that an axial thrust opposed to a flow direction of the operating fluid through said turbine stages () can be exerted on said rotor () by said axial thrust ...

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Номер записи: 9
14-11-2013 дата публикации

DOUBLE-WALLED TURBOCHARGER HOUSING, FLANGE AND CONNECTION THEREOF

Номер: US20130302159A1
Автор: Grussmann Elmar, Lesch Artur
Принадлежит:

A double-walled turbocharger housing made of sheet metal includes an inner sheet metal shell which conducts hot exhaust gases and a relatively cold outer sheet metal shell which is spaced apart from the inner sheet metal shell via an air gap. The double-walled turbocharger housing is connected to a bearing flange with a circumferential collar via a common welding seam. The bearing flange is provided with a collar on an outside which faces away from the hot exhaust gas. An outer end of the inner sheet metal shell is provided with a collar with which it embraces the outer sheet metal shell. Both sheet metal shells are connected with the collar of the bearing flange via a common welding seam, wherein an air gap is present between the inner sheet metal shell and the outer sheet metal shell up to the outer end of the inner sheet metal shell. 1. In combination:a double walled turbocharger housing, comprising an inner sheet metal shell, and an outer sheet metal shell spaced apart from the inner sheet metal shell via an air gap, said inner sheet metal shell having a collar on an outer end and embracing the outer sheet metal shell with the collar, said air gap extending up to an outer end of the inner sheet metal shell;a bearing flange having a collar on an outside facing away from hot exhaust gas; anda welding seam, joining the inner sheet metal shell and the outer sheet metal shell to the collar of the bearing flange.2. The combination of claim 1 , wherein the turbocharger housing is constructed for connection to a rotor group with adjustable turbine geometry via the bearing flange.3. The combination of claim 1 , wherein the air gap on the outer end of the inner sheet metal shell has a width of at least 1 mm.4. The combination of claim 1 , wherein the collar of the inner sheet metal shell is clamped between the outer sheet metal shell and the collar of the bearing flange.5. The combination of claim 4 , wherein the collar of the inner sheet metal shell is clamped between ...

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Номер записи: 10
05-12-2013 дата публикации

EXPANSION JOINT AND STEAM TURBINE SYSTEM INCLUDING THE SAME

Номер: US20130323027A1
Автор: Bando Yuji, Nagashima Jun, Nishijima Hiromu, Oshita Tomohiro, Shimakawa Tsukasa
Принадлежит:

An expansion joint that is provided between a steam turbine outlet and a condenser inlet, including: an upstream baffle tube that has one end secured to an upstream fixing end and the other end as a free end, and forms a steam channel; a downstream baffle tube that has one end secured to a downstream fixed end and the other end as a free end, the free end being relatively movable outside the free end of the upstream baffle tube; and a flexible cylinder that is formed of a non-metal material using a resin sheet, and deformable while airtightly surrounding the baffle tubes. 1. An expansion joint provided between a steam turbine outlet and a condenser inlet , comprising:an inner metal cylinder that has one end secured to an upstream fixing end and the other end as a free end, and that forms a steam channel;an outer metal cylinder that has one end secured to a downstream fixed end and the other end as a free end, the free end being movable relative to the inner metal cylinder at a radial outside of the free end of the inner metal cylinder; anda flexible cylinder that is formed of a non-metal material using a resin sheet and that is deformable while airtightly surrounding an outer portions of the inner metal cylinder and an outer portions of the outer metal cylinder.2. The expansion joint according to claim 1 , wherein the flexible cylinder includes a glass cloth stacked on the resin sheet.3. The expansion joint according to claim 1 , wherein the steam turbine and the condenser are components of a steam turbine system for driving machines mounted on a floating body or a ship for treating liquefied gas.4. A steam turbine system comprising:a steam turbine rotationally driven by steam;a condenser that condenses steam discharged from the steam turbine; and{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'an expansion joint which is configured according to and which is provided between the steam turbine and the condenser.'} The present invention relates to an expansion joint ...

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Номер записи: 11
05-12-2013 дата публикации

HEAT SHIELD FOR A LOW-PRESSURE TURBINE STEAM INLET DUCT

Номер: US20130323036A1
Автор: DAGORN Kevin, LAURENT Xavier
Принадлежит: ALSTOM TECHNOLOGY LTD.

The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss. 1. An assembly comprising:a duct,and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element, wherein:the duct comprises at least one boss per shell, which boss is fixed to the duct and against which boss the shell rests,at least one orifice and one boss face one another, andthe fixing element passes through the orifice facing the boss andthe fixing element is fixed to the boss.2. The assembly according to claim 1 , wherein a first of the shells has a rim on one lateral edge to overlap a lateral edge of another of the shells.3. The assembly according to claim 1 , wherein each boss is surmounted by a cap.4. The assembly according to further comprising at least one partition between a first and a second boss claim 1 , the partition being welded to at least the first boss and having a height smaller than that of the first boss.5. The assembly according to further comprising an overlapping element joined to at least one shell of a first segment of the assembly and overlapping one end of a shell of a second segment.6. The assembly according to wherein each segment and the duct between them define a space of constant height.7. The assembly according to wherein each segment and the duct between them define a space filled with air.8. The assembly according to wherein the overlapping element is T-shaped.9. A turbine comprising an outer casing claim 5 , an inner ...

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Номер записи: 12
09-01-2014 дата публикации

COMBUSTOR TRANSITION DUCT ASSEMBLY WITH INNER LINER

Номер: US20140010644A1
Автор: Charron Richard C., Pierce Daniel J.
Принадлежит:

A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced. 1. A transition duct assembly for a turbine engine comprising:a transition duct having a hollow body with an inner peripheral surface and an outer peripheral surface, the transition duct having an inlet and an outlet, the transition duct having an inlet end and an outlet end, the inner peripheral surface of the transition duct being convergent along a majority of the transition duct when moving from the inlet end to the outlet end thereof; andan inner liner removably received within the transition duct, the inner liner having a generally hollow body with an inner peripheral surface and an outer peripheral surface, the outer peripheral surface of the inner liner being correspondingly convergent to the inner peripheral surface of the transition duct, and the inner peripheral surface defining an internal flow passage through the assembly.2. The transition duct system of wherein the transition duct is made of a different material than the inner liner.3. The transition duct system of wherein the inlet end of the transition duct includes a flange claim 1 , wherein the inlet end of the inner liner includes a ...

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Номер записи: 13
20-02-2014 дата публикации

CENTRIFUGAL COMPRESSOR

Номер: US20140050575A1
Автор: KIM ChunKyung
Принадлежит: Korea Fluid Machinery Co., LTD.

Disclosed is a centrifugal compressor having improved operation performance to improve durability. The centrifugal compressor includes an impeller connected to a rotary shaft and configured to radially eject a fluid suctioned in an axial direction upon rotation thereof; a shroud configured to cover front and rear sides of the impeller and having a suction port formed to face one surface of the impeller at a center of one side thereof; a volute chamber formed at an outer periphery of the shroud in a circumferential direction thereof and configured to guide the fluid ejected by the impeller to an ejection port; and a regulator installed at one side of the shroud and configured to selectively communicate a space formed at the other surface of the impeller with the outside. 1. A centrifugal compressor comprising:a rotary shaft having a main flow path formed therein in an axial direction thereof to be rotated;an impeller connected to a first end of the rotary shaft, and configured to suction a fluid in an axial direction and eject the fluid in a radial direction;a thrust bearing disk having a thrust cooling flow path formed therein in the radial direction, and integrally formed with a second end of the rotary shaft to keep a rotation balance with the impeller; anda gas bearing including a radial bearing and a thrust bearing disposed at the rotary shaft and an outer surface of the thrust bearing disk, wherein an air gap is formed to support a rotating load.2. The centrifugal compressor according to claim 1 , wherein the thrust cooling flow path is branched at least once in a circumferential direction of the thrust bearing disk claim 1 , and having an inner end in communication with the main flow path and an outer end formed to pass through the gas bearing.3. The centrifugal compressor according to claim 2 , wherein the main flow path is in communication with a through-hole of the thrust bearing installed to pass through the second end of the rotary shaft in a ...

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Номер записи: 14
14-01-2016 дата публикации

Fan drive thrust balance

Номер: US20160010490A1
Автор: Frederick M. Schwarz, John A. Glahn
Принадлежит: United Technologies Corp

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.

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Номер записи: 15
03-02-2022 дата публикации

TURBINE HOUSING AND TURBOCHARGER

Номер: US20220034239A1
Автор: FUKUI Tatsuya, IIJIMA Kai, KATSU Yoshihito, Sasaki Yuji, SUGIURA Hikaru, YUMOTO Ryosuke
Принадлежит: IHI CORPORATION

A turbine housing has: a first inner member; a second inner member contacting with the first inner member; a turbine scroll flow path enclosed and defined by the first inner member and the second inner member; a first casting housing covering the first inner member at a side opposite to the second inner member; a second casting housing covering the second inner member at a side opposite to the first inner member; an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside; a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; and an inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member. 1. A turbine housing comprising:a first inner member;a second inner member contacting with the first inner member;a turbine scroll flow path enclosed and defined by the first inner member and the second inner member;a first casting housing covering the first inner member at a side opposite to the second inner member;a second casting housing covering the second inner member at a side opposite to the first inner member;an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside;a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; andan inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member.2. The turbine housing according to claim 1 , comprising:a first cooling flow path formed in the first casting housing, a cooling medium passing through the first cooling flow path; anda second cooling flow path formed in the second casting housing, a cooling medium passing through the second cooling flow path.3. The turbine housing according to claim 2 , wherein the first and ...

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Номер записи: 16
18-01-2018 дата публикации

SEALING ARRANGEMENT ON COMBUSTOR TO TURBINE INTERFACE IN A GAS TURBINE

Номер: US20180016923A1
Автор: Benz Urs, IMFELD Jost, MATHEWS Hans-Christian
Принадлежит: ANSALDO ENERGIA SWITZERLAND AG

A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner. 1. A gas turbine unit comprising:a combustor having a liner;a turbine, arranged downstream of the liner along a main flow gas direction (M) and including a plurality of first stage vanes;a rotor cover support located inwardly of the vanes;a sealing arrangement at a combustor to turbine interface, the sealing arrangement having a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner, or between the rotor cover support and a bulkhead located at an inner downstream end of the liner.2. Gas turbine unit as claimed in claim 1 , wherein the first dogbone seal comprises:a central laminar portion; anda first and a second bulged edge, the edges being straight.3. Gas turbine unit as claimed in claim 2 , wherein a first end of the flat dogbone seal is housed in a groove of the rotor cover support.4. Gas turbine unit as claimed in claim 3 , wherein a portion of the rotor cover support provided with the groove is configured as an additional part.5. Gas turbine unit as claimed in claim 1 , wherein the sealing arrangement comprises:a second dogbone seal extending between the rotor cover support and a vane inner platform.6. Gas turbine unit as claimed in claim 5 , wherein the second dogbone seal comprises:a central laminar portion and a first and a second bulged edge, at least the second edge being curved.7. Gas turbine unit as claimed in claim 1 , comprising:a honeycomb seal arranged on a bulkhead portion ...

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Номер записи: 17
01-05-2014 дата публикации

TURBINE COWLING SYSTEM

Номер: US20140119886A1
Автор: Corratti Anthony Angelo, Lopez Partida Erik Eduardo, Predmore Daniel Ross, Sherwood Robert James
Принадлежит: GENERAL ELECTRIC COMPANY

A steam turbine cowling system is disclosed. The steam turbine cowling system including: a lower portion configured to be disposed proximate an inner casing of a steam turbine; and an upper portion connected to at least one of the lower portion and the inner casing, the upper portion shaped to be disposed proximate the inner casing of the steam turbine, the upper portion substantially defining a flowpath about the inner casing. 1. A steam turbine cowling system comprising:a lower portion configured to be disposed proximate an inner casing of a steam turbine; andan upper portion connected to at least one of the lower portion and the inner casing, the upper portion shaped to be disposed proximate the inner casing of the steam turbine and substantially defining a flowpath about the inner casing.2. The steam turbine cowling system of claim 1 , wherein at least one of the upper portion and the lower portion is configured as an insulator about the inner casing.3. The steam turbine cowling system of claim 1 , wherein the lower portion is permanently connected to the inner casing.4. The steam turbine cowling system of claim 1 , wherein the upper portion is connected to at least one of the inner casing or a steam guide in the steam turbine.5. The steam turbine cowling system of claim 4 , wherein the upper portion is releasably coupled to the inner casing.6. The steam turbine cowling system of claim 1 , wherein the at least one of the upper portion and the lower portion include a substantially smooth radially inward facing surfaces.7. The steam turbine cowling system of claim 1 , wherein the upper portion includes a steam inlet.8. The steam turbine cowling system of claim 1 , wherein the upper portion is configured to guide a flow toward the lower portion.9. The steam turbine cowling system of claim 1 , wherein the upper portion and the lower portion substantially enclose the inner casing and define a flowpath from a top of the inner casing to a condenser.10. The steam ...

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Номер записи: 18
04-02-2021 дата публикации

Active Stability Control of Compression Systems Utilizing Electric Machines

Номер: US20210033101A1
Автор: Barone Dominic, Gemin Paul Robert, Radun Arthur Vorwerk
Принадлежит:

The present disclosure is directed to turbine engines and systems for active stability control of rotating compression systems utilizing an electric machine operatively coupled thereto. In one exemplary aspect, an electric machine operatively coupled with a compression system, e.g., via a shaft system, is controlled to provide shaft damping for instability fluctuations of the pressurized fluid stream within the compression system. Based on control data indicative of a system state of the compression system, a control parameter of the electric machine is adjusted to control or change an output of the shaft system. Adjusting the shaft system output by adjusting one or more control parameters of the electric machine allows the compression system to dampen instability fluctuations of the fluid stream within the compression system. A method for active stability control of a compression system operatively coupled with an electric machine via a shaft system is also provided. 1. A turbine engine , comprising:a compressor configured to pressurize an incoming air stream into a pressurized air stream;a combustion chamber fluidly connected with the compressor and configured to receive the pressurized air stream from the compressor, wherein fuel is injected into the pressurized air stream and ignited in the combustion chamber so as to raise a temperature and energy level of the pressurized air stream;a turbine fluidly connected with the combustion chamber and configured to receive combustion products that flow from the combustion chamber;a shaft system;an electric generator operatively coupled with the compressor via the shaft system;one or more electrical loads electrically connectable with the electric generator via a power bus system; receive control data indicative of a system state of the compressor;', 'determine a damping control command representative of instructions for adjusting a control parameter of at least one of the electric generator and the one or more electrical ...

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Номер записи: 19
06-02-2020 дата публикации

Steam turbine

Номер: US20200040732A1
Автор: Takuro Koda
Принадлежит: Mitsubishi Heavy Industries Compressor Corp

A steam turbine includes: a rotor; a casing; a thrust bearing; a steam inlet; a first pipe; a first regulation valve; a second pipe; a second regulation valve; and a control device. The control device estimates an exhaust flow rate of the steam turbine based on an operating point map which derives the exhaust flow rate of the steam turbine from an operating point of the steam turbine and estimates the thrust force applied to the thrust bearing based on the exhaust flow rate.

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Номер записи: 20
26-02-2015 дата публикации

Bearing systems for turbochagers used on internal combustion engines

Номер: US20150056071A1
Автор: Woollenweber William E.
Принадлежит:

A bearing system for a turbocharger rotor assembly that includes an elongated bearing carrier with anti-friction bearings on each end carried in a stationary housing. The elongated bearing carrier is supported within the housing by axially spaced elastomeric bands in grooves in the outside diameter of the bearing carrier that cooperate with grooves in the bore of the stationary housing within which the elastomeric bands are seated to carry the axial thrust of the rotor assembly in both axial directions. 1. In a bearing system for a rotating assembly carried in a housing of a turbocharger for an internal combustion engine , the improvement wherein the bearing system and housing combine to form a coolant cavity by an elongated bearing carrier whose outer surface forms one surface defining the coolant cavity and is sealed with said housing by an elastomeric band on each end of said one surface , said elastomeric bands being seated in grooves in said housing bore to carry rotor thrust in both axial directions.2. The improvement of wherein said elongated bearing carrier has a cylindrical outside surface with a peripheral “O”-ring groove formed on each end of said one surface and said elastomeric bands are “O”-rings seated in said peripheral grooves that are located to coincide with said grooves in said bearing housing bore when said elongated bearing carrier is assembled within said housing.3. The improvement of wherein the elastomeric bands seated in said peripheral grooves and are seated in said grooves in said housing bore claim 1 , they function to carry rotor thrust in both axial directions.4. A turbocharger for use on internal combustion engines claim 1 , comprising:a bearing housing carrying a turbocharger rotating assembly including a rotatable shaft with a compressor wheel at one end rotatably drivable by an engine exhaust gas turbine wheel at the opposite end, said rotatable shaft being rotatably carried within a tubular bearing carrier by ball bearings ...

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Номер записи: 21
22-05-2014 дата публикации

TURBINE CASING WITH SERVICE WEDGE

Номер: US20140140839A1
Автор: Batzinger Thomas James, DAVI Michael Alan
Принадлежит: GENERAL ELECTRIC COMPANY

A turbine casing is provided and includes first and second turbine casing shells configured to be removably coupled to one another. At least one of the first and second turbine casing shells is formed to define an access slot. At least one service wedge is configured to be removably installed in the access slot. 1. A turbine casing , comprising:first and second turbine casing shells configured to be removably coupled to one another,at least one of the first and second turbine casing shells being formed to define an access slot; andat least one service wedge configured to be removably installed in the access slot.2. The turbine casing according to claim 1 , wherein the first turbine casing shell comprises a lower hemispherical casing and the second turbine casing shell comprises an upper hemispherical casing and is formed to define the access slot.3. The turbine casing according to claim 1 , wherein the access slot is defined along a centerline of the at least one of the first and second turbine casing shells.4. The turbine casing according to claim 1 , wherein a position of the access slot is defined such that the access slot is offset from a centerline of the at least one of the first and second turbine casing shells.5. The turbine casing according to claim 1 , wherein the at least one of the first and second turbine casing shells is formed to define multiple access slots and the at least one service wedge comprises multiple service wedges claim 1 , each one of the multiple service wedges being configured to be removably installed in a corresponding one of the multiple access slots.6. The turbine casing according to claim 5 , wherein the multiple access slots are arranged symmetrically relative to a centerline of the at least one of the first and second turbine casing shells.7. The turbine casing according to claim 1 , wherein the access slot is elongate in an axial dimension of at least one of the first and second turbine casing shells.8. The turbine casing ...

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Номер записи: 22
28-02-2019 дата публикации

AXIAL THRUST BALANCING DEVICE

Номер: US20190063221A1
Автор: Bruurs Kevin
Принадлежит:

An axial thrust balancing mechanism for a rotating shaft apparatus such as a rotary pump provides self-regulating thrust compensation while avoiding contact and wear between rotating and static elements. A rotor fixed to the shaft includes a cylindrical male section proximal to but not extending within a cylindrical female section of a non-rotating stator, such that a gap formed therebetween is varied in width by shaft displacements caused by axial thrusts. Pressurized fluid within the female section applies a thrust-compensating force to the rotor that is controlled by the gap size. The female section is larger in diameter than the male section, thereby preventing any contact therebetween. The disclosed mechanism can be combined with a thrust-compensating drum so as to reduce the thrust to a residual level that can be regulated. The rotor and stator can be stepwise varied to provide a plurality of gaps and intermediate chambers therebetween. 1. A thrust regulating mechanism for an apparatus having a shaft that is subject to an axial displacement caused by an axial thrust , the mechanism comprising:a first segment that is longitudinally fixed to and coaxial with the rotatable shaft, and a second segment that surrounds but is not longitudinally fixed to the shaft, the first and second segments being configured such that there is a relative rotation therebetween during operation of the apparatus, the second segment being in fluid communication with a high pressure fluid region; anda cylindrical male section included on one of the first and second segments, and a cylindrical female section included on the other of the first and second segments, the male section being terminated by a circular leading edge and the female section being terminated at a front edge thereof by a circular opening that is larger in diameter than circular leading edge of the male section,the leading edge of the male section being proximal to the front edge of the female section without entering ...

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Номер записи: 23
28-02-2019 дата публикации

GAS TURBINE HAVING AXIAL THRUST PISTON AND RADIAL BEARING

Номер: US20190063222A1
Автор: Larson Marco, Savilius Nicolas
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A gas turbine having an axially adjustable rotor, has the following components: at least one external compressor air bleed for bleeding compressor air; a control valve for adjusting the amount of compressor air bled via the at least one external compressor air bleed; an axial thrust piston that can be supplied with the compressor bleed air via a supply line in such a way that a different axial compensation thrust is applied to same when the amount of compressor bleed air is adjusted; and a radial bearing which cooperates with the axial thrust piston for bearing purposes, and which can also be directly or indirectly supplied with the compressor bleed air via the supply line. 1. A gas turbine having an axially adjustable rotor , comprising the following components:at least one external compressor bleed for extracting compressor air;a control valve for adjusting the quantity of compressor air which is extracted via the at least one external compressor bleed;an axial thrust piston which can be supplied with the extracted compressor air via a feed pipe in such a way that with adjustment of the quantity of compressor air a different axial compensating thrust is applied to this;a radial bearing at the end of the gas turbine which interacts with the axial thrust piston in a bearing-technological manner, and which can also be supplied directly or indirectly with the extracted compressor air via the feed pipe.2. The gas turbine as claimed in claim 1 ,wherein the axial thrust piston and the radial bearing are interconnected in series with regard to the supply with compressor air.3. The gas turbine as claimed in claim 1 ,wherein the axial thrust piston and the radial bearing are interconnected in parallel with regard to the supply with compressor air.4. The gas turbine as claimed in claim 1 ,wherein provision is made for at least two external compressor bleeds for extracting compressor air at a different pressure level and both open into the feed pipe for the axial thrust ...

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Номер записи: 24
28-02-2019 дата публикации

SEGMENTED CONDUIT WITH AIRFOIL GEOMETRY

Номер: US20190063241A1
Автор: Colebrook Mark W.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A conduit that includes a first segment forming a first sidewall of the conduit and a second segment forming a second sidewall of the conduit. The first segment may include a first inner surface and a first outer surface and the second segment may include a second inner surface and a second outer surface. The first segment may be coupled to the second segment such that the first inner surface and the second inner surface jointly form an inner conduit surface and the first outer surface and the first inner surface jointly form at least a portion of an outer conduit surface, wherein the outer conduit surface has an airfoil geometry. The first segment and the second segment may be detachably coupled together. 1. A conduit comprising:a first segment forming a first sidewall of the conduit, the first segment comprising a first inner surface and a first outer surface; anda second segment forming a second sidewall of the conduit, the second segment comprising a second inner surface and a second outer surface;wherein the first segment is coupled to the second segment such that the first inner surface and the second inner surface jointly form an inner conduit surface and the first outer surface and the first inner surface jointly form at least a portion of an outer conduit surface, wherein the outer conduit surface has an airfoil geometry.2. The conduit of claim 1 , wherein the first segment and the second segment are detachably coupled together.3. The conduit of claim 1 , wherein the first outer surface at least partially forms one of an upper surface and a lower surface of the airfoil geometry of the outer conduit surface and the second outer surface at least partially forms the other of the upper surface and the lower surface of the airfoil geometry of the outer conduit surface.4. The conduit of claim 3 , further comprising a third segment and a fourth segment claim 3 , wherein the third segment couples the first segment to the second segment and forms a leading edge ...

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Номер записи: 25
05-03-2020 дата публикации

TURBOMACHINE WITH AXIAL FORCE RECOVERY AT THE FAN VIA PRESSURIZED GAS FEED

Номер: US20200072053A1
Автор: BECOULET Julien Fabien Patrick, Brault Michel Gilbert Roland, CHASSAGNE Amelie Argie Antoinette, YVON Didier Jean-Louis
Принадлежит:

A turbomachine having a fan shaft supported by a first bearing positioned downstream of the fan, the first bearing including an outer ring attached to an annular support secured to the stator. The turbomachine includes at least one gas feed duct leading into an enclosure positioned against the disc, the gas feed duct being adapted to be fed at a second end with pressurized gas taken from an airstream of a high-pressure compressor of the turbomachine, so that the gas applies an axial force towards upstream on the disc during some operating phases of the turbomachine. The turbomachine further includes a ferrule imperviously sealing the enclosure. 1. Turbomachine comprising a fan driven in rotation by a shaft in relation to an inlet casing of the turbomachine , the fan comprising blades mounted on a fan disc , the shaft being supported by a first bearing positioned downstream of the fan , said first bearing comprising an outer ring attached to the inlet casing ,the turbomachine comprising at least one gas feed duct with a first end opening into an enclosure positioned against the disc, the turbomachine further comprising a ferrule imperviously sealing the enclosure,wherein the gas feed duct is adapted to be fed at a second end by pressurized gas taken from an airstream of a high pressure compressor of the turbomachine, so that said gas applies an axial upstream force on the disc during some operating phases of the turbomachine.2. The turbomachine according to claim 1 , wherein the gas feed duct is provided with a valve to control the conveying of gas into the enclosure.3. The turbomachine according to claim 1 , the enclosure being longitudinally limited by the disc and by a bearing support surrounding the shaft and the first bearing claim 1 , a gas feed duct leading into a cavity made in the bearing support.4. The turbomachine according to claim 1 , wherein a gas feed duct leads into the enclosure at a piercing facing a side portion of the disc.5. The turbomachine ...

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Номер записи: 26
12-06-2014 дата публикации

STEAM TURBINE HOUSING

Номер: US20140161608A1
Автор: Gaida Andre, Konya Zsolt, Kuhn Martin, Sperla Frank
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A steam turbine housing is provided having a housing wall and a stiffening cradle attached to the inner side which has two encircling inner webs which are arranged axially adjacent to one another and which project radially inward from the housing wall. Between the inner webs, running parallel and axially centrally, a central web is attached to the inner side of the housing wall, the radially inner edge of which is straight, wherein at the radially inner edge of the central web, the central web forks in a Y-shaped manner inward into two transition webs which extend to and merge into the adjacent inner web, such that the inner webs are fastened directly to the housing wall outside the circumferential extent of the transition webs and are fastened to the housing wall via the transition webs and the central web within the circumferential extent of the transition webs. 1. A steam turbine housing comprising:a housing wall, to the inside of which is attached a stiffening cradle having two circumferential inner webs arranged axially next to one another and projecting radially inward from the housing wall, a central web being attached to the inside of the housing wall between the inner webs so as to run parallel to these and axially centrally,the radially inner rim of the central web being straight so that the longitudinal ends of this rim meet the housing wall, defining the circumferential extent of the central web,wherein the central web forks, at its inner rim, in the shape of an inward-facing Y to form two transition webs which in each case extend as far as the adjacent inner web and merge into the latter,such that, outside the circumferential extent of the transition webs, the inner webs are attached to the housing wall directly, while inside the circumferential extent of the transition webs they are attached to the housing wall via the transition webs and the central web.2. The steam turbine housing as claimed in claim 1 ,wherein the inner rim of the central web has a ...

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Номер записи: 27
14-04-2016 дата публикации

SHEET METAL TURBINE HOUSING WITH CELLULAR STRUCTURE REINFORCEMENT

Номер: US20160102579A1
Автор: Hanna David R., Hu Leon, Sun Harold Huimin
Принадлежит:

Systems are provided for a reinforcement element coupled to a sheet metal turbine housing that imparts desirable thermal-protective and structurally strengthening characteristics to the housing layers. In one example, a system may include a turbine comprising a housing surrounding a turbine rotor, the housing having an outer layer surrounding an inner layer at a distance to form an intermediate space between the inner and outer layers. Moreover, disposed in the intermediate space is a reinforcement element coupled to the inner and outer layers, providing strength and consistent rigidity without a significant increase in weight to the housing. 1. A turbine comprising: an inner layer;', 'an outer layer, the outer layer surrounding the inner layer at a distance to form an intermediate space between the inner and outer layers; and', 'a reinforcement element disposed within the intermediate space and coupled to at least one of the inner layer and outer layer maintaining a threshold length between the inner layer and the rotor., 'a housing surrounding a rotor, the housing having2. The turbine of claim 1 , wherein the reinforcement element comprises a body of corrugated or bellowed layers of a sheet metal forming a pattern.3. The turbine of claim 2 , wherein the pattern is a honeycomb-like shape such that the cross-section of the reinforcement element is a plurality of hexagons.4. The turbine of claim 2 , wherein the pattern is a bellowing wave claim 2 , such that the cross-section of the reinforcement element is a sine wave.5. The turbine of claim 2 , wherein the pattern is a plurality of squares or triangles aligned in series.6. The turbine of claim 1 , wherein the reinforcement element is in face-sharing contact with a first surface of the outer layer facing toward the turbine rotor and a second surface of the inner layer facing away from the turbine rotor.7. The turbine of claim 1 , wherein the reinforcement element is coupled to one or more of the inner layer and ...

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Номер записи: 28
29-04-2021 дата публикации

BEARING STRUCTURE

Номер: US20210123360A1
Автор: HUH Jaemin, UNEURA Yutaka
Принадлежит: IHI CORPORATION

A bearing structure includes: a rotation member including a plurality of extended portions extending radially outward from a shaft portion and arranged separated away from each other in an axial direction of the shaft portion; and a bearing member in which a counterface surface facing one of the plurality of extended portions in the axial direction is included in one or a plurality of main bodies. 1. A bearing structure comprising:a rotation member including a shaft portion and a plurality of extended portions extending radially outward from the shaft portion and arranged separated away from each other in an axial direction of the shaft portion;a large diameter portion having a diameter larger than a diameter of the shaft portion and including the extended portion on each of one side and another side in the axial direction, the large diameter portion being included in the rotation member;a bearing member including a plurality of main bodies through which the shaft portion is inserted, the plurality of main bodies being arranged on each of one side and another side in the axial direction with respect to the large diameter portion, the plurality of main bodies including a counterface surface facing one of the plurality of extended portions in the axial direction; anda turbine housing in which a through hole is formed, the through hole in which the bearing member is arranged.2. The bearing structure according to claim 1 , wherein the rotation member includes a pair of the extended portions arranged so as to face each other in the axial direction.3. The bearing structure according to claim 1 , wherein the bearing member includes the main body located between a pair of the extended portions arranged so as to face each other in the axial direction claim 1 , the main body including a pair of counterface surfaces facing the pair of extended portions claim 1 , respectively.4. The bearing structure according to claim 2 , wherein the bearing member includes the main body ...

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Номер записи: 29
17-07-2014 дата публикации

Steam turbine comprising a thrust balance piston

Номер: US20140199161A1
Автор: Christian Lenz, Dominic Schlehuber, Martina Holder, Norbert Pieper, Rudolf PÖTTER, Uwe Zander
Принадлежит: SIEMENS AG

A cooling mechanism for a steam turbine is provided, which has, in the area of the valve connection a cooling channel, into which cooling steam flows from the flow channel, the steam then being fed as cooling steam in the area of the thrust balance piston.

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Номер записи: 30
24-07-2014 дата публикации

INNER CASING FOR STEAM TURBINE ENGINE

Номер: US20140205435A1
Автор: Giusti Enrico, Grilli Marco, Imparato Enzo
Принадлежит: GENERAL ELECTRIC COMPANY

A system includes a steam turbine. The steam turbine includes an outer casing and an inner casing disposed within the outer casing. The inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion. The steam turbine also includes an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage. The steam turbine further includes at least one reaction stage having multiple blades. The at least one reaction stage is integrated within the inner casing. 1. A system , comprising: an outer casing; and', 'an inner casing disposed within the outer casing, wherein the inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion;', 'an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage;', 'at least one reaction stage comprising a plurality of blades, wherein the at least one reaction stage is integrated within the inner casing., 'a steam turbine comprising2. The system of claim 1 , wherein the impulse stage is disposed within the inner casing upstream of the at least one reaction stage.3. The system of claim 1 , wherein the inner casing comprises a plurality of steam ducts that define a fluid flow path through the upper and lower inner casing portions claim 1 , and the fluid flow path is configured to provide full arc admission of the fluid to the impulse stage via the fluid flow path.4. The system of claim 3 , wherein the inner casing comprises a flange horizontally split in the axial direction claim 3 , the upper inner casing portion comprises an upper flange portion and the lower inner casing portion comprises a lower flange portion claim 3 , and the upper and lower flange portions form the flange.5. The system of claim 4 , wherein the at least one steam duct of the ...

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Номер записи: 31
25-04-2019 дата публикации

TURBO-ENGINE HOUSING, EQUIPPED WITH A THERMAL PROTECTION SHELL AND AN ANTI-WEAR STRIP

Номер: US20190120083A1
Автор: BAZOT Olivier, EDYNAK Jérémy Philippe Pierre, HUSSAIN Farhana, LIBES Fanny Marie
Принадлежит:

A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell. 1. A turbo-engine module , comprising:a turbo-engine housing,a thermal protection shell of the housing, wherein the thermal protection shell is configured to cover at least partially the housing in order to protect the housing thermally,wherein the module comprises a wear protection strip which is situated between the housing and the thermal protection shell in a junction region of the housing and the thermal protection shell,wherein the wear protection strip comprises at least one recess, wherein the wear protection strip is open-worked at the recess,wherein the recess is situated outside a zone for fastening the wear protection strip to the thermal protection shell and/or wherein the recess is situated outside a zone for fastening the wear protection strip to the housing.2. The turbo-engine module according to claim 1 , wherein the wear protection strip covers a housing portion claim 1 , wherein the wear protection strip is made of the same material as the material of the housing portion claim 1 , and/or wherein the wear protection strip is made of the same material as the material of the thermal protection shell.3. The turbo-engine module according to claim 1 , wherein the wear protection strip has a thickness between 0.3 mm and 0.8 mm.4. The turbo-engine module according to claim 1 , wherein the thermal protection shell is secured to the housing by at least one attachment claim 1 ,wherein the wear protection strip is fastened to the housing and to the thermal protection shell by the attachment.5. The turbo-engine module according to claim 4 , wherein the ...

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Номер записи: 32
31-07-2014 дата публикации

COOLING FOR A FLUID FLOW MACHINE

Номер: US20140212269A1
Автор: KÄSTNER Christoph, Potter Rudolf
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A fluid flow machine, in particular a steam turbine, is provided having a piston-equalizing line which conducts a vapour from a fresh vapour region of a second flow duct to a thrust-equalizing piston, wherein the surface of the piston-equalizing line is enlarged, and wherein the inner surface of the piston-equalizing line is enlarged. 110.-. (canceled)11. A turbomachine comprisinga rotor mounted rotatably about an axis of rotation, an inner housing arranged about the rotor and an outer housing arranged about the inner housing,wherein a first flow region and a second flow region, formed in the opposite flow direction to the first flow region, are arranged between the rotor and the inner housing,wherein the rotor has a thrust-equalizing piston,wherein a piston-equalizing line is formed for introducing steam between the inner housing and the thrust-equalizing piston,wherein the piston-equalizing line outer surface is embodied to be enlarged with respect to a pipe outer surface and/or the piston-equalizing line inner surface is embodied to be enlarged with respect to a pipe inner surface,wherein outer cooling ribs are arranged on the piston-equalizing line outer surface, andwherein the outer cooling ribs are arranged in series in the direction of the piston-equalizing line.12. The turbomachine as claimed in claim 11 ,wherein the outer cooling ribs are formed as annular disks extending in the radial direction with respect to the direction of the piston-equalizing line.13. The turbomachine as claimed in claim 12 ,wherein the annular disks are arranged at regular intervals.14. The turbomachine as claimed in claim 11 ,wherein inner cooling ribs are arranged on the piston-equalizing line inner surface.15. The turbomachine as claimed in claim 14 ,wherein the inner cooling ribs are arranged in series in the inner circumferential direction.16. The turbomachine as claimed in claim 15 ,wherein the inner cooling ribs are embodied as projections extending in the axial direction ...

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Номер записи: 33
21-05-2015 дата публикации

ROTOR FOR A STEAM TURBINE

Номер: US20150139780A1
Автор: Devries Jorg
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A turbomachine is provided, wherein the rotor comprises a planetary gear on which low-pressure end stage blades are arranged, wherein the planetary gear is designed in such a way that the frequency of the rotating blades is lower than the frequency of the rotor. 1. A rotor for a turbomachine having a planetary gearset comprisinga shaft and a crown wheel which is arranged about the shaft and can adapted to be arranged in a rotationally fixed manner,wherein the crown wheel has internal teeth which interact with multiple internal planet gears,a planet disk which is arranged about the shaft and on which the planet gears are rotatably arranged,wherein the shaft has a sun gear which interacts with the planet gears and rotor blades which are arranged on the planet disk,wherein rotor blade stages formed of further rotor blades are arranged fixedly on the rotor.2. The rotor as claimed in claim 1 ,wherein the planet disk is sealed with respect to the shaft.3. The rotor as claimed in claim 2 ,wherein an oil seal is arranged between the shaft and the planet disk.4. The rotor as claimed in claim 2 ,wherein a steam seal is arranged between the shaft and the planet disk.5. The rotor as claimed in claim 1 ,wherein at least four planet gears are arranged.6. The rotor as claimed in claim 1 ,wherein the planet gears, the sun gear and the crown wheel are dimensioned such that a shaft rotational frequency of the shaft is higher than the planet disk rotational frequency of the planet disk.7. The rotor as claimed in claim 1 ,wherein the planet disk is connected to a rotor disk.8. The rotor as claimed in claim 7 ,wherein the rotor blades are arranged on the rotor disk.9. A steam turbine having a rotor as claimed in .10. The steam turbine as claimed in claim 9 ,{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'wherein the steam turbine is of double-flow configuration and each flow channel has a planetary gearset as claimed in .'} This application is the US National Stage of International ...

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Номер записи: 34
17-05-2018 дата публикации

STEAM TURBINE

Номер: US20180135414A1
Автор: KODA Takuro
Принадлежит: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION

A steam turbine includes: a rotor shaft including a shaft core that rotates about an axis and disk portions that are fixed to the shaft core and expand toward a radially outer side in the shaft core; and a plurality of rotor blades that are fixed to outer peripheries of the disk portions and are disposed in a circumferential direction of the shaft core. A first surface that is toward a first direction including a directional component toward a radially inner side of the shaft core is formed on each of the rotor blades, and a second surface that is toward a second direction including a directional component toward the radially outer side and faces the first surface is formed on each of the disk portions. 1. A steam turbine , comprising: a shaft core that rotates about an axis; and', 'disk portions that are fixed to the shaft core and expand toward a radially outer side in the shaft core; and, 'a rotor shaft comprisinga plurality of rotor blades that are fixed to outer peripheries of the disk portions and are disposed in a circumferential direction of the shaft core,wherein a first surface that is toward a first direction including a directional component toward a radially inner side of the shaft core is formed on each of the rotor blades,wherein a second surface that is toward a second direction including a directional component toward the radially outer side and faces the first surface is formed on each of the disk portions, andwherein a balance hole that is recessed to communicate in an axial direction in which the shaft core extends is formed in at least one of the first surface and the second surface.2. The steam turbine according to claim 1 , wherein each of the rotor blades comprises:a blade body that extends in the radial direction,a platform on the radially inner side of the blade body, anda blade root on the radially inner side of the platform, wherein the blade root is fitted into a blade groove formed in each of the disk portions,wherein in the blade root, ...

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Номер записи: 35
09-05-2019 дата публикации

TURBINE HOUSING

Номер: US20190136717A1
Автор: Isaji Satoru, Sato Akira
Принадлежит: AISIN TAKAOKA CO., LTD.

An outer housing formed of a sheet metal is provided such that its open end portion surrounds an outer edge portion of an inner housing formed by casting. An outer protrusion an annular protrusion and a connecting portion are provided on the outer edge portion of the inner housing The open end portion of the outer housing is joined to a protruding end of the outer protrusion a protruding end of the annular protrusion and an end edge of the connecting portion whereby the inner housing and the outer housing are integrated. 1. A turbine housing comprising:an inner housing formed by casting and including a scroll tube portion which surrounds a turbine chamber for accommodating a turbine impeller and has a scroll flow passage through which a flow exhaust gas flows circularly and goes out to the turbine chamber, and an introduction tube portion which leads an inflow exhaust gas to the scroll flow passage, and an outlet passage portion through which the flow exhaust gas flows out of the turbine chamber flows; andan outer housing formed of a sheet metal and including an open end portion which surrounds an outer edge portion of the inner housing when viewed in a direction of a scroll center line and an exhaust outlet which is provided on a side opposite the open end portion and through which the flow exhaust gas flowing out of the outlet passage portion is discharged,wherein the inner housing has a protrusion protruding outward from the outer edge portion of the inner housing, and a protruding end of the protrusion and the open end portion of the outer housing are joined to each other, whereby the outer housing and the inner housing are integrated.2. A turbine housing according to claim 1 , whereinthe scroll flow passage has a flow passage inlet through which the flow exhaust gas flows into the scroll flow passage, and a flow passage outlet through which the flow exhaust gas flows out of the scroll flow passage, and a merging portion in which the flow exhaust gas flowing out ...

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Номер записи: 36
26-05-2016 дата публикации

FORGED CAST FORGED OUTER CASE FOR A GAS TURBINE ENGINE

Номер: US20160146052A1
Автор: Bauer Steven J., McGinnis Christine F.
Принадлежит:

A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section. 1. A case assembly for a gas turbine engine , comprising:a cast case section cast case section configured to be welded between a forward case section and an aft case section.2. The case assembly as recited in claim 1 , wherein said cast case section includes a machined interface.3. The case assembly as recited in claim 1 , wherein said cast case section includes a raised boss.4. The case assembly as recited in claim 1 , wherein said cast case section includes a machined surface.5. The case assembly as recited in claim 1 , wherein said forward case section and said aft case section are forged.6. The case assembly as recited in claim 5 , wherein said forged forward case section is configured for containment of a high pressure turbine rotor stage.7. The case assembly as recited in claim 6 , wherein said forged forward case section includes a forward flange.8. The case assembly as recited in claim 6 , wherein said forged aft case section is configured for containment of a low pressure turbine rotor stage.9. The case assembly as recited in claim 8 , wherein said forged aft case section includes an aft flange.10. The case assembly as recited in claim 5 , wherein said forged forward case section and said forged aft case section define respective forward and aft containment zones.11. The case assembly as recited in claim 1 , wherein said forged forward case section and said forged aft case section define respective forward and aft containment zones.12. The case assembly as recited in claim 1 , further comprising a forward weld between said forged forward case section and said cast case section outside of said forward containment zone and an aft weld between said cast case section and said forged aft case section outside of said aft containment zone.13. The case assembly as recited in claim 1 , wherein said case is a ...

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Номер записи: 37
24-05-2018 дата публикации

Turbine Assembly Method

Номер: US20180142571A1
Автор: Ishibashi Koji, KODERA Juichi, MIZUMI Shunsuke
Принадлежит:

A turbine assembly method includes a positional information measurement process in which positional information on a plurality of specific portions set on an outer surface of a casing is measured in a state before releasing of bolt fastening of the casing at a time of disassembly of the turbine and in a predetermined disassembly state after the releasing of the bolt fastening, and an alignment process in which positional adjustment of a stationary component with respect to the casing is made based on the measurement results of the positional information on the specific portions in the positional information measurement process. 1. A method of assembling a turbine including a casing divided into a casing lower part and a casing upper part , a turbine rotor contained in the casing , and a stationary component supported inside the casing and divided into a lower side and an upper side , the casing lower part and the casing upper part being connected together by bolt fastening ,the method comprising:a positional information measurement process in which positional information on a plurality of specific portions set on an outer surface of the casing is measured in a state before releasing of bolt fastening of the casing at a time of disassembly of the turbine and in a predetermined disassembly state after the releasing of the bolt fastening; andan alignment process in which positional adjustment of the stationary component with respect to the casing is made based on measurement results in the positional information measurement process.2. The method of assembling the turbine according to claim 1 , whereinthe predetermined disassembly state after the releasing of the bolt fastening of the casing in the positional information measurement process is a state in which the casing upper part, the upper side of the stationary component, and the turbine rotor are removed, andthe specific portions are set on the casing lower part.3. The method of assembling the turbine according to ...

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Номер записи: 38
21-08-2014 дата публикации

CASING COOLING DUCT

Номер: US20140234073A1
Автор: Moreton Kevin, Scott Kevin
Принадлежит:

A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine. 112-. (canceled)13. A turbine , comprising:an inner casing to which at least a stator vane of a turbine section is mountable, andan outer casing, which is arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing,wherein the outer cooling channel comprises a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel,wherein the cooling channel comprises a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine,wherein the fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel comprises a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.14. The turbine according to claim 13 , wherein the fluid inlet is formed in the outer casing.15. The turbine according to claim 13 , wherein the fluid outlet is formed in the inner casing.16. The turbine according to claim 13 , wherein the outer cooling channel is formed with a converging shape for ...

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Номер записи: 39
31-05-2018 дата публикации

BEARING COMPARTMENT SCAVENGE CONTROL

Номер: US20180149040A1
Автор: James Denman H., Sodaro Joseph J., Witlicki Russell B.
Принадлежит:

Aspects of the disclosure are directed to a system associated with an engine, comprising: a bearing compartment, a scavenge line coupled to the bearing compartment at a first end of the scavenge line that receives a fluid via the first end of the scavenge line, a fluid pump coupled to the scavenge line at a second end of the scavenge line to receive the fluid, and a flow control valve having a variable flow area and disposed in the scavenge line to control flow of the fluid in the scavenge line and the fluid pump. 1. A system associated with an engine , comprising:a bearing compartment;a scavenge line coupled to the bearing compartment at a first end of the scavenge line that receives a fluid via the first end of the scavenge line;a fluid pump coupled to the scavenge line at a second end of the scavenge line to receive the fluid; anda flow control valve having a variable flow area and disposed in the scavenge line to control flow of the fluid in the scavenge line and the fluid pump.2. The system of claim 1 , further comprising:a seal,wherein the seal provides air to the bearing compartment during a steady state condition associated with an operation of the engine.3. The system of claim 2 , wherein the air is provided by a compressor section of the engine.4. The system of claim 2 , wherein a flow control mechanism of the flow control valve is substantially or fully closed during the steady state condition.5. The system of claim 4 , wherein the flow control valve includes at least one bypass orifice that provides at least a portion of the fluid through the flow control valve during the steady state condition.6. The system of claim 2 , wherein a flow control mechanism of the flow control valve controls the variable flow area and is at least partially open during a transient condition associated with the operation of the engine.7. The system of claim 6 , wherein the transient condition corresponds to a deceleration of the engine.8. The system of claim 1 , further ...

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Номер записи: 40
11-06-2015 дата публикации

INFLOW SEGMENT FOR A TURBOMACHINE

Номер: US20150159486A1
Автор: Forster Ingo, Musch Christian, Zander Uwe
Принадлежит: SIEMENS AKTIENGESELLCHAFT

A turbomachine is provided having an inflow segment which carries an inflow segment vane and bores, a partial mass flow arriving through these bores at a relief space and leading to a cooling system. 18-. (canceled)9. A turbomachine , comprisinga rotor mounted rotatably about an axis of rotation, with rotor blades arranged on the rotor,a casing arranged about the rotor, with guide vanes attached inside the casing,a flow duct formed between the rotor and the casing,a supply line arranged in the casing and formed for supplying steam,an inflow segment arranged in the casing,inflow segment guide vanes arranged in the inflow segment, andbores arranged in the inflow segment which establish a fluidic connection between the supply line and a relief space arranged between the inflow segment and the rotor,wherein the bores are inclined, with respect to a radial direction through the axis of rotation, by an angle α of between 40° and 80°.10. The turbomachine as claimed in claim 9 ,wherein the bores are formed such that part of the supply steam is fed through the bores and part of the supply steam is fed through the inflow segment guide vanes.11. The turbomachine as claimed in claim 9 ,wherein the inflow segment has a hub-side ring segment in which are formed the bores.12. The turbomachine as claimed in claim 9 ,wherein the bores are arranged upstream of the inflow segment guide vanes, as seen from the flow direction of the supply steam.13. The turbomachine as claimed in claim 9 ,wherein six bores are formed.14. The turbomachine as claimed in claim 9 ,wherein the casing is formed as an inner casing and an outer casing is arranged around the inner casing.15. The turbomachine as claimed in claim 9 ,wherein the turbomachine is formed as a steam turbine. This application is the US National Stage of International Application No. PCT/EP2013/064429 filed Jul. 9, 2013, and claims the benefit thereof. The International Application claims the benefit of European Application No. ...

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Номер записи: 41
08-06-2017 дата публикации

THRUST BEARING AND ROTARY MACHINE

Номер: US20170159702A1
Автор: DANMOTO Yosuke, FUTAE Takaya, Ishizaki Tatsuya, KUBOTA Mitsushige, Suzuki Hiroshi
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

To reduce bearing loss due to an oil-shortage region on a pad facing a thrust collar, a thrust bearing according to at least one embodiment of the present invention includes a thrust collar, and at least one bearing pad disposed along a circumferential direction on a bearing surface, the at least one bearing pad having a tapered portion and a land portion. Each of the at least one bearing pad is formed so that a periphery portion on an outer side with respect to a radial direction gets closer to an inner side with respect to the radial direction toward an upstream side with respect to the rotational direction. 1. A thrust bearing , comprising:a thrust collar fixed to a rotational shaft; andat least one bearing pad disposed along a circumferential direction on a bearing surface facing the thrust collar, the at least one bearing pad having a tapered portion formed so that clearance between the at least one bearing pad and the thrust collar decreases toward a downstream side with respect to a rotational direction, and a land portion formed continuously from the tapered portion toward the downstream side with respect to the rotational direction so that the clearance is constant,wherein each of the at least one bearing pad is formed so that a periphery portion on an outer side with respect to a radial direction gets closer to an inner side with respect to the radial direction toward an upstream side with respect to the rotational direction.2. The thrust bearing according to claim 1 ,wherein the at least one bearing pad comprises a first bearing pad, and a second bearing pad disposed adjacently to the first bearing pad on a downstream side of the first bearing pad with respect to the rotational direction, andwherein a boundary line between the land portion of the first bearing pad and the tapered portion of the second bearing pad is formed so as to incline from the radial direction toward the downstream side with respect to the rotational direction.3. The thrust bearing ...

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Номер записи: 42
18-06-2015 дата публикации

COMPRESSOR OR TURBINE WITH BACK-DISK SEAL AND VENT

Номер: US20150167467A1
Автор: Guidry Mike, Reyenga James W., Thompson Glenn F.
Принадлежит: HONEYWELL INTERNATIONAL INC.

A turbine or compressor wheel mounted in a housing. The wheel is carried on two radial bearings both mounted in a wall of the housing. The wall has a venting orifice that is not impeded by moving parts such as bearings. The wall also has a circular seal member extending toward a back-disk of the wheel with only a very small clearance. The seal member is composed of a material significantly softer than the material of the wheel. 1. A rotary machine , comprising:a housing; anda rotor configured to rotate within the housing along an axis of rotor rotation, the rotor including a rotational pressure-changing wheel configured with a hub and with a plurality of blades, the plurality of blades being configured to exchange the pressure of gas passing through the blades and rotor kinetic rotational energy, and the hub includes a blade surface that carries and supports the blades, and a back-disk on an axially opposite side of the hub from the blade surface;wherein the housing forms a chamber wall facing the back-disk, the chamber wall and back-disk defining a back-disk chamber; andwherein the chamber wall forms an orifice that opens the back-disk chamber to an environment having a different pressure from the back-disk chamber, the orifice not being impeded by moving parts.2. The rotary machine of claim 1 , wherein the effective size of the orifice is selected to limit the pressure change of the back-disk chamber through the orifice.3. The rotary machine of claim 1 , and further comprising:a back-disk seal member, the back-disk seal member extending substantially between the back-disk and the chamber wall, the back-disk seal member extending circumferentially around the back-disk chamber;wherein the back-disk seal member is composed of a material significantly softer than the materials of the hub and the chamber wall.4. The rotary machine of claim 3 , wherein the back-disk seal member forms a plurality of separate sub-protrusions claim 3 , each separate sub-protrusion ...

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Номер записи: 43
18-06-2015 дата публикации

Low-pressure turbine

Номер: US20150167468A1
Автор: Patrick Bison, Sebastian Voss
Принадлежит: SIEMENS AG

A double-flow low-pressure partial turbine is provided herein, wherein the exhaust steam of the first flow and the exhaust steam of the second flow are deflected in a common direction within the outer housing and thus axial outlet flow occurs.

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Номер записи: 44
30-05-2019 дата публикации

Fluid recirculation turbine system

Номер: US20190162113A1
Автор: Hasham Hamzamiyan Chougule, Kiran Pithamber, Kiran.S Rao
Принадлежит: Honeywell International Inc

A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.

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Номер записи: 45
06-06-2019 дата публикации

THRUST BEARING SYSTEM WITH INVERTED NON-CONTACTING DYNAMIC SEALS FOR GAS TURBINE ENGINE

Номер: US20190170067A1
Автор: Caprario Joseph T.
Принадлежит:

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed. 1. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool comprising:providing a spool defining a longitudinal axis and including a thrust bearing supporting a hub and a compressor mechanically coupled to a turbine by said hub;establishing a first sealing relationship along the spool, including positioning a first non-contacting dynamic seal relative to the spool, the first non-contacting dynamic seal including a first body attached to a first floating shoe that seals with first rotatable inner surfaces of the spool to define a first flow cavity, and the first floating shoe radially inward of the first rotatable inner surfaces with respect to the longitudinal axis;establishing a second sealing relationship along the spool, including positioning a second non-contacting dynamic seal relative to the spool, the second non-contacting dynamic seal including a second body attached to a second floating shoe that seals with second rotatable inner surfaces of the spool to define a second flow cavity, and the second floating shoe radially inward of the second rotatable inner surfaces with respect to the longitudinal axis; andestablishing a third sealing relationship along the spool, including positioning a third non-contacting dynamic seal relative to the spool, the third non-contacting dynamic seal including a third body attached to a third floating shoe that seals with rotatable outer surfaces of the hub, the third non-contacting dynamic seal positioned axially between the first and second ...

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Номер записи: 46
06-06-2019 дата публикации

BALANCING SYSTEM AND METHOD FOR TURBOMACHINE

Номер: US20190170152A1
Автор: SCARBOLO Luca
Принадлежит:

The balancing system has a balancing body to be mounted on a rotor of a turbomachine and a sealing ring to be mounted on a stator of the turbomachine; the sealing ring is arranged around the balancing body so that the balancing body can rotate about a rotation axis, thus there is a clearance between the body and the ring; furthermore, there is an arrangement for changing an axial position of the sealing ring during operation of the turbomachine so that the clearance can be adjusted. The possibility of adjusting clearance during operation of the turbomachine, such balancing system provides a good balancing action with a small leakage and a small risk of mechanical interference at any time during operation of the turbomachine. 2. The balancing system of claim 1 , wherein an inner surface of the sealing ring is frustum shape.3. The balancing system of claim 1 , wherein an outer surface of the portion of the balancing body is frustum shape.4. The balancing system of claim 1 , further comprising a control unit arranged to control the arrangement so to adjust the clearance.5. The balancing system of claim 4 , wherein the control unit is arranged to perform an open-loop control or a closed-loop control.6. The balancing system of claim 1 , wherein the arrangement comprises an actuator being electric-type or a magnetic-type or a hydraulic-type or a pneumatic-type.7. The balancing system of claim 1 , wherein the balancing body has a first surface and a second surface claim 1 , wherein the balancing body is arranged so that a fluid at a first pressure exerts a force on the first surface and pushes the balancing body axially in a first sense and a fluid at a second pressure exerts a force on the second surface and pushes the balancing body axially in a second sense claim 1 , the second sense being opposite to the first sense.8. A turbomachine comprising a balancing system according to claim 1 , wherein the balancing body is fixed to a shaft of the turbomachine.9. A method of ...

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Номер записи: 47
18-09-2014 дата публикации

METHOD AND APPARATUS TO IMPROVE HEAT TRANSFER IN TURBINE SECTIONS OF GAS TURBINES

Номер: US20140271111A1
Автор: Ballard, Black Kenneth Damon, Bozkurt Ozgur, Danescu Radu Ioan, JR. Henry Grady
Принадлежит: GENERAL ELECTRIC COMPANY

A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide. 1. A system , comprising: a combustion section;', 'a turbine section coupled to the combustion section, wherein the turbine section comprises at least one turbine stage having a plurality of turbine blades coupled to a rotor, an inner casing circumferentially disposed about the plurality of turbine blades, and an outer casing circumferentially disposed about at least a portion of the inner casing, wherein the inner casing and the outer casing define a cavity between the inner casing and the outer casing, wherein the cavity comprises a volume extending between a forward portion and an aft portion to facilitate distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing, wherein the forward portion is closer to the combustion section than the aft portion, wherein the outer casing comprises at least one air inlet for the air to flow into the aft portion of the cavity, and the inner casing comprises at least one air outlet for the air to flow out of the forward portion of the cavity; and', 'at least one flange disposed within the cavity, wherein the at ...

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Номер записи: 48
04-06-2020 дата публикации

TURBOCHARGER

Номер: US20200173452A1
Автор: ASANO Hirohito, IGARASHI Naoki, IKEGAMI Hiroaki, TSUKIYAMA Takashi
Принадлежит: TOYOTA JIDOSHA KABUSHIKI KAISHA

A compressor wheel includes a shaft portion, which extends in the rotation axis direction of the compressor wheel. Blades protrude in the radial direction from the shaft portion. The blades are spaced apart from each other in the circumferential direction of the compressor wheel. The compressor housing has an accommodation space that accommodates the compressor wheel. The compressor housing also has an introduction passage defined therein. The introduction passage is connected to the accommodation space from the intake side and introduces intake air into the accommodation space. Plate-shaped guide vanes protrude from the inner wall surface of the introduction passage. The guide vanes are spaced apart from each other in the circumferential direction of the introduction passage. The number of the guide vanes is the smallest odd number that is greater than the number of the blades. 1. A turbocharger comprising:a compressor housing attached to an intake line; anda compressor wheel that is accommodated in the compressor housing, wherein a shaft portion that extends in a rotation axis direction of the compressor wheel, and', 'a plurality of blades that protrudes outward from the shaft portion in a radial direction,, 'the compressor wheel includes'}the blades are spaced apart from each other in a circumferential direction of the compressor wheel,an accommodation space and an introduction passage are defined in the compressor housing,the accommodation space is configured to accommodate the compressor wheel,the introduction passage is connected to the accommodation space from a first side in the rotation axis direction to introduce intake air into the accommodation space,a plurality of plate-shaped guide vanes protrude from an inner wall surface of the introduction passage,the guide vanes are spaced apart from each other in a circumferential direction of the introduction passage, anda number of the guide vanes is the smallest odd number that is greater than a number of the ...

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Номер записи: 49
15-07-2021 дата публикации

TURBINE AND THRUST LOAD ADJUSTING METHOD

Номер: US20210215046A1
Автор: Iwai Shogo, MAEDA Hideyuki, NISHIMURA Koki, OKUYAMA Tomomi, Ono Takahiro, Tashima Tsuguhisa
Принадлежит: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION

According to an embodiment, a turbine comprises: a casing; a rotor shaft; turbine stages; a thrust bearing which receives thrust load in the axial direction generated by a flow of a working fluid supplied to the turbine stages; a balance piston which is formed on the rotor shaft along a circumferential direction and projects in a radial direction from the rotor shaft, for adjusting a thrust contact pressure; and a thrust load adjusting mechanism which applies pressures of a pressure-increasing side and a pressure-decreasing side to at least one of a balance piston inner-side chamber and a balance piston outer-side chamber which sandwich the balance piston in the axial direction. 1. A turbine comprising:a casing;a rotor shaft penetrating the casing;a plurality of turbine stages arranged in the casing along an axial direction of the rotor shaft;a thrust bearing which receives thrust load in the axial direction generated by a flow of a working fluid supplied to the turbine stages;a balance piston which is formed on the rotor shaft along a circumferential direction and projects in a radial direction from the rotor shaft, for adjusting a thrust contact pressure applied to the thrust bearing; anda thrust load adjusting mechanism which applies pressures of a pressure-increasing side and a pressure-decreasing side to at least one of a balance piston inner-side chamber and a balance piston outer-side chamber which sandwich the balance piston in the axial direction.2. The turbine according to claim 1 ,wherein the thrust load adjusting mechanism comprises:a low pressure-side pipe connected to a low-pressure region;a high pressure-side pipe connected to a high-pressure region;a low pressure-side control valve disposed on the low pressure-side pipe;a high pressure-side control valve disposed on the high pressure-side pipe; anda controller which outputs an opening/closing command to the low pressure-side control vale and the high pressure-side control valve,wherein the low ...

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Номер записи: 50
11-06-2020 дата публикации

DEVICE FOR HOLDING A COOLING TUBE FOR A TURBOMACHINE CASING

Номер: US20200182058A1
Автор: BEAUQUIN Nicolas Jean-Marc Marcel, Blanchard Stephane Pierre Guillaume, MOREAUX Gaëlle Inès Méganne, MORLIERE Simon Nicolas
Принадлежит: SAFRAN AIRCRAFT ENGINES

A device for holding () at least one cooling tube () of a turbomachine casing () cooling system (), the holding device including a fixing frame (), a holding member () being configured to hold two cooling tubes (), and a connection assembly () between the holding member () and a fixing frame (), extending on either side of the frame, the connection assembly () comprising a connection part () extending through an opening () of the fixing frame from an outer portion () to the inner portion () of the connection assembly, the inner portion () being disposed between two cooling tubes () and secured to the holding member () while the outer portion () comprises a resilient return member () urged in compression towards the fixing frame by the connection part (). 1. A device for holding at least one cooling tube of a turbomachine casing cooling system , the holding device extending about an axis defining an axial direction and including a fixing frame adapted to be secured to the casing by being disposed in a radially outer manner with respect to the casing , a holding member configured to hold the cooling tube , and a connection assembly which connects the holding member and the fixing frame , wherein the connection assembly extends on either side of the fixing frame , defining with respect to the fixing frame an outer portion of the connection assembly radially external to the fixing frame and an inner portion of the connection assembly radially internal to the fixing frame , on the casing side , the connection assembly comprising a connection part extending through an opening of the fixing frame from the outer portion to the inner portion , the inner portion radially internal to the fixing frame being secured to the holding member while the outer portion comprises a resilient return member urged in compression towards the fixing frame by the connection part , wherein the holding member is configured to hold two axially adjacent cooling tubes , and the inner portion of the ...

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Номер записи: 51
23-07-2015 дата публикации

Coasting-wheel with aeronautic levitation for harmonic electric generation

Номер: US20150204205A1
Автор: Panteleev Milen K., Shaban Yasser R.
Принадлежит:

The present invention titled: a coasting-wheel with aeronautic levitation for harmonic electric generation is a device to generate electric energy or power via the principle of electromagnetic induction during the phase of energy-in and during the coasting phase; energy-off. It differs from the conventional electric generators and alternators as such the latter include an element of stator and an element of rotor but in the present invention the armature and magnets undergo rotation. Second, all electric generators operate in non-harmonic mode, i.e., when the input fuel is turned off the electric generator or alternator stops but in the present invention the electricity is generated during the coasting phase. It differs from the well-known apparatus flywheel as such the latter is a storage device and not a device for electric generation. In the present invention the coasting wheel is discharging its rotational kinetic energy into electric energy instantaneously during its spinning phase when the source of energy is turned off as well as it generates electricity during the phase of energy-in. 2. The apparatus of claim 1 , wherein the armature (coil conductor) and permanent magnets undergo simultaneous rotation in the opposite direction during the phase of energy-in.3. The apparatus of claim 1 , wherein the armature (coil conductor) and permanent magnets undergo simultaneous rotation in the opposite direction during the phase of energy-off (during the coasting phase).5. The apparatus of claim 4 , wherein the armature (coil conductor) and permanent magnets undergo simultaneous rotation in the opposite direction during the phase of energy-in.6. The apparatus of claim 4 , wherein the armature (coil conductor) and permanent magnets undergo simultaneous rotation in the opposite direction during the phase of energy-off (during the coasting phase). Not ApplicableIndividual EffortsIt may be argued that the function of the present invention is related to the function of the ...

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Номер записи: 52
14-07-2016 дата публикации

GAS TURBINE ENGINE MID-TURBINE FRAME TIE ROD ARRANGEMENT

Номер: US20160201512A1
Автор: Bauer Steven J., Chuong Conway, Dale Timothy, Liebel Christina S.
Принадлежит:

A gas turbine engine mid-turbine frame includes inner and outer cases that are arranged about an engine axis. A radial plane is arranged normal to the engine axis. The inner and outer cases are secured to one another by a tie rod that extends along a longitudinal axis. The longitudinal axis is arranged at an acute angle relative to the radial plane. 1. A gas turbine engine mid-turbine frame comprising:inner and outer cases arranged about an engine axis, a radial plane arranged normal to the engine axis, the inner and outer cases secured to one another by a tie rod that extends along a longitudinal axis, the longitudinal axis arranged at an acute angle relative to the radial plane.2. The mid-turbine frame according to claim 1 , wherein the acute angle is between 0°-30°.3. The mid-turbine frame according to claim 2 , wherein the acute angle is between 3°-15°.4. The mid-turbine frame according to claim 3 , wherein the acute angle is between 5°-9°.5. The mid-turbine frame according to claim 1 , comprising an airfoil arranged between the inner and outer cases claim 1 , and the tie rod extending through the airfoil.6. The mid-turbine frame according to claim 5 , wherein the outer case includes a boss that has a hole claim 5 , and a fastener received in the hole and secured to an end of the tie rod claim 5 , the fastener abutting a surface of the boss claim 5 , the surface extending in a generally axial direction that is arranged at the acute angle relative to the engine axis.7. The mid-turbine frame according to claim 5 , wherein the tie rod includes a flange secured to the inner case and arranged at the acute angle.8. A gas turbine engine comprising:a turbine section including high and low pressure turbines; 'inner and outer cases arranged about an engine axis, a radial plane arranged normal to the engine axis, the inner and outer cases secured to one another by a tie rod that extends along a longitudinal axis, the longitudinal axis arranged at an acute angle relative to ...

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Номер записи: 53
02-07-2020 дата публикации

ACTIVE THRUST MANAGEMENT OF A TURBOPUMP WITHIN A SUPERCRITICAL WORKING FLUID CIRCUIT IN A HEAT ENGINE SYSTEM

Номер: US20200208536A1
Автор: BOWAN Brett
Принадлежит:

Aspects of the invention disclosed herein generally provide a heat engine system, a turbopump system, and methods for lubricating a turbopump while generating energy. The systems and methods provide proper lubrication and cooling to turbomachinery components by controlling pressures applied to a thrust bearing in the turbopump. The applied pressure on the thrust bearing may be controlled by a turbopump back-pressure regulator valve adjusted to maintain proper pressures within bearing pockets disposed on two opposing surfaces of the thrust bearing. Pocket pressure ratios, such as a turbine-side pocket pressure ratio (P1) and a pump-side pocket pressure ratio (P2), may be monitored and adjusted by a process control system. In order to prevent damage to the thrust bearing, the systems and methods may utilize advanced control theory of sliding mode, the multi-variables of the pocket pressure ratios P1 and P2, and regulating the bearing fluid to maintain a supercritical state. 1. A heat engine system , comprising:a working fluid circuit to contain a working fluid, the working fluid circuit having a high pressure side and a low pressure side, wherein a portion of the working fluid is in a supercritical state when the heat engine system is in operation;a heat exchanger fluidly coupled to and in thermal communication with the high pressure side of the working fluid circuit and fluidly coupled to and in thermal communication with a heat source stream, the heat exchanger to transfer thermal energy from the heat source stream to the working fluid within the high pressure side;an expander fluidly coupled to the working fluid circuit and disposed between the high pressure side and the low pressure side to convert a pressure drop in the working fluid to mechanical energy;a rotating shaft coupled to the expander to drive a device with the mechanical energy;a recuperator fluidly coupled to the working fluid circuit to transfer thermal energy from the working fluid in the low ...

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Номер записи: 54
11-07-2019 дата публикации

TURBINE WITH PRESSURE DISTRIBUTER

Номер: US20190211747A1
Автор: Colodel Luiz-Alexandre, Di Giandomenico Giuseppe, Uhlmann Dietmar
Принадлежит:

The invention relates to a turbine () having an impeller () arranged in a housing (). The turbine () has an inflow region () and an outflow region () and a working medium flows through said turbine during operation. The working medium flows into the inflow region (), along a front side () formed on the impeller () and subsequently out of the outflow region (). There is a pressure drop at the front side () between the inflow region () and the outflow region (). A pressure distributer () is arranged on the rear side () of the impeller (), opposite the front side (). The pressure distributer () comprises a slide ring (), which cooperates with the rear side () of the impeller () and thereby forms a vapour-lubricated throttle. A first flow path () runs through the throttle, wherein the throttle hydraulically divides the rear side () into a first region () and a second region (). The first region () borders the inflow region (), and the second region borders a pressure chamber (). During operation, the inflow region () is applied with a higher pressure than the pressure chamber (). The slide ring () is axially moveable. A sealing ring () arranged in a groove () cooperates with the slide ring (). A second flow path () runs from the inflow region () to the pressure chamber () between the groove () and the slide ring (). The second flow path () can be closed by the sealing ring (). The sealing ring () can be moved in the groove () in a defined manner. 1202326202122212323222321229232323931232351232312322312111211131334131522111413152333341aababb. A turbine () having an impeller () arranged in a housing () , wherein the turbine () has an inflow region () and an outflow region () and a working medium flows through said turbine during operation , wherein the working medium flows into the inflow region () , along a front side () formed on the impeller () and subsequently out of the outflow region () , wherein there is a pressure drop on the front side () between the inflow region ...

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Номер записи: 55
10-08-2017 дата публикации

BALANCING OF AXIAL THRUST FORCES WITHIN A GAS TURBINE ENGINE

Номер: US20170226859A1
Автор: Edwards David A., THORNTON Stewart T.
Принадлежит: ROLLS-ROYCE PLC

A thrust balancing mechanism for balancing axial loads on a rotor thrust bearing is described. The mechanism comprises a piston arrangement axially mounted on a stationary structure about a centre axis arranged, in use, in coaxial alignment with a rotating shaft carrying the rotor thrust bearing A hydrodynamic thrust bearing is mounted, in use, between the piston and the rotor thrust bearing The piston is pressurised so as to impart to the rotor thrust bearing via the hydrodynamic thrust bearing an axial load which counters an axial load imparted to the rotor thrust bearing by the rotating shaft 1. A thrust balancing mechanism for balancing axial loads on a rotor thrust bearing , the mechanism comprising at least one piston axially mounted on a stationary structure , about a centre axis arranged , in use , in coaxial alignment with a rotating shaft carrying the rotor thrust bearing , and one or more hydrodynamic thrust bearings mounted , in use , between the piston(s) and the rotor thrust bearing , the piston(s) pressurised so as to impart to the rotor thrust bearing via the hydrodynamic thrust bearing an axial load which counters an axial load imparted to the rotor thrust bearing by the rotating shaft.2. A thrust balancing mechanism as claimed in further including an annular plate arranged claim 1 , in use claim 1 , axially between the hydrodynamic thrust bearing and the rotor thrust bearing arrange such that the piston(s) transmits an axial load via the hydrodynamic thrust bearing to the annular plate which is fixedly mounted to the rotating shaft.3. A thrust balancing mechanism as claimed in wherein the piston(s) comprise a single annular piston.4. A thrust balancing mechanism as claimed in wherein the pistons comprise multiple pistons arranged in an annular configuration.5. A thrust balancing mechanism as claimed in wherein the pistons are operable independently of each other to balance a localised axial load.6. A thrust balancing mechanism as claimed in wherein ...

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Номер записи: 56
27-08-2015 дата публикации

CASE ASSEMBLY FOR A GAS TURBINE ENGINE

Номер: US20150240662A1
Автор: Blume Karl D., Niggemeier Chris J.
Принадлежит:

A case for a gas turbine engine includes an integrated HPC Diffuser case operable to contain a combustor section and a portion of a High Pressure Compressor. 1. A case for a gas turbine engine comprising:an integrated High Pressure Compressor Diffuser case operable to contain a combustor section and a portion of a compressor section.2. The case as recited in claim 1 , wherein said integrated HPC Diffuser case is a housing with a reinforced area.3. The case as recited in claim 2 , wherein said reinforced area defines an increased thickness.4. The case as recited in claim 1 , wherein said integrated HPC Diffuser case includes a HPC flange to provide a bolted connection with a HPC case.5. The case as recited in claim 1 , wherein said integrated HPC Diffuser case includes a HPT flange to provide a bolted connection with a HPT case.6. The case as recited in claim 1 , wherein said integrated HPC Diffuser case includes a HPC flange to provide a bolted connection with a HPC case and a HPT flange to provide a bolted connection with a HPT case.7. The case as recited in claim 6 , wherein no flange is located between said HPC flange and said HPT flange.8. The case as recited in claim 7 , wherein a boss arrangement is located between said HPC flange and said HPT flange.9. The case as recited in claim 1 , wherein said portion of said compressor section includes two stages.10. The case as recited in claim 1 , wherein said portion of said compressor section includes two stages of an eight stage High Pressure Compressor.11. A case assembly of a gas turbine engine comprising:a fan case;an intermediate case boltable to said fan case;a High Pressure Compressor case boltable to said intermediate case;an integrated High Pressure Compressor Diffuser case boltable to said High Pressure Compressor case;a High Pressure Turbine case boltable to said integrated High Pressure Compressor Diffuser case;a Mid Turbine Frame case boltable to said High Pressure Turbine case;a Low Pressure Turbine ...

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Номер записи: 57
17-08-2017 дата публикации

STEAM TURBINE AND METHOD FOR OPERATING A STEAM TURBINE

Номер: US20170234131A1
Автор: de Lazzer Armin, Walkenhorst Jan, Zander Uwe
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A steam turbine having a cooling option, in which steam is taken from the flow channel, the steam cooling the thrust-compensating intermediate floor, being mixed with a small amount of live steam and being returned to the flow channel. A method cools the steam turbine, wherein steam is extracted from the high-pressure region and is fed to a space between the thrust-compensating partition wall and inner casing, wherein steam from the space between the thrust-compensating partition wall and the inner casing is fed via a first cross feedback passage to the high-pressure region. 1. A steam turbine comprising:an inner casing and an outer casing and also a rotor which is arranged in a rotatably supported manner inside the inner casing,wherein the outer casing is arranged around the inner casing,wherein the rotor has a high-pressure region which is arranged along a first flow direction and an intermediate-pressure region which is arranged along a second flow direction,wherein the inner casing has a plurality of high-pressure stator blades in the high-pressure region, which are arranged in such a way that a high-pressure flow passage, having a plurality of high-pressure blading stages which in each case have a row of high-pressure rotor blades and a row of high-pressure stator blades, is formed along the first flow direction,wherein the inner casing has a plurality of intermediate-pressure stator blades in the intermediate-pressure region, which are arranged in such a way that an intermediate-pressure flow passage, having a plurality of intermediate-pressure blading stages which in each case have a row of intermediate-pressure rotor blades and a row of intermediate-pressure stator blades, is formed along the second flow direction,wherein the rotor has a thrust-compensating partition wall between the high-pressure region and the intermediate-pressure region,wherein the inner casing has a connection which, as a communicating pipe, is formed between the high-pressure flow ...

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Номер записи: 58
10-09-2015 дата публикации

MODULAR TURBOMACHINE INNER AND OUTER CASINGS WITH MULTI-STAGE STEAM EXTRACTION SITES

Номер: US20150252681A1
Автор: Amirtharajah Jeyaruban Selliah, Kotian Dayananda Thukra, Swan Stephen Roger
Принадлежит: GENERAL ELECTRIC COMPANY

Various embodiments include methods and apparatuses of forming turbomachine casing intermediate structures. In some embodiments apparatuses include a steam turbomachine casing intermediate structure including an inner shell having an external surface and inner shell cavity, and defining an opening for allowing fluid entry to the cavity and an outer shell having an internal surface, these surfaces defining at least one closed, axial-extending chamber, the inner shell and outer shells each having access regions adjacent the closed chamber, each of the access regions including a plurality of locations, selectable to be machined to create an exhaust slot or an exhaust opening in the inner casing or the outer casing, respectively, and wherein a structural integrity of the casing is uniform regardless of which of the axial locations are selected to be machined, where the exhaust opening is fluidly connected with the at least one closed chamber through the outer shell. 1. A steam turbomachine casing intermediate structure comprising:an inner shell having an external surface, wherein a material of the inner shell defines an inner shell cavity, and wherein the material of the inner shell defines an opening for allowing fluid from a steam path of the turbomachine to enter the inner shell cavity; andan outer shell having an internal surface, the internal surface of the outer shell and the external surface of the inner shell defining at least one closed chamber extending in an axial direction of the steam turbomachine,the inner shell having a first access region adjacent the at least one closed chamber, the first access region including a plurality of inner shell axial locations, wherein at least one of the plurality of inner shell axial locations is selectable to be machined to create an exhaust slot for allowing fluid to exit the inner shell cavity and enter the at least one closed chamber, and wherein a structural integrity of the casing is uniform regardless of which of the ...

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Номер записи: 59
01-09-2016 дата публикации

METHOD AND SYSTEM FOR A CERAMIC MATRIX COMPOSITE SHROUD HANGER ASSEMBLY

Номер: US20160251982A1
Автор: Shapiro Jason David
Принадлежит:

A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud. 1. A shroud and shroud hanger assembly for a gas turbine engine , said assembly comprising:a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion; anda shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud.2. The shroud and hanger assembly of claim 1 , wherein said forward and aftward hanger portions are configured to couple together using a mechanical fastener connection.3. The shroud and hanger assembly of claim 1 , wherein said forward and aftward hanger portions are configured to couple together using a bolted connection.4. The shroud and hanger assembly of claim 1 , wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion.5. The shroud and hanger assembly of claim 1 , wherein the first and second materials are ceramic matrix composite materials.6. The shroud and hanger assembly of claim 1 , wherein said shroud is supported radially by a pin extending thorough radially outwardly extending walls of said shroud and extending through radially inwardly extending legs of said ...

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Номер записи: 60
24-09-2015 дата публикации

TOOL FOR REMOVING AN INNER CASING FROM A TURBOMACHINE

Номер: US20150267563A1
Автор: FROIDEVAUX Gerard, HUBER Tobias Christoph, ROZMAN Ivan, SCHWARZ Karsten, Seng Daniel
Принадлежит:

A tool for installing or uninstalling a segment of an inner housing of a turbomachine. The turbomachine includes an outer housing, at least partially surrounding an inner housing and a rotor, concentrically arranged within the inner housing. The rotor is equipped with a number of rotor grooves. The inner housing is divided at an essentially horizontal split plane into an upper segment and a lower segment. The tool includes a first portion insertable into any of the rotor grooves, and furthermore includes a second portion disposed at a distance from the first portion. This second portion is connectable to the lower segment of the inner housing. 1. A tool for installing or uninstalling a segment of an inner housing of a turbomachine , wherein this turbomachine includes an outer housing , at least partially surrounding an inner housing and a rotor , concentrically arranged within the inner housing , the rotor being equipped with a number of rotor grooves , and wherein the inner housing is divided at an essentially horizontal split plane into an upper segment and a lower segment , the tool comprising a first portion , this portion being insertable into any of said rotor grooves , and furthermore comprises a second portion , disposed at a distance from the first portion , this second portion being connectable to the lower segment of the inner housing.2. The tool according to claim 1 , wherein the first portion comprises a section that is complementarily designed to the contour of the rotor grooves.3. The tool according to claim 1 , wherein a section of the first portion is designed as a fir tree.4. The tool according to claim 1 , at least comprising a first portion claim 1 , designed for insertion into any of the rotor grooves claim 1 , a second portion claim 1 , designed to be connected to a part of the lower segment of the inner housing claim 1 , and a platform connecting said first portion with said second portion.5. The tool according to claim 4 , wherein the second ...

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Номер записи: 61
01-10-2015 дата публикации

STRUCTURAL GUIDE VANE CIRCUMFERENTIAL LOAD BEARING SHEAR PIN

Номер: US20150275694A1
Автор: Conner Steven L., Feigleson Steven J., Hyatt Thomas B., KLINETOB Carl Brian, Reinhardt Gregory E., Rembish Paul Thomas
Принадлежит:

A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads. 1. A turbofan engine comprising:a fan case circumscribing a plurality of fan blades disposed about an axis;a core engine case including a bulkhead disposed about the axis;at least one structural guide vane attached on an outer end to the fan case and at an inner end to the bulkhead; anda shear pin extending between the inner end of the structural guide vane and the bulkhead.2. The turbofan engine as recited in claim 1 , wherein the inner end of the structural guide vane includes a forward portion attached to a forward case and an aft portion attached to the bulkhead.3. The turbofan engine as recited in claim 2 , wherein a plurality of forward fasteners extend transverse to the axis through corresponding openings in the forward portion of the inner side into the forward case and a plurality of aft fasteners extend through a corresponding plurality of openings in the bulkhead substantially parallel to the axis for securing the inner end to the bulkhead.4. The turbofan engine as recited in claim 3 , wherein the inner end of the structural guide vane includes openings corresponding with the plurality of openings in the bulkhead and the shear pin is disposed between the openings in the inner end of the structural guide vane.5. The turbofan engine as recited in claim 4 , wherein the bulkhead includes blind holes that receive a corresponding shear pin.6. The turbofan engine as recited in claim 3 , wherein an interface between the aft portion of the structural guide vane and the bulkhead includes mating aligning surfaces.7. The turbofan engine as recited in claim 6 , wherein the aligning surfaces includes diverging aft surface of the inner ...

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Номер записи: 62
13-08-2020 дата публикации

Turbine Engine Tie Rod Systems

Номер: US20200256216A1
Автор: Feindel David T., Kantany Nicholas W., Rappoli Nico M.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine turbine section has tie rod assemblies interconnecting an inner diameter structure and an outer casing. Each tie rod has: an inner diameter end; an outer diameter end; and an eyelet of an outer diameter spherical bearing formed at the outer diameter end. A first clevis carries a spherical ball of the bearing, a shank of said clevis extending to an outer diameter (OD) end. A tensioning bolt is mated to a threaded opening in said clevis OD end whereby tightening said bolt applies a tension to said rod. A radial span between a center of the outer diameter spherical bearing and an inner diameter surface of the outer casing is at least 50% greater than that between an outer diameter (OD) surface of the outer ring and the center. 2. The gas turbine engine turbine section of claim 1 , the tie rod assemblies further comprising: 'the strut extends radially between the clevis OD end and the outer casing to transmit the tension from the associated rod to the outer casing.', 'a plurality of struts, each strut respectively associated with an associated one of the tie rods, wherein3. The gas turbine engine turbine section of wherein:each strut has a hollow body extending between an outer diameter end an inner diameter end;the inner diameter end has a web; andthe associated tensioning bolt extends through the web.4. The gas turbine engine turbine section of wherein:each strut outer diameter end has one or more laterally outwardly protruding mounting projections; andone or more fasteners secure the one or more mounting projections to the outer casing.5. The gas turbine engine turbine section of wherein:each strut is formed of a wrought nickel-based alloy.6. The gas turbine engine turbine section of wherein:a radial span between a center of the outer diameter spherical bearing and the clevis shank OD end is at least 50% greater than a radial span between an outer diameter (OD) surface of the outer ring and the center of the spherical bearing.7. The gas turbine ...

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Номер записи: 63
27-08-2020 дата публикации

PIVOT FOR A SLIDING BEARING

Номер: US20200271008A1
Автор: Dombek Alexis Claude Michel, LEMOINE Julie Marie Renée
Принадлежит:

The invention relates to a pivot () for a sliding bearing of an epicyclic train, comprising an annular wall () defining an axial passage () and comprising a first () and a second () annular groove opening axially in opposite directions (L, L) and each defined by two coaxial inner () and outer () annular branches formed at the axial ends of the annular wall (). According to the invention, the recesses () are made in at least one bottom wall () of one of the annular grooves (). 19.-. (canceled)10. A pivot for a sliding bearing of an epicyclic train , comprising an annular wall defining an axial passage and comprising a first and a second annular groove opening axially in opposite directions and each defined by two coaxial inner and outer annular branches formed at the axial ends of the annular wall , characterized in that recesses are formed in at least one bottom wall of one of the annular grooves.11. A pivot according to claim 10 , wherein the recesses are distributed around the axial passage.12. A pivot according to claim 11 , wherein the recesses are regularly distributed around the axial passage.13. A pivot according to claim 10 , wherein the recesses are holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove.14. A pivot according to claim 11 , wherein the recesses are holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove.15. A pivot according to claim 12 , wherein the recesses are holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove.16. A pivot according to claim 11 , wherein the holes are substantially straight.17. A pivot according to claim 16 , wherein the holes are inclined relative to an axis of the axial passage.18. The pivot according to claim 17 , wherein the holes are inclined relative to the axis of the axial passage by an angle between 0° and 30°.19. An ...

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Номер записи: 64
12-10-2017 дата публикации

ASSEMBLY, IN PARTICULAR OF ENGINE COMPONENTS

Номер: US20170292408A1
Автор: CATALDI Giovanni, SCHAEFER Martin, SISTANINIA Meisam, UGEL Diego
Принадлежит: ANSALDO ENERGIA SWITZERLAND AG

An assembly of at least two members. One of the members supports the other member, the assembly defining an axial direction, a radial direction, and a circumferential direction, an inner member of the at least two members being received radially inside an outer member of the at least two members, wherein the inner member and the outer member am attached to each other by a support arrangement, the support arrangement including at least one floating support assembly as a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at the outer member. A displacement of support points in a radial direction results in an interrelated relative displacement of the support points in an axial direction end vice versa. 1. An assembly comprising:at least two members, wherein one of the members supports the other member, the assembly defining an axial direction (x), a radial direction (r), and a circumferential direction;{'b': '10', 'an inner member of said at least two members being received radially inside an outer member () of said at least two members, wherein the inner member and the outer member are attached to each other by a support arrangement, the support arrangement including;'}at least one floating support assembly, wherein the floating support assembly provides a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at outer member, the floating support assembly being arranged and configured to provide for a guided relative displacement between the inner member support point and the outer member support point along a displacement path; andwherein the displacement path of the reiative diSplacement is inclined with respect to the axial direction (x) as well as to the radial direction (r) at a nonzero angle (Θ), such that a relative displacement of the support points in the radial direction will result in an interrelated ...

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Номер записи: 65
03-09-2020 дата публикации

PIVOT FOR A SLIDING BEARING

Номер: US20200277877A1
Автор: Dombek Alexis Claude Michel, LEMOINE Julie Marie Renée
Принадлежит:

The invention relates to a pivot () for a sliding bearing of an epicyclic train, comprising an annular wall defining an axial passage and comprising a first () and a second annular groove opening axially in opposite directions and each defined by two coaxial inner () and outer () annular branches formed at the axial ends of the annular wall. According to the invention, the pivot comprises a plurality of first holes () opening at a first end into the first annular groove () and at a second opposite end into the second annular groove, these holes being made over an angular sector of between 5° and 330°. 18.-. (canceled)9. Pivot for a sliding bearing of an epicyclic train , comprising an annular wall delimiting an axial passage and comprising a first and a second annular grooves opening axially in opposite directions and each delimited by two coaxial inner and outer annular branches formed at the axial ends of the annular wall , characterised in that it comprises a plurality of first holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove , these holes being produced over an angular sector between 05° and 330°.10. Pivot according to claim 9 , the first holes being produced over an angular sector between 180° and 330°.11. Pivot according to claim 9 , wherein a counterbore is provided at the opening of at least one of the first end and the second end of each of the first holes.12. Pivot according to claim 9 , wherein the first holes are substantially straight.13. Pivot according to claim 9 , wherein the first openings are inclined relative to an axis of the axial passage.14. Pivot according to claim 13 , wherein the first openings are inclined relative to the axis of the axial passage by an angle of between 0° and 30°.15. Pivot according to claim 11 , wherein the first openings are inclined relative to an axis of the axial passage.16. Pivot according to claim 12 , wherein the first openings are inclined ...

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Номер записи: 66
29-10-2015 дата публикации

ACCESS PANEL(S) FOR AN INNER NACELLE OF A TURBINE ENGINE

Номер: US20150308291A1
Автор: Brown Keith T.
Принадлежит: Rohr, Inc.

An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least partially cover an aperture in the nacelle wall. The outer nacelle axially overlaps the access panel. 1. An assembly for a turbine engine with an axial centerline , the assembly comprising:an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;the inner nacelle including a nacelle wall and at least one access panel adapted to at least partially cover an aperture in the nacelle wall;wherein the outer nacelle axially overlaps the access panel.2. The assembly of claim 1 , further comprising:a bifurcation extending radially between the outer nacelle and the inner nacelle;wherein the outer nacelle, the inner nacelle and the bifurcation form an O-duct through which the bypass flowpath axially extends.3. The assembly of claim 1 , wherein the nacelle wall has an outer surface that extends axially along and at least three hundred and twenty degrees around the centerline.4. The assembly of claim 1 , whereinthe nacelle wall extends axially along the centerline; andthe aperture extends axially within and radially through the nacelle wall.5. The assembly of claim 1 , whereinthe nacelle wall extends axially along the centerline; andthe aperture extends circumferentially within and radially through the nacelle wall.6. The assembly of claim 1 , wherein the access panel extends circumferentially to a panel side claim 1 , and the access panel is hinged to the nacelle wall at the panel side.7. The assembly of claim 1 , wherein the access panel is removably fastened to the nacelle wall.8. The assembly of claim 1 , further comprising:a second access panel adapted to partially cover the aperture in the nacelle wall;wherein the access panel and the second access panel are ...

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Номер записи: 67
29-10-2015 дата публикации

COMPRESSOR WITH THRUST BALANCING AND METHOD THEREOF

Номер: US20150308443A1
Автор: ALBAN Thomas, Stalder Benjamin
Принадлежит:

A compressor for a motor-compressor set, comprising, on a rotating shaft, a balancing piston, a set of bladed wheels, a rear cavity of the piston adjacent to the balancing piston on a side opposite to the set of bladed wheels, a regulation valve suitable for coupling the rear cavity to the input of the set of bladed wheels, a suction pressure chamber coupled to the input of the set of bladed wheels, the rear cavity being arranged between the balancing piston and the suction pressure chamber. The compressor comprises a discharge pressure chamber arranged between the rear cavity of the piston and the suction pressure chamber, the discharge pressure chamber being coupled via a discharge line to a discharge area between the set of bladed wheels and the balancing piston. 1. A compressor for a motor-compressor set , the compressor comprising:a rotating shaft;a balancing piston;a set of bladed wheels;a rear cavity of the balancing piston adjacent to the balancing piston on a side opposite to the set of bladed wheels;a regulation valve configured to couple the rear cavity to the input of the set of bladed wheels;a suction pressure chamber coupled to the input of the set of bladed wheels, wherein the rear cavity is between the balancing piston and the suction pressure chamber; anda discharge pressure chamber between the rear cavity of the balancing piston and the suction pressure chamber, the discharge pressure chamber being coupled via a discharge line to a discharge area between the set of bladed wheels and the balancing piston.2. The compressor according to claim 1 , further comprising an input flange emerging on a gas input line coupled to the input of the set of bladed wheels.3. The compressor according to claim 1 , further comprising labyrinth seals between the suction pressure chamber and the discharge pressure chamber on the one hand claim 1 , and between the discharge pressure chamber and the rear cavity of the balancing piston on the other hand.4. The compressor ...

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Номер записи: 68
24-09-2020 дата публикации

LINER APPARATUS AND METHOD OF INSPECTING AND/OR CLEANING A LINER ANNULAR REGION

Номер: US20200300125A1
Автор: Cheng Daniel, Coulibaly Mahamoud, Parsons Rachelle, Rosencrans Paul, Singh Anshuman
Принадлежит:

A liner for a gas turbine engine is provided that includes an outer wall, an inner wall, and a plurality of structural elements disposed between the inner wall and the outer wall. The outer wall is spaced apart from the inner wall and is disposed radially outside of the inner wall. The outer wall and inner wall form an annular structure having a circumference, and an annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall. Each of the structural elements is attached to the outer wall and the inner wall. The outer wall includes at least one inspection port extending through the outer wall configured for access to the annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall. 1. A liner for a gas turbine engine , comprising:an outer wall;an inner wall;wherein the outer wall is spaced apart from the inner wall and is disposed radially outside of the inner wall, the outer wall and inner wall forming an annular structure having a circumference, and an annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall; anda plurality of structural elements disposed between the inner wall and the outer wall, and each of the plurality of structural elements is attached to the outer wall and the inner wall;wherein the outer wall includes at least one inspection port extending through the outer wall configured for access to the annular region disposed between the first interior surface of the outer wall and the second interior surface of the inner wall.2. The liner of claim 1 , wherein the outer wall includes first cooling apertures claim 1 , and wherein the at least one inspection port disposed in the outer wall has an area that is greater than the area of any of the first cooling apertures.3. The liner of claim 1 , further including at least one an inspection port cover ...

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Номер записи: 69
03-10-2019 дата публикации

Turbocharger

Номер: US20190301304A1
Автор: Albrecht Daniel, BRAUN Steffen, DENKEL Harald, HAAS Bernd, NIEBUHR Johannes, Spatz Urban, WEIHARD Stefan
Принадлежит:

A turbocharger, with a turbine for expanding a first medium, a compressor for compressing a second medium utilising energy extracted in the turbine during expansion of the first medium. A turbine housing and a compressor housing are connected to a bearing housing. A casing radially and axially surrounds the turbine housing, the compressor housing, and/or the bearing housing at least in sections, which is connected to the respective housing via multiple fastening devices. At least some of the fastening devices extend through a wall of the casing into the housing include metallic damping elements made of wire on opposite sides of the wall of the casing through which the same extend. 1. A turbocharger , comprising:a turbine for expanding a first medium;a turbine housing of the turbine;a compressor for compressing a second medium utilising energy extracted in the turbine during expansion of the first medium;a compressor housing of the compressor;a bearing housing arranged between and connected to the turbine housing and the compressor housing;a casing that radially and axially surrounds at least in sections one or more of the turbine housing, the compressor housing, and the bearing housing;multiple fastening devices configured to connect the casing to the respective housing to be surrounded by extending through a respective wall of the casing into the housing to be encased; andat least one of the multiple fastening devices, comprises metallic damping elements made of wire on sides located opposite the respective wall of the casing through which the at least one of the multiple fastening devices extends.2. The turbocharger according to claim 1 , wherein the metallic damping elements are formed as wire pads.3. The turbocharger according to claim 2 , wherein the wire pads comprise multiple layers of a wire fabric claim 2 , a wire mesh claim 2 , or a knitted wire fabric.4. The turbocharger according to claim 3 , wherein the multiple layers are connected to one another.5. ...

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Номер записи: 70
19-11-2015 дата публикации

METHOD FOR BALANCING THRUST, TURBINE AND TURBINE ENGINE

Номер: US20150330220A1
Автор: "DErcole Michele", ASTI Antonio, Ceccherini Alberto, CEI Stefano, Landi Giacomo
Принадлежит:

A turbine comprising a rotatable rotor and a pressure chamber; a wall of the pressure chamber is arranged to act on the rotor so that to balance thrust exerted by the rotor when it rotates; a conduit connects the pressure chamber and arranged to a pressure source; a valve associated to the conduit may open and close the conduit; the valve is arranged to open automatically when the pressure upstream of the valve exceeds a first predetermined threshold value; in this way, when the load of the turbine is high excessive thrust is balanced because of the higher pressure in the pressure chamber.

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Номер записи: 71
01-11-2018 дата публикации

SYSTEMS AND METHODS FOR DYNAMIC BALANCING OF STEAM TURBINE ROTOR THRUST

Номер: US20180313215A1
Автор: Mehra Mahendra Singh
Принадлежит:

The present application provides a steam turbine system. The steam turbine system may include a rotor, a high pressure section positioned about the rotor, one or more high pressure extraction conduits extending from the high pressure section, a high pressure control valve positioned on each of the high pressure extraction conduits, an intermediate pressure section positioned about the rotor, one or more intermediate pressure extraction conduits extending from the intermediate pressure section, an intermediate pressure control valve positioned on each of the intermediate pressure extraction conduits, and a controller in communication with the high pressure control valves and the intermediate pressure control valves and operable to selectively adjust respective positions of the high pressure control valves and the intermediate pressure control valves to balance thrust acting on the rotor. 1. A steam turbine system , comprising:a rotor;a high pressure section positioned about the rotor;one or more high pressure extraction conduits extending from the high pressure section and configured to direct one or more high pressure extraction flows of steam;a high pressure control valve positioned on each of the high pressure extraction conduits;an intermediate pressure section positioned about the rotor;one or more intermediate pressure extraction conduits extending from the intermediate pressure section and configured to direct one or more intermediate pressure extraction flows of steam;an intermediate pressure control valve positioned on each of the intermediate pressure extraction conduits; anda controller in communication with the high pressure control valves and the intermediate pressure control valves, wherein the controller is operable to selectively adjust respective positions of the high pressure control valves and the intermediate pressure control valves to balance thrust acting on the rotor.2. The steam turbine system of claim 1 , further comprising a thrust bearing ...

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Номер записи: 72
08-11-2018 дата публикации

ROTARY MACHINE AND METHOD FOR CONTROLLING ROTARY MACHINE

Номер: US20180320551A1
Автор: Hashimoto Shinya, IIJIMA Takayoshi, Kataoka Masahito
Принадлежит:

A rotary machine, including: 1. A rotary machine , comprising:a rotor extending in an axial direction, the rotor comprising a first thrust collar and a second thrust collar projecting radially outward;a first thrust bearing device configured to receive load acting in the axial direction via the first thrust collar;a second thrust bearing device configured to receive load acting in the axial direction via the second thrust collar; anda load control device configured to control load acting on at least one of the first thrust bearing device and the second thrust bearing device.2. The rotary machine according to claim 1 , whereinthe second thrust bearing device comprises a second thrust bearing body configured to support a surface of the second thrust collar facing the axial direction; andthe load control device comprises a drive device configured to press the second thrust bearing body in the axial direction.3. The rotary machine according to claim 2 , whereinthe second thrust bearing body comprises a bearing pad configured to support load from the second thrust collar, and a carrier ring configured to support the bearing pad; andthe drive device is configured to press the bearing pad.4. The rotary machine according to claim 2 , whereinthe second thrust bearing body comprises a bearing pad configured to support load from the second thrust collar, and a carrier ring configured to support the bearing pad; andthe drive device is configured to press the carrier ring.5. The rotary machine according to claim 2 , wherein the second thrust bearing body is disposed only on one side of the second thrust collar in the axial direction.6. The rotary machine according to claim 5 , whereinthe first thrust bearing device comprises a first thrust bearing body configured to support a surface of the first thrust collar facing the axial direction; andthe first thrust bearing body is disposed on either side of the first thrust collar in the axial direction.7. The rotary machine according ...

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Номер записи: 73
17-10-2019 дата публикации

METHOD FOR THE ASSEMBLY OF A RADIAL TURBINE AND RADIAL TURBINE

Номер: US20190316469A1
Автор: RIZZI Dario, Spadacini Claudio
Принадлежит: EXERGY S.P.A.

A method for the assembly of a counter-rotating radial turbine includes: preparing a central case; pre-assembling a first turbine unit and a second turbine unit, each including: a half-case delimiting a housing; a rotating unit with a shaft housed and rotatably supported in the housing and that is free to rotate about an axis of rotation with respect to said housing; a rotor disc joined to and overhanging a distal end of the shaft and having a front bladed face facing the opposite side with respect to the half-case. The method includes coupling the first pre-assembled turbine unit and the second pre-assembled turbine unit to the central case so as to arrange the front bladed face of the first rotor disc in front of the front bladed face of the second rotor disc, wherein, following the coupling process, the first half-case and the second half-case laterally close the central case. 1. A method for the assembly of a counter-rotating radial turbine , comprising: [ 'a first half-case delimiting a first housing; a first rotating unit comprising a first shaft housed and rotatably supported in the first housing and that is free to rotate about a first axis of rotation with respect to said first housing; a first rotor disc joined to and overhanging a distal end of the first shaft and having a front bladed face facing the opposite side with respect to the first half-case; wherein pre-assembling the first turbine unit comprises: preparing the first half-case delimiting the first housing; preparing the first rotating unit comprising a first support sleeve and the first shaft rotatably housed in the first support sleeve; housing the first rotating unit in the first housing and fixing the first support sleeve to the first half-case;', 'pre-assembling a first turbine unit comprising, 'a second half-case delimiting a second housing; a second rotating unit comprising a second shaft housed and rotatably supported in the second housing and that is free to rotate about a second axis of ...

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Номер записи: 74
17-10-2019 дата публикации

TURBINE HOUSING AND TURBO CHARGER PROVIDED WITH SAME

Номер: US20190316516A1
Автор: ARAI Takashi
Принадлежит: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.

Provided is a turbine housing () having: a housing part () that forms a spiral space (S) extending around a rotating shaft (); a heat-shielding core () which is disposed in the spiral space (S) and forms a spiral exhaust gas flow passage (S) in which exhaust gas introduced from an exhaust gas introduction port flows; and a variable nozzle mechanism () that guides the exhaust gas to a turbine wheel, wherein heat-shielding spaces (S S S) are formed between the inner circumferential surface of the housing part () and the outer circumferential surface of the heat-shielding core (), and wherein the heat-shielding core () has a first flange part () and a second flange part () and is fixed between the variable nozzle mechanism () and the housing part () while a first sealing () is interposed between the first flange part () and the variable nozzle mechanism (). 1. A turbine housing connected to a bearing housing rotatably supporting a rotating shaft of a turbine wheel , the turbine housing comprising:a housing part having a first inner circumferential side wall portion, a first outer circumferential side wall portion, and a first bottom surface part and forming a spiral space extending around the rotating shaft;a flow passage part having a second inner circumferential side wall portion, a second outer circumferential side wall portion, and a second bottom surface part, disposed in the spiral space, and forming a spiral exhaust gas flow passage in which exhaust gas introduced from an exhaust gas introduction port flows; anda nozzle part guiding the exhaust gas introduced into the exhaust gas flow passage to the turbine wheel connected to the rotating shaft, whereina heat-shielding space is formed between an inner circumferential surface of the housing part and an outer circumferential surface of the flow passage part,the flow passage part has an inner circumferential side flange part protruding from the second inner circumferential side wall portion to an inner ...

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Номер записи: 75
03-12-2015 дата публикации

Instrumented flow passage of a turbine engine

Номер: US20150345335A1
Автор: Acquaviva Jermone, Corbin Claude Gaston, GIORDAN Jeremy, Kockenpo Florian, Lamarche Nicolas, Seigneuret Nicolas
Принадлежит:

The invention relates to an annular air flow passage () for a turbine engine such as a turbojet or a turboprop, crossed by an instrumented rod () that includes means for measuring characteristics of a flow potentially traveling along the passage, said rod extending between an outer annular wall () and an inner annular wall () of the passage. According to the invention, outer connection means () fasten an outer end () of the instrumented rod to the outer wall in a manner that is rigid in all directions, and inner connection means () fasten an inner end () of the instrumented rod to the inner wall, in a manner that is rigid in the circumferential direction and that has at least one degree of freedom to move in a first direction () extending between the inner and outer walls () of the passage and having at least a radial component. 1. An annular air flow passage for a turbine engine such as a turbojet or a turboprop , the passage being provided with an instrumented rod that crosses it and that includes means for measuring characteristics of a flow potentially traveling along the passage , said rod extending between an outer annular wall and an inner annular wall of the passage , the passage being characterized in that outer connection means fasten an outer end of the instrumented rod to the outer wall in a manner that is rigid in all directions , and inner connection means fasten an inner end of the instrumented rod to the inner wall , in a manner that is rigid in the circumferential direction of the passage and that has at least one degree of freedom to move in a first given direction extending between the inner and outer walls of the passage and having at least a radial component.2. A passage according to claim 1 , wherein the inner connection means fasten the inner end of the instrumented rod to the inner wall with a degree of freedom to move in a second given direction substantially perpendicular to the first given direction.3. A passage according to claim 1 , ...

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Номер записи: 76
24-10-2019 дата публикации

TURBINE AND TURBINE SYSTEM

Номер: US20190323351A1
Автор: MAEDA Hideyuki, TSURUTA Kazutaka
Принадлежит: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION

A turbine which has: a balance piston disposed in a turbine rotor; a plurality of balance piston seals disposed on a casing side in a manner to face the balance piston; a balance piston extraction hole allowing extraction from between the plurality of balance piston seals to a middle stage of the turbine stages; an exhaust connection piping connecting a low pressure side of the balance piston to a turbine exhaust system; a exhaust connection piping valve mechanism which is provided in the exhaust connection piping; a plurality of seal mechanisms provided between the low pressure side of the balance piston and the atmosphere; and an exhaust piping allowing exhaust from between the plurality of seal mechanisms. 1. A turbine comprising:a casing;a turbine rotor disposed to penetrate the casing;a plurality of turbine stages disposed in the casing and provided along a shaft direction of the turbine rotor;a working fluid injection pipe allowing a working medium to be injected into the casing and to be distributed from the front stage toward the rear stage of the turbine stages, thereby rotating the turbine rotor;a balance piston disposed in the turbine rotor;a plurality of balance piston seals disposed in the casing in a manner to face the balance piston;a balance piston extraction hole allowing extraction from between the plurality of balance piston seals to the middle stage of the turbine stages;an exhaust connection piping connecting a low pressure side of the balance piston to a turbine exhaust system;an exhaust connection piping valve mechanism provided in the exhaust connection piping;a plurality of seal mechanisms provided between the low pressure side of the balance piston and the atmosphere; andan exhaust piping allowing exhaust from between the plurality of seal mechanisms.2. The turbine according to claim 1 ,wherein the exhaust connection piping valve mechanism comprises a regulating valve and an opening/closing valve.3. The turbine according to claim 1 , ...

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Номер записи: 77
24-10-2019 дата публикации

GAS TURBINE ENGINE INNER BARREL

Номер: US20190323383A1
Автор: BEWICK Clare L., INGLEY Lucian
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct. 1. A gas turbine engine for an aircraft comprising:an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor;a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core;a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct;an inner cowl which provides an aerodynamic fairing surrounding the engine core, the inner cowl being rearwards of and axially spaced from the inner ring, and including one or more door sections which are openable to enable maintenance access to the engine core; andan inner barrel which surrounds the engine core and bridges the inner ring and the inner cowl, the inner barrel having a circumferentially extending rear edge which provides an engagement formation for engagement with the door sections when they are closed.2. A gas turbine engine according to claim 1 , wherein the inner barrel is formed as a unitary structure ...

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Номер записи: 78
01-12-2016 дата публикации

BEARING STRUCTURE AND TURBOCHARGER

Номер: US20160348719A1
Автор: Daito Yuichi, KANEDA Shinichi, KOJIMA Hideyuki, SUGIURA Tomomi, UNEURA Yutaka
Принадлежит: IHI CORPORATION

A bearing structure includes: an outer circumferential groove formed on an outer circumferential surface of a cylindrical portion of a semi-floating metal bearing, and including two opposed surfaces opposed to each other in an axial direction of a shaft and a bottom surface connected to the two opposed surfaces; a radial hole penetrating a wall portion defining the bearing hole so as to communicate with the bearing hole, and facing the outer circumferential groove of the semi-floating metal bearing; a locking member having a body inserted into the radial hole from the outer side of the shaft, wherein at least part of the body is interposed between the two opposed surfaces and fixed to the outer circumferential groove; and an opposed portion provided in the housing, and opposed to the part of the body of the locking member when the locking member is fixed to the outer circumferential groove. 1. A bearing structure in which a semi-floating metal bearing having a cylindrical portion is housed in a bearing hole formed in a housing , and a shaft is rotatably supported by a bearing surface formed on an inner circumferential surface of the cylindrical portion , the bearing structure comprising:an outer circumferential groove formed on an outer circumferential surface of the cylindrical portion of the semi-floating metal bearing, and including two opposed surfaces opposed to each other in an axial direction of the shaft and a bottom surface connected to the two opposed surfaces;a radial hole penetrating, in a radial direction of the shaft, a wall portion defining the bearing hole of the housing so as to communicate with the bearing hole, and facing the outer circumferential groove of the semi-floating metal bearing housed in the bearing hole;a locking member having a body inserted into the radial hole from an outer side in the radial direction of the shaft, wherein at least part of the body is interposed between the two opposed surfaces and fixed to the outer ...

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Номер записи: 79
30-11-2017 дата публикации

GAS TURBINE FACILITY

Номер: US20170342860A1
Автор: Itoh Masao, Iwai Yasunori, MAEDA Hideyuki, MORISAWA Yuichi, Nakamura Yasuaki
Принадлежит: KABUSHIKI KAISHA TOSHIBA

A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder. 1. A gas turbine facility comprising:a casing;a combustor provided in the casing to combust fuel and oxidant;a cylinder surrounding a periphery of the combustor, the cylinder dividing a space between the casing and the combustor;a turbine rotated by combustion gas exhausted from the combustor;a heat exchanger which cools the combustion gas exhausted from the turbine;a high-temperature combustion gas supple pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the high-temperature combustion gas supple pipe guiding the combustion gas heated in the heat exchanger into the cylinder by penetrating between the casing and the cylinder; anda low-temperature combustion gas supply pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the casing and the cylinder.2. The gas turbine facility according to claim 1 ,wherein the high-temperature combustion gas supple pipe penetrates inside the low-temperature combustion gas supply pipe,wherein the low-temperature combustion gas supply pipe is coupled to the casing, andwherein the combustion gas flowing through the low-temperature combustion gas supply pipe passes between the high-temperature combustion gas supply pipe ...

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Номер записи: 80
30-11-2017 дата публикации

PRESSURE VESSEL AND TURBINE

Номер: US20170342861A1
Автор: HATANO Kohei
Принадлежит:

It is aimed to improve circularity. In a casing, in which a cylindrical shape thereof is divided into two parts in a radial direction thereof and the casing is connected in the cylindrical shape via flanges thereof protruding outward in the radial direction at both divided ends thereof; increased thickness portions that increase radial direction thickness thereof are formed in a portion excluding the divided ends and circular arc center portions farthest from the divided ends, the portion being between the divided ends and the circular arc center portions. 1. A pressure vessel , in which a cylindrical shape thereof is divided into two parts in a radial direction thereof , and the pressure vessel is connected in the cylindrical shape via flanges protruding outward in the radial direction at both divided ends thereof , whereinincreased thickness portions that increase radial direction thickness thereof are formed in a portion excluding the divided ends and circular arc center portions farthest from the divided ends, the portion being between the divided ends and the circular arc center portions.2. The pressure vessel according to claim 1 , wherein the increased thickness portions are provided symmetrically with reference to center positions between the divided ends and the circular arc center portions.3. The pressure vessel according to claim 1 , wherein the increased thickness portions are provided such that thickness of both end portions thereof is gradually increased toward center positions between the divided ends and the circular arc center portions.4. The pressure vessel according to claim 1 , wherein the increased thickness portions are provided continuously along a center axis direction of the cylindrical shape.5. A turbine claim 1 , in which a rotor is rotatably provided inside a casing claim 1 , wherein{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'the pressure vessel according to is applied to the casing.'} The present invention relates to a pressure ...

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Номер записи: 81
07-12-2017 дата публикации

TURBOMACHINE

Номер: US20170350252A1
Автор: Banzhaf Bernd, Eisenmenger Nadja, Rueckert Frank Ulrich, Wengert Andreas
Принадлежит:

The turbomachine comprises a casing (), there being arranged in the casing an impeller () arranged on a driven shaft. The turbomachine has an inflow region () and an outflow region () and, in operation, is flowed through by a working medium. The working medium flows into the inflow region, along a front side () formed on the impeller and subsequently out of the outflow region, there being a pressure drop at the front side between the inflow region and the outflow region. A pressure divider () is arranged on the rear side of the impeller, opposite the front side. 1202623242620212221232322232122923232323219aabab. A turbomachine () with a casing () , wherein an impeller () , which is arranged on an output shaft ( , is arranged in the casing () , wherein the turbomachine () has an inflow region () and an outflow region () and during operation is exposed to a throughflow of working medium , wherein the working medium flows into the inflow region () , along a front side () which is formed on the impeller () and then flows out of the outflow region () , wherein a pressure drop exists on the front side () between the inflow region () and the outflow region () , wherein a pressure divider () is arranged on the a rear side () of the impeller () which is opposite the front side () so that during operation at least a part of the rear side () is loaded with a lower pressure than the pressure of the inflow region () , characterized in that the pressure divider () is constructed as a steam-lubricated seal.22025262524112625239. The turbomachine () as claimed in claim 1 , characterized in that a shaft sealing ring () is arranged on the casing () claim 1 , wherein the shaft sealing ring () interacts with the output shaft () and wherein a pressure chamber () is formed between the casing () claim 1 , the shaft sealing ring () claim 1 , the impeller () and the pressure divider ().3201122. The turbomachine () as claimed in claim 2 , characterized in that the pressure chamber () is ...

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Номер записи: 82
07-11-2019 дата публикации

AXIAL THRUST LOADING MITIGATION IN A TURBOCHARGER

Номер: US20190338787A1
Автор: Curtis Eric Warren, Hanna Dave R., Hu Leon, Sun Harold Huimin, Yi Jianwen James
Принадлежит:

Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load. 19- (canceled)10. A regenerative turbocharger system of an internal combustion engine , comprising:a back-to-back turbo pump with a back of a first impeller facing a back of a second impeller;a hydraulic turbine;a compressor;a turbine; anda common turbine shaft, with the back-to-back turbo pump, the hydraulic turbine, the compressor, and the turbine all mounted on the turbine shaft.11. The regenerative turbocharger system of claim 10 , wherein the back-to-back turbo pump has dual inlets and a single common volute discharge outlet.12. The regenerative turbocharger system of claim 11 , wherein the back-to-back turbo pump compresses hydraulic fluid received from the engine and connects to a high pressure tank to store the compressed hydraulic fluid.13. The regenerative turbine system of claim 10 , wherein the hydraulic turbine is a back-to-back hydraulic turbine.14. The regenerative turbocharger system of claim 13 , wherein the back-to-back hydraulic turbine has a single inlet receiving hydraulic fluid compressed by the back-to-back turbo pump and has dual discharge ports.15. A regenerative turbocharger system of an internal combustion engine claim 13 , comprising:a partial back plate compressor;a back-to-back hydraulic turbine comprising two turbine rotors coupled back-to-back;a turbine; anda common turbine shaft, the back-to-back hydraulic turbine, the partial back plate compressor, and the turbine each mounted on the common turbine shaft.16. The regenerative turbocharger system of claim 15 , ...

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Номер записи: 83
06-12-2018 дата публикации

TURBINE ENGINE WITH UNDULATING PROFILE

Номер: US20180347403A1
Автор: AVANCHA Ravikanth, Beacock Robert J., Dailey Lyle Douglas, Manoharan Mahendran, SESHADRI Ganesh
Принадлежит:

An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile. 1. A turbine engine comprising:an outer casing having a first surface and defining an axial centerline; andan inner casing located within the outer casing and having a second surface spaced from the first surface to define an annular channel between the first and second surfaces, and combustion air flows through the annular channel in a forward to aft direction;wherein one of the first or second surfaces has an undulating profile.2. The turbine engine of wherein both first and second surfaces have the undulating profile.3. The turbine engine of wherein the annular channel has an overall increasing cross-sectional area.4. The turbine engine of wherein the cross-sectional area of the annular channel alternatingly increase/decreases.5. The turbine engine of wherein the undulating profile is defined at least in part by non-uniform slopes at the first and/or second surface.6. The turbine engine of wherein a static pressure within the annular channel increases when the annular channel increases and decreases when the annular channel decreases.7. The turbine engine of wherein the outer casing comprises a plurality of hangers and shroud segments together defining the first surface.8. The turbine engine of wherein the inner casing comprises a plurality of platforms together defining the second surface.9. The turbine engine of further including at least one stage comprising circumferentially arranged vanes and circumferentially arranged blades wherein the vanes and blades extend radially between a tip seal and a rim seal.10. The turbine engine of wherein a static pressure delta is reduced across the ...

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Номер записи: 84
15-12-2016 дата публикации

COMPONENT WHICH CAN BE SUBJECTED TO HOT GAS FOR A GAS TURBINE AND SEALING ARRANGEMENT HAVING SUCH A COMPONENT

Номер: US20160362996A1
Автор: Ahmad Fathi, Müsgen Ralf, Radulovic Radan, Schuler Marco
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A component which can be subjected to hot gas for a gas turbine, the component having at least one wall, which includes a first surface as far as an edge, the first surface for delimiting a hot gas flow path of the gas turbine, and which includes a second surface, which adjoins the edge and is arranged transversely to the first surface. A groove for receiving a sealing element is arranged in the second surface and extends at least partially along the edge at a distance from the edge. The groove includes a groove base lying opposite the groove opening and two mutually facing side walls which adjoin the groove base and extend along the edge. At least one of the side walls has at least one groove-shaped recess. 1. A component which can be subjected to hot gas for a gas turbine , having at least one wall , the component comprising:a first surface as far as an edge, wherein the first surface is adapted for delimiting a hot gas flow path of the gas turbine, anda second surface which adjoins the edge and is arranged transversely with respect to the first surface, wherein a groove for receiving a sealing element is arranged in the second surface and extends at least partially along the edge at a distance from the edge, andwherein the groove comprises a groove base and two mutually facing side walls which adjoin said groove face and extend along the edge, of which side walls one of the two is arranged on the hot gas side and the other is arranged on the cold gas side and each have recesses,wherein at least some of the recesses are combined to form a group, the recesses of which are arranged in such a manner that two of said recesses of said group are arranged in the hot-gas-side side wall and are spaced apart from each other in such a manner that a further recess of said group, which recess is arranged in the cold-gas-side side wall, partially lies opposite each of the two hot-gas-side recesses.2. The component as claimed in claim 1 ,wherein each side wall has a plurality of ...

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Номер записи: 85
20-12-2018 дата публикации

TURBINE COMPONENT AND TURBINE SHROUD ASSEMBLY

Номер: US20180363508A1
Автор: Hafner Matthew Troy, JR. Frederic Woodrow, Roberts, Taxacher Glenn Curtis
Принадлежит:

A turbine component including an outer shroud arranged within a turbine and including opposed extending portions. An inner shroud shields the outer shroud from a gas flowing along a gas path within the turbine during its operation and including opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud. A first pin and second pin have a respective first end and second end. The first arcuate portion having a first engagement region for engaging the first end, and second arcuate portion having a second engagement region for engaging the second end. In response to engagement of the first engagement region and the first end of the first pin, and engagement of the second engagement region and the second end of the second pin, the inner shroud is prevented from twisting relative to the outer shroud. 1. A turbine component comprising:an outer shroud arranged within a turbine and further comprising opposed extending portions;an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud;a first pin having a first end; anda second pin having a second end;wherein the first arcuate portion having a first engagement region for engaging the first end and second arcuate portion having a second engagement region for engaging the second end;wherein in response to engagement of the first engagement region and the first end of the first pin, and engagement of the second engagement region and the second end of the second pin, the inner shroud is prevented from twisting relative to the outer shroud.2. The turbine component of claim 1 , wherein the first engagement region and the second engagement region are aligned.3. The turbine ...

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Номер записи: 86
05-12-2019 дата публикации

Axial Load Management System

Номер: US20190368549A1
Автор: Bugra Han Ertas, Douglas Carl Hofer, Younkoo Jeong
Принадлежит: General Electric Co

An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.

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Номер записи: 87
31-12-2020 дата публикации

CHARGING DEVICE

Номер: US20200408110A1
Автор: Blasch Philipp, Kuhne Oliver, Martens Anatolij
Принадлежит:

The invention relates to a charging device (), in particular an exhaust gas turbocharger (), 1. A charging device , comprising:a bearing housing and a shaft supported therein;an axial bearing disk supporting the shaft in an axial direction;the bearing housing including a receptacle structured and arranged to receive the axial bearing disk;the receptacle including one of (i) a single lug that protrudes radially relative to an axis of the shaft and (ii) a single recess that opens radially relative to the axis of the shaft;the axial bearing disk including the other one of (i) the lug and (ii) the recess;wherein the recess is configured complementary to the lug; andwherein the lug and the recess are structured and arranged such that the axial bearing disk is installable within the receptacle only in a single predefined installation position of the axial bearing disk.2. The charging device according to claim 1 , wherein the recess has an axial thickness and the lug has an axial thickness that are smaller than an axial thickness of the axial bearing disk.3. The charging device according to claim 2 , wherein the axial thickness of the recess and the axial thickness of the lug are equal to half the axial thickness of the axial bearing disk.4. The charging device according to claim 1 , wherein the recess and the lug are symmetrical with respect to a radial direction of the shaft.5. The charging device according to claim 1 , wherein:the recess has an axial thickness identical to an axial thickness of the axial bearing disk;the lug has an axial thickness that is smaller than the axial thickness of the axial bearing disk; andthe recess and the lug are asymmetrical with respect to a radial direction of the shaft.6. The charging device according to claim 1 , wherein:the recess has an axial thickness and the lug has an axial thickness that are identical to an axial thickness of the axial bearing disk; andthe recess and the lug are asymmetrical with respect to a radial direction of ...

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Номер записи: 88
16-06-2005 дата публикации

Steam turbine and method for producing such a steam turbine

Номер: DE10353451A1
Автор: Martin Reigl
Принадлежит: Alstom Technolgoy AG

Bei einer Dampfturbine (40) mit einem um eine Achse (47) drehbaren Rotor (18), der konzentrisch von einem Gehäuse (11) umschlossen ist, werden eine drastische Verkürzung der Anfahrzeiten und deutlich reduzierte Herstellungskosten dadurch erreicht, dass das Gehäuse (11) einen massiven hohlzylindrischen Grundträger (21) und mehrere, den Grundträger (21) konzentrisch umschließende Schalen (21, 12, 22, 13, 23, ..., 17, 27) umfasst, die aus einem gebogenen Blech hergestellt sind und zwischen denen mit Dampf füllbare Zwischenräume (48) vorgesehen sind. In a steam turbine (40) with a about an axis (47) rotatable rotor (18) which is concentrically enclosed by a housing (11), a drastic reduction of the start-up times and significantly reduced production costs are achieved in that the housing (11) a solid hollow cylindrical base support (21) and a plurality of the base support (21) concentrically enclosing shells (21, 12, 22, 13, 23, ..., 17, 27), which are made of a bent sheet metal and between them with Steam-fillable spaces (48) are provided.

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Номер записи: 89
16-05-2004 дата публикации

TURBINE TREE AND PROCEDURE TO REFRIGERATE A TURBINE TREE.

Номер: ES2206713T3
Автор: Armin Drosdziok, Axel Remberg, Ernst-Erich Mihle
Принадлежит: SIEMENS AG

LA INVENCION SE REFIERE A UN EJE DE TURBINA (1) QUE TIENE UNA ZONA DE ENTRADA (3) PARA UN FLUIDO (4A), EN PARTICULAR PARA VAPOR, Y TIENE COMO MINIMO DOS REBAJES (5A, 5B) SITUADOS AXIALMENTE A UNA DISTANCIA DE LA ZONA DE ENTRADA (3) Y SEPARADOS ENTRE SI, Y QUE SE UTILIZAN PARA ALOJAR POR LO MENOS UNO DE LOS ALABES DE LA TURBINA (6A, 6B). EL EJE DE LA TURBINA (1) ESTA DISEÑADO CON UN ESPACIO HUECO (7), ASOCIADO A LA ZONA DE ENTRADA (3) Y CONECTADO A UN CONDUCTO DE ALIMENTACION (8) Y A UN CONDUCTO DE DESCARGA (9) PARA PASO DEL FLUIDO (4B) PARA REFRIGERAR EL EJE DE LA TURBINA (1). LA INVENCION SE REFIERE ADEMAS A UN PROCESO PARA REFRIGERAR UNA ZONA DE ENTRADA (3) DE UN EJE DE TURBINA (1) MONTADO EN UNA TURBINA DE VAPOR. THE INVENTION REFERS TO A TURBINE AXIS (1) THAT HAS AN INPUT ZONE (3) FOR A FLUID (4A), IN PARTICULAR FOR STEAM, AND HAS A MINIMUM TWO SALES (5A, 5B) SITUATED AT A DISTANCE OF THE ENTRY AREA (3) AND SEPARATE BETWEEN YES, AND THAT ARE USED TO STAY AT LEAST ONE OF THE TURBINE WINGS (6A, 6B). THE TURBINE AXIS (1) IS DESIGNED WITH A HOLLOW SPACE (7), ASSOCIATED WITH THE INPUT AREA (3) AND CONNECTED TO A FEEDING CONDUCT (8) AND TO A DOWNLOAD CONDUCT (9) FOR FLUID PASSAGE (9) 4B) TO REFRIGERATE THE TURBINE AXIS (1). THE INVENTION REFERS IN ADDITION TO A PROCESS FOR COOLING AN ENTRY AREA (3) OF A TURBINE AXIS (1) MOUNTED IN A STEAM TURBINE.

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Номер записи: 90
24-11-2022 дата публикации

GAS TURBINE ENGINE WITH FLUID CIRCUIT AND EJECTOR

Номер: US20220372885A1
Автор: Berdowski Tomasz Edward, Czerwinski Maciej, Kulinski Piotr Jerzy, Sharma Ashish, Sobaniec Miroslaw
Принадлежит:

A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit. 1. A gas turbine engine , the engine comprising:a vane assembly comprising a flowpath wall, wherein a fluid circuit is extended through the flowpath wall, and wherein the fluid circuit defines a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit, and wherein the vane assembly comprises an ejector positioned at the fluid circuit, wherein the ejector defines a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit, wherein the ejector comprises a nozzle positioned downstream of the second inlet opening relative to the second flow of fluid into the fluid circuit and configured to urge the first fluid flow through the fluid circuit.2. The gas turbine engine of claim 1 , wherein the second inlet opening is positioned downstream along the fluid circuit of the first inlet opening.3. (canceled)4. The gas turbine engine of claim 1 , wherein the nozzle comprises a converging cross-sectional area relative to the second flow of fluid from the second inlet opening toward an outlet opening of the fluid circuit.5. The gas turbine engine of claim 1 , wherein the fluid circuit forms a converging-diverging nozzle positioned at the fluid circuit downstream of the nozzle.6. The gas turbine engine of claim 1 , wherein the fluid circuit forms a torturous flowpath claim 1 , a grid structure claim 1 , or a ...

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Номер записи: 91
27-10-2012 дата публикации

Turbine nozzle assembly

Номер: RU2465467C2
Автор: Стивен С. БЕРДЖИК, Томас В. КРОЛЛ
Принадлежит: Дженерал Электрик Компани

FIELD: machine building. SUBSTANCE: turbine nozzle assembly includes blade with internal and external side walls, external ring and flow divider with horizontal elongation. Boundary of transition between external ring and external side wall has enveloped/enveloping transition boundary or radial locking mechanism. Boundary of transition between horizontal elongation and internal side wall has radial locking mechanism or enveloped/enveloping transition boundary. Radial locking mechanism includes an enveloped step projecting along the axis out of the side wall and provided with a flange on its radial side in the form of the second enveloped step projecting along the axis to side wall. Enveloped/enveloping transition boundary includes radial enveloping groove on side wall and mating radial enveloped step. Where the enveloped/enveloping transition boundary is located on rear edge of side wall, it is connected by means of a butt weld located throughout the length of enveloped/enveloping transition boundary. Axial length of enveloped/enveloping transition boundary is approximately less than 1/4 of axial length of alignment between side wall and external ring or horizontal elongation. EFFECT: inventions allow reducing the distortion of steam flow trajectory in turbine and simplifying its assembly. 32 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 465 467 (13) C2 (51) МПК F01D 25/24 (2006.01) F01D 3/02 (2006.01) F01D 9/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2007133831/06, 10.09.2007 (24) Дата начала отсчета срока действия патента: 10.09.2007 (72) Автор(ы): БЕРДЖИК Стивен С. (US), КРОЛЛ Томас В. (US) (73) Патентообладатель(и): ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (US) R U Приоритет(ы): (30) Конвенционный приоритет: 11.09.2006 US 11/518,708 (43) Дата публикации заявки: 20.03.2009 Бюл. № 8 2 4 6 5 4 6 7 (45) Опубликовано: 27.10.2012 Бюл. № 30 Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО " ...

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Номер записи: 92
04-09-2013 дата публикации

Systems, Methods, and Apparatus for Controlling Gas Leaking in a Turbine

Номер: EP2211016A3
Автор: Wei-Min Ren
Принадлежит: General Electric Co

Systems, methods and apparatuses for controlling gas leakage or for axial thrust compensation in a turbine are provided. A plurality of seals (214) in series may be provided where each of the plurality of seals (214) may be operable to reduce gas backflow pressure from an inlet (212) of a turbine component (202). Further, one or more channels (216) may be operable to direct at least a portion of the gas backflow from respective points within the plurality of seals (214) to corresponding points within a gas flow path of the turbine. The communication channels are located either in the casing or in the rotor of the turbine.

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Номер записи: 93
05-03-1983 дата публикации

遠心式羽根車装置

Номер: JPS5838302A
Автор: Hisashi Mitani, 三谷　寿
Принадлежит: Shimadzu Corp, Shimazu Seisakusho KK

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

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Номер записи: 94
10-09-2015 дата публикации

Способ эксплуатации ротационной машины

Номер: RU2014106549A
Автор: Михаэль КУРШ, Штефан ЯНССЕН
Принадлежит: СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ

1. Способ эксплуатации ротационной машины с установленным в подшипнике (39) ротором (14), который в момент работы подвержен действию силы тяги, действующей, главным образом, только в аксиальном направлении, и сила тяги воспринимается и отводится первым упорным подшипником (43) подшипника (39) через смазку, причем подшипник (39) содержит второй упорный подшипник (45),отличающийся этапом,на котором второй упорный подшипник (45) при появлении силы тяги по меньшей мере периодически одновременно создает усилие, действующее на первый упорный подшипник (43) в направлении тяги.2. Способ по п. 1,в котором усилие, действующее в направлении основного сдвига, активируют только после аксиальных колебаний ротора (14), или с их появлением.3. Способ по п. 1 или 2,осуществляемый в нестационарных режимах работы и/или в режиме частичной нагрузки на ротационную машину, выполненную в виде турбомашины.4. Способ по п. 1 или 2,осуществляемый турбомашиной, выполненной в виде стационарной газовой турбины (10).5. Способ по п. 3,осуществляемый турбомашиной, выполненной в виде стационарной газовой турбины (10).6. Способ по одному из пп. 1, 2 или 5,осуществляемый до и/или во время аксиального сдвига ротора (14).7. Способ по п. 3,осуществляемый до и/или во время аксиального сдвига ротора (14).8. Способ по п. 4,осуществляемый до и/или во время аксиального сдвига ротора (14).9. Способ по одному из пп. 1, 2, 5, 7 или 8, в котором подшипник выполнен в виде гидравлического осевого подшипника.10. Способ по п. 3, в котором подшипник выполнен в виде гидравлического осевого подшипника.11. Способ по п. 4, в котором подшипник выполнен в виде гидравлического осевого подшипника.12. Способ по п. 6, в котором подши РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 3/04 (13) 2014 106 549 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014106549/06, 23.07.2012 (71) Заявитель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) Приоритет(ы): (30) Конвенционный приоритет: 21 ...

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Номер записи: 95
27-12-2012 дата публикации

Устройство для регулирования суммарной осевой нагрузки и паровой турбины (варианты)

Номер: RU2011125375A
Автор: Бернард Артур Мл. КУТЮР, Бинаяк РОЙ, Кейси Уилльям ДЖОНС, Сяоцин ЧЖЕН
Принадлежит: Дженерал Электрик Компания

1. Устройство для регулирования суммарной осевой нагрузки паровой турбины, содержащей вращающийся вал, содержащееактивное втягиваемое уплотнение (АВУ), предназначенное для уплотнения вращающегося вала смежно со ступенчатым участком на указанном валу в секции турбины,первый канал для протечки, проточно соединяющий первую ступень секции турбины с зоной уплотнительного приспособления перед АВУ и содержащий первый регулирующий клапан и второй регулирующий клапан,второй канал для протечки, проточно соединяющий вторую ступень секции турбины, которая следует за первой ступенью, с зоной уступа, расположенной непосредственно перед указанным ступенчатым участком, и содержащий третий регулирующий клапан,соединительный канал, проточно соединяющий первый канал для протечки, между первым и вторым регулирующими клапанами, со вторым каналом для протечки и содержащий четвертый регулирующий клапан, иконтроллер, выполненный с возможностью активного управления регулирующими клапанами для регулирования суммарной осевой нагрузки путем регулирования осевого давления на указанном ступенчатом участке.2. Устройство по п.1, в котором контроллер дополнительно выполнен с возможностью активного управления регулирующими клапанами для регулирования суммарной осевой нагрузки путем регулирования осевого давления на указанном ступенчатом участке с одновременным обеспечением втягивания АВУ во время по меньшей мере одного из рабочих режимов, режима с экстремальной осевой нагрузкой или жесткого рабочего режима.3. Устройство по п.2, в котором рабочий режим с экстремальной осевой нагрузкой выбран из группы, состоящей из исполь РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2011 125 375 (13) A (51) МПК F01K 7/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (71) Заявитель(и): Дженерал Электрик Компания (US) (21)(22) Заявка: 2011125375/06, 22.06.2011 Приоритет(ы): (30) Конвенционный приоритет: 23.06.2010 US 12/821,386 A 2 0 1 1 1 2 5 3 7 5 R U Ñòð.: 1 ru A (57) Формула ...

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Номер записи: 96
27-12-2012 дата публикации

Устройство для регулирования суммарной осевой нагрузки паровой турбины (варианты) и паровая турбина

Номер: RU2011125374A
Автор: Бернард Артур Мл. КУТЮР, Бинаяк РОЙ, Кейси Уилльям ДЖОНС, Сяоцин ЧЖЕН
Принадлежит: Дженерал Электрик Компани

1. Устройство для регулирования суммарной осевой нагрузки паровой турбины, содержащей вращающийся вал, содержащееактивное втягиваемое уплотнение (АВУ), предназначенное для уплотнения вращающегося вала смежно со ступенчатым участком на указанном валу в секции турбины,первый канал для протечки, проточно соединяющий первую ступень секции турбины с зоной уплотнительного приспособления смежно с АВУ и содержащий первый регулирующий клапан и второй регулирующий клапан,второй канал для протечки, проточно соединяющий вторую ступень секции турбины, давление в которой отличается от давления в первой ступени, с зоной уступа, расположенной непосредственно рядом с указанным ступенчатым участком, и содержащий третий регулирующий клапан,соединительный канал, проточно соединяющий первый канал для протечки, между первым и вторым регулирующими клапанами, со вторым каналом для протечки и содержащий четвертый регулирующий клапан, иконтроллер, выполненный с возможностью активного управления регулирующими клапанами для регулирования суммарной осевой нагрузки путем регулирования осевого давления на указанном ступенчатом участке.2. Устройство по п.1, в котором контроллер дополнительно выполнен с возможностью активного управления регулирующими клапанами для регулирования суммарной осевой нагрузки путем регулирования осевого давления на указанном ступенчатом участке с одновременным обеспечением втягивания АВУ во время по меньшей мере одного из рабочих режимов, режима с экстремальной осевой нагрузкой или жесткого рабочего режима.3. Устройство по п.2, в котором рабочий режим с экстремальной осевой нагрузкой выбран и� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2011 125 374 (13) A (51) МПК F03B 15/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (71) Заявитель(и): Дженерал Электрик Компани (US) (21)(22) Заявка: 2011125374/06, 22.06.2011 Приоритет(ы): (30) Конвенционный приоритет: 23.06.2010 US 12/821,391 A 2 0 1 1 1 2 5 3 7 4 R U Ñòð.: 1 ru A (57) Формула ...

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Номер записи: 97
10-08-2013 дата публикации

Система увеличения жесткости внутреннего корпуса паровой турбины (варианты) и паровая турбина

Номер: RU2012103746A
Автор: Дэниел Росс ПРЕДМОР, ПАРТИДА Эрик Эдуардо ЛОПЕС, Раджендра ГОНУР, Роберт Джеймс Шервуд
Принадлежит: Дженерал Электрик Компани

1. Система (2) увеличения жесткости внутреннего корпуса паровой турбины, содержащая сегмент (4) внутреннего корпуса и элемент (6) жесткости, прикрепленный к наружной поверхности (8) указанного сегмента (4) и проходящий от нее радиально наружу, причем элемент (6) жесткости выполнен с обеспечением опоры для по меньшей мере части сегмента (4) внутреннего корпуса.2. Система (2) по п.1, в которой элемент (6) жесткости проходит в осевом направлении по наружной поверхности (8) сегмента (4) внутреннего корпуса.3. Система (2) по п.1, в которой элемент (6) жесткости проходит по меньшей мере частично кольцеобразно по наружной поверхности (8) сегмента (4) внутреннего корпуса.4. Система (2) по п.1, в которой элемент (6) жесткости имеет проходящую в осевом направлении часть и проходящую по меньшей мере частично кольцеобразно часть (22).5. Система (2) по п.1, в которой сегмент (4) внутреннего корпуса содержит паровпускной патрубок (16).6. Система (2) по п.5, дополнительно содержащая проходящий по меньшей мере частично в радиальном направлении элемент жесткости, расположенный вокруг наружной поверхности паровпускного патрубка.7. Система (2) по п.5, в которой элемент (6) жесткости содержит крепежный элемент (14), выполненный с возможностью размещения в нем обеспечивающего перемещение элемента для перемещения сегмента (4) внутреннего корпуса.8. Система (2) по п.1, в которой элемент (6) жесткости проходит через внутреннюю поверхность (10) сегмента (4) внутреннего корпуса.9. Система (2) увеличения жесткости внутреннего корпуса паровой турбины, содержащая сегмент (4) внутреннего корпуса, имеющий первую половину и вторую половину, и элементы (6) жесткости, расположенные вокруг наружно� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 25/00 (13) 2012 103 746 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2012103746/06, 30.01.2012 (71) Заявитель(и): Дженерал Электрик Компани (US) Приоритет(ы): (30) Конвенционный приоритет: 01.02. ...

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Номер записи: 98
07-09-2015 дата публикации

A rotary machine including a passive axial balancing system

Номер: KR101550748B1
Автор: 로랑 파브리, 파비엥 발, 프랑소와 당귀
Принадлежит: 에스엔이씨엠에이

본 발명은 메인 액체 흐름을 통과시키는 회전기에 관한 것으로서, 상기 회전기는, 상기 회전기의 케이싱에 대하여 회전하도록 장착된 축(20), 및 제1 축선방향 지지력을 상기 축에 가하기에 적합한 능동형 축선방향 균형 시스템을 포함한다. The present invention relates to a rotating machine for passing a main liquid stream comprising a shaft (20) mounted for rotation with respect to the casing of the rotating machine, and an active axial balance System. 본 발명은 메인 액체 흐름으로부터 발생되는 2차 액체 흐름(F2)에 대한 회로와, 제2 축선방향 지지력을 상기 축에 가하기에 적합한 수동형 축선방향 균형 시스템(42)을 포함하되, 상기 수동형 축선방향 균형 시스템에 2차 액체 흐름(F2)에 대한 상기 회로가 제공된다. The invention comprises a circuit for a secondary liquid flow (F2) originating from a main liquid flow and a passive axial balancing system (42) adapted to apply a second axial bearing force to said shaft, said passive axial balance The system is provided with the above circuit for the secondary liquid flow (F2). 회전기, 메인 액체 흐름, 축, 2차 액체 흐름, 회로 Rotor, main liquid flow, shaft, secondary liquid flow, circuit

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Номер записи: 99
27-07-2011 дата публикации

Способ и система для регулирования протечки газа в турбине и турбина

Номер: RU2010101708A
Автор: Вей-Мин РЕН, Вей-Мин РЕН (US)
Принадлежит: Дженерал Электрик Компани, Дженерал Электрик Компани (US)

1. Способ (400) регулирования протечки газа в турбине, включающий: ! использование (405) группы расположенных последовательно уплотнений для уменьшения давления обратного потока газа из входа турбины, ! использование (410) одного или нескольких каналов, которые направляют по меньшей мере часть обратного потока газа от соответствующих точек в пределах указанных уплотнений к соответствующим точкам в пределах газового тракта турбины, и ! направление (415) части обратного потока газа к указанным точкам в пределах газового тракта через указанные один или несколько каналов. ! 2. Способ по п.1, в котором дополнительно уравновешивают общее осевое усилие, создаваемое обратным потоком газа, общим осевым усилием, создаваемым газовым трактом турбины. ! 3. Способ по п.2, в котором при уравновешивании общего осевого усилия, создаваемого обратным потоком газа, общим осевым усилием, создаваемым газовым трактом турбины, регулируют соответствующий радиус, связанный с каждым из указанных уплотнений. ! 4. Способ по п.1, в котором при использовании (410) одного или нескольких каналов используют один или несколько каналов в пределах корпуса турбины. ! 5. Способ по п.1, в котором при использовании (410) одного или нескольких каналов используют один или несколько каналов в пределах ротора турбины. ! 6. Способ по п.1 в котором давление обратного потока газа в одной из указанных соответствующих точек в пределах указанных уплотнений приблизительно равно давлению в газовом тракте в соответствующей точке в пределах газового тракта. ! 7. Способ по п.1, в котором при использовании (405) указанных уплотнений используют примерно от четырех до примерно шести упло� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2010 101 708 (13) A (51) МПК F02C 7/28 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2010101708/06, 21.01.2010 (71) Заявитель(и): Дженерал Электрик Компани (US) Приоритет(ы): (30) Конвенционный приоритет: 22.01.2009 US ...

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Номер записи: 100