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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

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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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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10-01-2017 дата публикации

Устройство охлаждения передней опоры ротора газотурбинного двигателя

Номер: RU0000167640U1

Полезная модель относиться к области двигателестроения и может быть использована в опорах газотурбинных двигателей (ГТД).Техническим результатом, на достижение которого направлена полезная модель, является повышение эффективности охлаждения масла в маслобаке и передней опоры ротора ГТД с помощью рабочего тела газотурбинного двигателя - воздуха и совмещение маслобака с теплообменником. Дополнительной технической задачей является уменьшение массы и габаритов двигателя.Технический результат достигается тем, что в устройстве охлаждения передней опоры ротора газотурбинного двигателя содержащем маслобак, стенки которого образуют проточную часть двигателя, элемент забора воздуха, блок агрегатов маслосистемы, сообщенный с маслобаком с присоединенными к нему трубопроводами подвода и отвода масла, в отличие от известного маслобак, образующий внутреннюю проточную часть двигателя, совмещен с теплообменником и размещен внутри двигателя между коком, который является одним из элементов забора воздуха, и передней опорой ротора компрессора, корпус маслобака снабжен воздушными каналами, соединенными с одной стороны с воздушными каналами в коке, которые открыты со стороны входа в двигатель набегающему потоку воздуха, а с другой стороны с полостью охлаждения наружного кольца подшипника передней опоры, при этом маслобак через блок агрегатов маслосистемы сообщен с внутренней полостью вала ротора компрессора, стенка которого снабжена отверстиями для подвода масла к внутреннему кольцу подшипника передней опоры.Для уменьшения массы и габаритов двигателя блок агрегатов маслосистемы размещен в полости передней опоры РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 167 640 U1 (51) МПК F02C 7/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ТИТУЛЬНЫЙ ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21)(22) Заявка: 2016126629, 01.07.2016 (24) Дата начала отсчета срока действия патента: 01.07.2016 Дата регистрации: (72) Автор(ы): Тишин Алексей Петрович (RU), Мезенцева Наталья Федоровна (RU), ...

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06-04-2018 дата публикации

Опора ротора газотурбинного двигателя

Номер: RU0000178526U1

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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12-04-2021 дата публикации

Устройство аварийной подачи смазки подшипника генератора энергоблока

Номер: RU0000203549U1

Полезная модель относится к электроэнергетической промышленности и может быть использована при конструировании опорных подшипников генераторов на газотурбинной установке с целью повышения их надежности и долговечности.Устройство содержит тавотницу 1, состоящую из двух соединяющихся между собой нагнетательной 7 и всасывающей 8 полостей. Торец 9 тавотницы 1 закреплен на подшипнике 6 и выполнен из материала, обладающего эффектом памяти формы. Нагнетательная полость 7 соединена с удлинительной трубкой и отверстием 2 для ввода консистентной смазки в полость подшипника 6.При перегреве подшипника 6 в материале торца 9 тавотницы 1 происходит обратное мартенситное превращение, он прогибается, удаляясь от подшипника. При этом в нагнетательной полости 7 создается избыточное давление, и консистентная смазка по удлинительной трубке 2 поступает к подшипнику 6 через отверстие 5.При снижении температуры подшипника 6 уменьшается нагрев торца 9, в котором происходит прямое мартенситное превращение. Торец приближается к подшипнику 6, в нагнетательной полости образуется вакуум, и смазка поступает из всасывающий полости 8 в нагнетательную полость 7 тавотницы. В случае повторного нагрева подшипника 6 цикл работы устройства повторяется. 2 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 203 549 U1 (51) МПК F01D 25/18 (2006.01) F16N 7/08 (2006.01) F16N 11/08 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F01D 25/18 (2021.02); F16N 7/08 (2021.02); F16N 11/08 (2021.02) (21)(22) Заявка: 2020125880, 04.08.2020 (24) Дата начала отсчета срока действия патента: 12.04.2021 Приоритет(ы): (22) Дата подачи заявки: 04.08.2020 (56) Список документов, цитированных в отчете о поиске: SU 1620770 A1, 15.01.1991. SU 1366748 A1, 15.01.1988. JP 2007100932 A, 19.04.2007. JP 10132193 A, 22.05.1998. CN 103899741 B, 06.04.2016. (45) Опубликовано: 12.04.2021 Бюл. № 11 2 0 3 5 4 9 R U (54) Устройство аварийной подачи смазки подшипника генератора энергоблока ...

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12-01-2012 дата публикации

Turbine for the expansion of gas/vapour

Номер: US20120009061A1
Автор: Mario Gaia, Roberto Bini
Принадлежит: TURBODEN SPA

The invention regards a turbine for the expansion of gas and vapour that comprises a body or casing with a volute for the transit of the fluid from an input to an output passage through at least a statoric and a rotoric group, a possible front shield that extends radially from said volute towards the axis of the turbine shaft, an external tube member fixed in front of said shield or said volute designed to hold the turbine shaft with the interposition of a supporting unit ( 19 ), where said turbine shaft ( 15 ) has a head ( 15′ ) supporting the rotoric group ( 16, 17 ). The turbine shaft ( 15 ) together with the rotoric group ( 16, 17 ) is movable axially between a work position, in which the head of said shaft is at a distance from an internal end of the external tube member ( 18 ) facing towards the statoric group, and a retracted position, in which the head of the shaft or a part of the rotoric group rests against said internal end of said tube member with the interposition of at least a front seal ( 41 ).

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26-01-2012 дата публикации

Steam turbine and method for adjusting thrust forces thereof

Номер: US20120017592A1
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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01-03-2012 дата публикации

Casing body through which hot gases can flow and comprising an inner heat shield

Номер: US20120047905A1
Принадлежит: Alstom Technology AG

A casing body for a hot gas flow includes an outer casing body having a hot gas side with a precisely prepared locating surface. A pin-type retainer is disposed on the locating surface, and an inner heat shield is disposed at a distance from the hot gas side of the outer casing body and fastened to the retainer.

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15-03-2012 дата публикации

Air-oil heat exchanger

Номер: US20120060466A1
Принадлежит: United Technologies Corp

A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams.

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15-03-2012 дата публикации

Apparatus and method for cooling a combustor cap

Номер: US20120060511A1
Принадлежит: General Electric Co

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

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22-03-2012 дата публикации

Turbine shroud thermal distortion control

Номер: US20120070276A1
Принадлежит: United Technologies Corp

A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.

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12-04-2012 дата публикации

Planetary gear system arrangement with auxiliary oil system

Номер: US20120088624A1
Автор: William G. Sheridan
Принадлежит: Individual

A lubricating system for lubricating components across a rotation gap has an input that provides lubricant to a stationary first bearing. The first bearing has an inner first race in which lubricant flows. A second bearing rotates within the first bearing and has a first opening in registration with the inner first race such that lubricant may flow from the inner first race through the first opening into a first conduit.

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26-04-2012 дата публикации

Seal apparatus

Номер: US20120098211A1
Принадлежит: General Electric Co

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

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03-05-2012 дата публикации

Bearing retention assembly for and method of assembling turbochargers

Номер: US20120107112A1
Автор: Daniel J. Barlog

An assembly for a turbocharger and a method of assembling a turbocharger are disclosed. Such an assembly can include an elongate pin having a tapered part and a protrusion at one end of the pin. The elongate pin is configured to be inserted within a housing opening and a cartridge opening such that the taper of the body portion of the pin mates with the taper of the housing opening. The cartridge opening is configured as to mate with the pin such that the pin substantially restricts the bearing cartridge from surging and rolling but substantially permits all other movements of the bearing cartridge.

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17-05-2012 дата публикации

Anisotropic bearing supports for turbochargers

Номер: US20120121446A1
Принадлежит: Honeywell International Inc

An exemplary anisotropic member supports a semi-floating bearing in a bore and can reduce non-synchronous vibration of the bearing in the bore. An anisotropic member can include an annular body configured to receive a semi-floating bearing and to space the bearing a distance from a bore surface and can be configured to impart anisotropic stiffness and damping terms to the semi-floating bearing when positioned in the bore. Such a member is suitable for use in a rotating assembly for a turbocharger where the bearing may be a semi-floating bearing. Various exemplary members, bearings, housings, assemblies, etc., are disclosed.

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14-06-2012 дата публикации

Gas turbine engine and cooling system

Номер: US20120144843A1

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique cooling system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooling one or more objects of cooling. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

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21-06-2012 дата публикации

Turbojet including an automatically variable flow rate bleed circuit for cooling air

Номер: US20120151936A1
Принадлежит: SNECMA SAS

Bleeding cooling air to cool a subassembly, e.g. such as a turbine, with automatic adjustment of the air flow section as a function of the speed of the engine. According to the invention, a shutter element is fastened to co-operate with a bleed hole, with the material that constitutes either the shutter element or the wall in which the hole is formed being of a type in which it is possible to create eddy currents, and a magnet is mounted to move past said arrangement.

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21-06-2012 дата публикации

Thrust bearing shaft for thrust and journal air bearing cooling in an air machine

Номер: US20120152383A1
Принадлежит: Hamilton Sundstrand Corp

A thrust bearing shaft has a radially enlarged thrust disk to be mounted between two static housing surfaces in an air cycle machine. A first portion of the thrust bearing shaft extends from a first face of the thrust disk. A second portion extends from a second opposed face of the thrust disk. The second portion has sealing ribs and six holes. The sealing ribs are spaced closer to the thrust disk than are the holes. A ratio of a distance from an end of the second portion to a center of the holes compared to a distance from the end of the second portion to the second face of the thrust disk is between 0.20 and 0.22. In addition, an air cycle machine incorporating the thrust bearing shaft, and a method of assembling the thrust bearing shaft into an air cycle machine are disclosed.

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28-06-2012 дата публикации

Gearbox assembly

Номер: US20120159966A1
Принадлежит: United Technologies Corp

An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.

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05-07-2012 дата публикации

Noise attenuation panel and a gas turbine component comprising a noise attenuation panel

Номер: US20120168248A1
Принадлежит: Volvo Aero Corp

A noise attenuation panel includes a first wall, a second wall and partition walls connected to the first and second walls and defining cells between the first and second walls. The first wall is provided with a plurality of through holes. At least two of the cells are interconnected via a communication hole. One of the through holes leads to a first of the at least two interconnected cells and a second of the interconnected cells is configured to prevent any gas flow through the second cell.

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12-07-2012 дата публикации

Runner for circumferential seals

Номер: US20120177486A1
Принадлежит: Individual

A runner assembly for a circumferential seal assembly includes a runner having an inwardly extending runner mounting flange, a flexible mounting structure and a retainer assembly therefore.

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12-07-2012 дата публикации

Gas Turbine Nozzle Arrangement and Gas Turbine

Номер: US20120177489A1
Автор: Stephen Batt
Принадлежит: SIEMENS AG

A sealing element is provided for sealing a leak path between a radial outer platform of a turbine nozzle and a carrier ring for carrying said radial outer platform. The carrier ring has an axially facing carrier ring surface and the radial outer platform has an axially facing platform surface. The carrier ring surface forms a first sealing surface and the platform surface forming a second sealing surface. The first and second sealing surfaces is aligned in a plane with a radial gap between them. The sealing element includes a leaf seal adapted to cover the gap between the first and second sealing surfaces, and an impingement plate for allowing impingement cooling of a radial outer surface of the radial outer platform. The impingement plate is adapted to be fixed to the turbine nozzle. The sealing element may be part of a nozzle arrangement of a gas turbine.

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19-07-2012 дата публикации

Cooled gas turbine engine member

Номер: US20120183386A1
Автор: Mark Owen Caswell

A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.

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02-08-2012 дата публикации

Continuous supply fluid reservoir

Номер: US20120192974A1
Принадлежит: United Technologies Corp

An assembly for holding a fluid includes an auxiliary reservoir inside a main reservoir. The auxiliary reservoir includes an auxiliary reservoir shell with a fill passage at or near its bottom. The auxiliary reservoir shell also has a vent passage at or near its top. The fill passage and the vent passage fluidically connect the auxiliary reservoir to the main reservoir. A fluid inlet is located inside the main reservoir and outside of the auxiliary reservoir. A fluid outlet located inside the auxiliary reservoir between the fill passage and the vent passage.

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02-08-2012 дата публикации

Gas turbine engine

Номер: US20120195737A1
Автор: David Butler
Принадлежит: SIEMENS AG

A gas turbine engine including a segment of an annular guide vane assembly is provided. When the engine is used, the segment directs hot combustion gases onto rotor blades of the engine. The segment includes a platform disposed at a side of the segment radially inward/outward with respect to the axis of rotation of the engine. The platform has a trailing edge portion downstream with respect to the flow of hot combustion gases through the segment, the trailing edge portion includes a rail that extends radially inwardly/outwardly from the trailing edge portion. The engine also includes a support and cooling arrangement for supporting the segment and directing a cooling fluid to cool the segment. The arrangement is located radially inward/outward of the platform, and includes a flange part that extends radially outwardly/inwardly from the arrangement. The arrangement further includes a leaf seal and a retaining pin.

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09-08-2012 дата публикации

Method and apparatus for cooling combustor liner in combustor

Номер: US20120198855A1
Принадлежит: General Electric Co

A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner.

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09-08-2012 дата публикации

Passive cooling system for a turbomachine

Номер: US20120201650A1
Принадлежит: General Electric Co

A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.

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09-08-2012 дата публикации

Core runout ceiling for turbine components

Номер: US20120201662A1
Принадлежит: Individual

A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed.

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30-08-2012 дата публикации

Improved bearing system

Номер: US20120219245A1
Принадлежит: Mckeirnan Jr Robert D

The improved bearing system includes a pair of axially split and generally cylindrical cartridges having respective bearing units configured to be mountable to a common axial shaft. An annular channel is generally formed from one of the cartridges for selectively receiving a preload ring. An annular groove is formed from a portion of the other cartridge and sized to slidably receive the preload ring. A preload element is disposed within the annular groove and axially compressed between a preload surface of the annular groove and the preload ring. The preload element maintains a simultaneous axial preload thrust on the bearing cartridges and respective bearing units in inwardly opposite axial directions.

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04-10-2012 дата публикации

Turbine combustion system cooling scoop

Номер: US20120247112A1
Принадлежит: Siemens Energy Inc

A scoop ( 54 ) over a coolant inlet hole ( 48 ) in an outer wall ( 40 B) of a double-walled tubular structure ( 40 A, 40 B) of a gas turbine engine component ( 26, 28 ). The scoop redirects a coolant flow ( 37 ) into the hole. The leading edge ( 56, 58 ) of the scoop has a central projection ( 56 ) or tongue that overhangs the coolant inlet hole, and a curved undercut ( 58 ) on each side of the tongue between the tongue and a generally C-shaped or generally U-shaped attachment base ( 53 ) of the scoop. A partial scoop ( 62 ) may be cooperatively positioned with the scoop ( 54 ).

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25-10-2012 дата публикации

System and method for removing heat from a turbomachine

Номер: US20120266601A1
Автор: Harold Edward Miller
Принадлежит: General Electric Co

The present invention provides systems and methods of removing heat from internal areas of a turbomachine. Embodiments of the present invention may incorporate a suction device and a control system. Operatively, these elements may collectively discharge remnants of a heated fluid and/or gas from those internal areas.

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25-10-2012 дата публикации

Turbine inlet casing with integral bearing housing

Номер: US20120269612A1
Принадлежит: General Electric Co

The present application provides a compressor inlet casing. The compressor inlet casing may include an inner bellmouth and a bearing housing. The bearing housing may include an integrally cast first half connected to the inner bellmouth and a cavity positioned between the inner bellmouth and the integrally cast first half of the bearing housing.

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06-12-2012 дата публикации

Ultra high pressure turbomachine for waste heat recovery

Номер: US20120306206A1
Принадлежит: R&D Dynamics Corp

A turbine-driven alternator (i.e., a turbomachine) suitable for generating electrical power from process gas waste energy. In particular suitable for very high density process gases such as super critical CO2, R134a, R245fa, etc. The turboalternator comprises two separate machines, specifically, a turbine device and an alternator device operatively connected together by a coupling shaft. The rotating shaft assemblies for each machines on the turbine side and the alternator side are supported by hydrodynamic foil gas bearings. The foil gas bearings use process gas at the turbine side, enabling high-pressure operation (˜3000 psia) and thrust load balancing. At the alternator side, cooling fluid is used in the foil gas bearings, enabling high-speed (˜40,000 rpm), low-windage, oil-free operation with closed-loop shaft cooling.

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20-12-2012 дата публикации

Deaerator and conduit assembly

Номер: US20120318912A1
Принадлежит: Individual

An example deaerator assembly includes a housing having a housing inlet and a housing outlet. A conduit configured to communicate a deaerated coolant is located within the housing. A mixture of coolant and air is deaerated as the mixture is communicated from the housing inlet to the housing outlet within the housing and outside the conduit.

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20-12-2012 дата публикации

Turbocharger, notably for a combustion engine

Номер: US20120321491A1
Принадлежит: SKF AB

The turbocharger comprises a shaft 14 , a housing 12 , a turbine wheel 20 and a compressor wheel 22 mounted onto the shaft, and at least a rolling bearing 18 disposed between the shaft and the housing and comprising an inner ring 26 , an outer ring 28 and at least one row of rolling elements 30 disposed into a rolling space 40 defined between the rings. A damping space 38 is defined between an outer surface 28 a of the outer ring and a bore 16 of the housing inside which a lubricant is located.

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27-12-2012 дата публикации

Systems and methods for cooling high pressure and intermediate pressure sections of a steam turbine

Номер: US20120328409A1
Принадлежит: General Electric Co

The present application provides a section cooling system for a steam turbine to limit a leakage flow therethrough. The section cooling system may include a first pressure flow extraction from a first section to a shaft packing location between the first section and a second section and a rotor aperture extending towards the first section. The first pressure flow extraction diverts the leakage flow from the first section into the rotor aperture so as to limit the leakage flow to the second section.

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03-01-2013 дата публикации

Flowpath insert and assembly

Номер: US20130000769A1
Автор: Darren M. Smith
Принадлежит: United Technologies Corp

A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.

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24-01-2013 дата публикации

Uncoupling system for an aircraft turbojet engine rotary shaft

Номер: US20130022448A1
Принадлежит: SNECMA SAS

A decoupling system for a rotary shaft of an aircraft turbojet, the decoupling system including: a rolling bearing including rolling elements inserted between a first ring fastened to a stationary bearing support and a second ring mounted in a mounting chamber fastened to a rotary shaft; a transmission mechanism transmitting rotary torque from the rotary shaft to the second ring; a mechanism allowing the second ring to move radially relative to the mounting chamber when a static force associated with an unbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of leaktight flexible bags interposed between the second ring and the mounting chamber and each including a heterogeneous structure including a porous capillary solid matrix and an associated liquid relative to which the matrix is lyophobic.

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31-01-2013 дата публикации

Three spool engine bearing configuration

Номер: US20130025257A1
Принадлежит: Individual

A disclosed gas turbine engine includes a core section having a low spool, intermediate spool and a high spool that rotate about a common axis. The intermediate spool is supported at an aft position by an inter-shaft bearing arrangement on the low spool. The low spool is supported for rotation in an aft position by an aft roller bearing supported on a turbine exhaust case of the gas turbine engine. The high spool is supported by a high spool aft roller bearing disposed within a high spool bearing compartment. The high spool bearing compartment is positioned within a radial space between the combustor and the axis.

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31-01-2013 дата публикации

Gear train lubricating device

Номер: US20130025405A1
Принадлежит: Kawasaki Jukogyo KK

A gear train lubricating device configured to supply lubricating oil OL to a gear included in a gear train is provided. The gear train lubricating device includes: a shroud covering, among components constituting the gear, at least teeth of the gear; and a lubricating oil supply port through which the lubricating oil OL is supplied to a meshing position of the gear. The shroud has an outlet port formed therein, through which the supplied lubricating oil OL is discharged. The outlet port is formed in a portion of the shroud that is positioned radially outward from the gear, such that the outlet port is disposed at an angular position that is 90°±15° forward from the meshing position in a rotation direction R 1 of the gear.

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31-01-2013 дата публикации

Strut, a gas turbine engine frame comprising the strut and a gas turbine engine comprising the frame

Номер: US20130028718A1
Принадлежит: Volvo Aero Corp

A strut is provided for being arranged between an annular inner structural casing and an annular outer structural casing in a gas turbine engine frame for carrying loads between the inner and outer structural casing during operation. The strut includes a first tube, which is configured to house a service line or pipe between the inner and outer structural casing. The strut includes a second tube, which is configured to house a fastening element for rigidly connecting the inner and outer structural casing. The first and second tube are arranged in a side-by-side relationship and rigidly attached to each other.

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28-02-2013 дата публикации

Turbocharger

Номер: US20130047605A1
Принадлежит: GM GLOBAL TECHNOLOGY OPERATIONS LLC

A turbocharger for an internal combustion engine, comprising a bearing housing, a rotating shaft coupled to the bearing housing, a compressor wheel mounted at one end of the rotating shaft, a compressor housing accommodating the compressor wheel and provided with an inlet and an outlet for an air stream, a turbine wheel mounted at the opposite end of the rotating shaft, and a turbine housing accommodating the turbine wheel and provided with an inlet and an outlet for an exhaust gas stream, wherein the bearing housing comprises a fastening flange suitable to be fixed to a component of the internal combustion engine, wherein the turbine housing is provided with a connecting pipe for fluidly connecting the turbine housing inlet with an exhaust manifold of the internal combustion engine, and wherein the connecting pipe includes means for compensating axial thermal deformations thereof.

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07-03-2013 дата публикации

Generator and accessory gearbox device with a generator

Номер: US20130057093A1
Принадлежит: Rolls Royce Deutschland Ltd and Co KG

The present invention proposes a generator for arrangement on a shaft of an accessory gearbox of an engine with a stator and with a rotor which can be coupled to a shaft of the accessory gearbox of the engine and which is rotatably mounted relative to the stator, where a stator area receiving the stator can be separated from a rotor area receiving the rotor. The rotor can be supplied with cooling medium in the rotor area. It furthermore proposes an accessory gearbox of an engine with a drive shaft operatively connectable to a main shaft of the engine and with at least one generator arranged on a shaft of the accessory gearbox.

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28-03-2013 дата публикации

Seal plate with cooling passage

Номер: US20130078079A1
Принадлежит: United Technologies Corp

A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.

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28-03-2013 дата публикации

AIR SYSTEM ARCHITECTURE FOR A MID-TURBINE FRAME MODULE

Номер: US20130078080A1
Принадлежит:

A mid-turbine frame is disposed between high and low pressure turbine assemblies. A secondary air system is defined in the mid-turbine frame (MTF) to provide cooling to the turbine section of the engine. The secondary air system may be used to cool and pressurize seals to assist with oil retention in bearing cavities. The temperature gain of the secondary air may be reduced by flowing the secondary air through one or more external lines and then generally radially inwardly through air passages defined in the MTF. 1. A gas turbine engine comprising first and second axially spaced-apart turbine rotor assemblies mounted for rotation on bearings housed in a bearing housing , the bearings having seals to restrict lubricant leakage from the bearing housing , and a mid-turbine frame disposed axially between the first and second rotor assemblies , the mid-turbine frame having structurally interconnected radially outer and inner cases , the bearing housing being mounted to the radially inner case of the mid-turbine frame and being disposed radially inwardly of the mid-turbine frame , said mid-turbine frame having a first air system for pressurizing and cooling the seals of the bearings in the bearing housing , said first air system comprising at least one air inlet defined in the radially outer case of said mid-turbine frame for receiving pressurized cooling air from at least one first external line disposed outside of a core casing of the engine where engine temperatures are lower , and a cooling air passage extending from said air inlet radially inwardly through said mid-turbine frame to said bearing housing.2. The gas turbine engine defined in claim 1 , wherein the first air system further comprises an air cooler for cooling the air prior to directing the same into the bearing housing.3. The gas turbine engine defined in claim 1 , wherein the mid-turbine frame further comprises an inter-turbine duct disposed between the radially outer case and the radially inner case ...

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28-03-2013 дата публикации

Sealing arrangement

Номер: US20130078091A1
Автор: Paul D. REES
Принадлежит: Rolls Royce PLC

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

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11-04-2013 дата публикации

EXTERNALLY THREADED JOURNAL HOUSING

Номер: US20130089407A1
Автор: Ranz Andrew J.
Принадлежит: DRESSER-RAND COMPANY

A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener. 1. A journal housing , comprising:a series of housing threads defined on an outer radial surface, the series of housing threads being adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing; anda shoulder extending radially-outward from the outer radial surface, the shoulder being disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener.2. The journal housing of claim 1 , wherein the series of housing threads comprises buttress threads.3. The journal housing of claim 2 , wherein the buttress threads comprise square buttress threads.4. The journal housing of claim 1 , wherein the series of housing threads comprises external threads and the series of casing threads comprises internal threads.5. The journal housing of claim 1 , wherein the at least one first mechanical fastener prevents the journal housing from threadably disengaging with the casing.6. The journal housing of claim 1 , wherein the casing comprises a compressor head.7. The journal housing of claim 1 , further comprising:an inner journal housing; andan outer journal housing disposed radially-outward from and concentric with the inner journal housing, wherein the outer journal housing defines the series of housing threads.8. The journal housing of claim 7 , wherein the inner journal housing comprises first and second outer surfaces that are radially offset from one another.9. The journal housing of claim 7 , wherein the inner journal housing comprises:a first inner journal housing section; anda ...

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11-04-2013 дата публикации

TURBINE BLADE TIP CLEARANCE CONTROL

Номер: US20130089408A1
Принадлежит: UNITED TECHNOLOGIES CORPORATION

An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising. 1. An aircraft engine for use in a fighter jet , said aircraft engine comprising;a high pressure turbine having a blade,an engine casing disposed about said blade,a shield disposed around said casing adjacent to said blade and creating an area between said shield and said casing,a gate for selectively controlling entry of cooling air into said area wherein said gate may be closed if said engine is maneuvering and wherein said gate may be open if cruising.2. The aircraft engine of wherein gate may be partially open if said engine is being operated in a steady state.3. The aircraft engine of wherein said gate is built into a front of said shield.4. The aircraft engine of wherein said gate comprises an opening and a strap having a slot claim 1 , said strap being movable relative to said opening such that said slot and said opening may be in register with each other.5. The aircraft engine of wherein said opening is disposed in front of said shield.6. The aircraft engine of wherein said opening has a race therein for holding said strap.7. The aircraft engine of wherein said strap moves within said race for moving said slots of said strap into and out of register with said openings.8. The aircraft engine of wherein said shield and said strap form an annulus.9. The aircraft engine of wherein said cooling air is fan air.10. A cooling system for an aircraft engine for use in a fighter jet claim 1 , the aircraft engine having a high pressure turbine having a blade and an engine casing disposed about said blade claim 1 , said cooling system comprising;a shield for disposal ...

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11-04-2013 дата публикации

BEARING ARRANGEMENT FOR A SHAFT OF A TURBOCHARGER

Номер: US20130089418A1
Принадлежит: Continental Automotive GmbH

A bearing arrangement for supporting a shaft in a turbocharger housing. The bearing arrangement includes a sleeve element and the sleeve element is formed with a flange section at each end for fastening the bearing arrangement in the turbocharger housing. 115-. (canceled)16. A bearing arrangement for supporting a shaft in a turbocharger housing , the bearing arrangement comprising:a sleeve element having ends, said sleeve element having a collar section at each end for fastening the bearing arrangement in the turbocharger housing.17. The bearing arrangement according to claim 16 , wherein one or both said collar sections are integrally formed on said sleeve element.18. The bearing arrangement according to claim 17 , wherein one or both said collar sections are flexible or rigid.19. The bearing arrangement according to claim 16 , wherein one or both said collar sections are formed as a separate part.20. The bearing arrangement according to claim 19 , wherein one or both said collar sections are flexible or rigid.21. The bearing arrangement according to claim 16 , wherein said sleeve element is configured for fastening between corresponding receptacles or projections on the turbocharger housing by way of said collar sections.22. The bearing arrangement according to claim 21 , wherein said sleeve element is to be fastened by clamping in or bracing in an axial direction.23. The bearing arrangement according to claim 16 , wherein one or both said collar sections are to be fastened to an associated receptacle or projection of the turbocharger housing.24. The bearing arrangement according to claim 23 , wherein one or both said collar sections are to be fastened to the receptacle or projection by screwing and/or pinning.25. The bearing arrangement according to claim 16 , wherein one end of a collar section claim 16 , in each case formed as a separate part claim 16 , is attached to said sleeve element by at least one of placing against claim 16 , pushing onto claim 16 , ...

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18-04-2013 дата публикации

TURBOMACHINE

Номер: US20130094938A1
Принадлежит: Cummins Turbo Technologies Limited

A turbomachine comprising a housing defining a bearing cavity and a turbine chamber separated by a first wall, a heat shield disposed between the first wall and the turbine wheel, a heat shield cavity defined between the first wall and the heat shield. The shaft extends through a passage defined in part by a first aperture in the wall and a second aperture in the heat shield. A first seal is provided between the shaft and the first aperture. The housing defines a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity. A second channel is provided between the heat shield cavity and the passage, the second channel opening to the passage on the opposite side of the first seal to the bearing assembly. A second seal is provided between the shaft and the second aperture. 1. A turbomachine comprising:a unitary housing defining a bearing cavity, a turbine chamber and an integral heat shield, the bearing cavity and turbine chamber being separated by a first wall;a turbine wheel mounted to a shaft for rotation within said turbine chamber about a machine axis;the heat shield disposed between the first wall and the turbine wheel, a heat shield cavity being defined between the first wall and the heat shield;the shaft extending from the turbine chamber into the bearing cavity through a passage defined at least in part by a first aperture in said first wall and a second aperture in the heat shield, the shaft being mounted for rotation on a bearing assembly provided in the bearing cavity;a first seal between the shaft and said first aperture;the housing defining a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity;a second channel between the heat shield cavity and said passage, the second channel opening to said passage on the opposite side of said first seal to said bearing assembly; anda second ...

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25-04-2013 дата публикации

Split accessory drive system

Номер: US20130098058A1
Автор: William G. Sheridan
Принадлежит: United Technologies Corp

A gas turbine engine includes a spool, a first accessory gearbox, a second accessory gearbox, and a scavenge pump. The first accessory gearbox is connected to and driven by the spool. The second accessory gearbox is connected to and driven by the first accessory gearbox. The scavenge pump is connected between the first accessory gearbox and the second accessory gearbox. The first accessory gearbox drives the second accessory gearbox through the scavenge pump.

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02-05-2013 дата публикации

Gearbox in a turbine engine

Номер: US20130104681A1
Принадлежит: SNECMA SAS

A gearbox in a turbine engine for imparting rotary drive to at least one piece of rotary equipment, the gearbox including a transmission shaft guided in rotation in bearings and carrying a toothed wheel meshing with at least one rotary drive gearwheel. One of the bearings is a rolling bearing mounted inside the toothed wheel in a radial plane containing the toothed wheel and the drive gearwheel, and another of the bearings is a smooth bearing for taking up forces tending to tilt the transmission shaft.

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02-05-2013 дата публикации

EXHAUST-GAS TURBOCHARGER

Номер: US20130108483A1
Принадлежит: BORGWARNER INC.

The present invention relates to an exhaust-gas turbocharger () having a compressor (); having a turbine (); having a bearing housing () which is connected at one end to the compressor () and at the other, turbine-side end () to the turbine () and which has an oil collecting chamber () at the turbine-side end () and which has a plain bearing arrangement () for a rotor shaft (), which plain bearing arrangement comprises a compressor-side bearing () with an inner bearing surface and an outer circumferential surface, and comprises a turbine-side bearing () which is spaced apart axially from the compressor-side bearing () and which has an inner bearing surface () and an outer circumferential surface (), wherein the compressor-side bearing () and the turbine-side bearing () are of different design. 2189810910. The exhaust-gas turbocharger () as claimed in claim 1 , wherein the outer diameter of the rotor shaft () in the region of the compressor-side bearing (′) and/or the outer diameter of the rotor shaft () in the region of the turbine-side bearing ()' is larger than the rotor shaft diameter between the bearings (′ claim 1 , ′).31. The exhaust-gas turbocharger () as claimed in claim 2 , wherein the diameter enlargement is realized by the provision of a slight bevel or by the provision of a shaft shoulder.419910. The exhaust-gas turbocharger () as claimed in claim 1 , wherein the compressor-side bearing (′) has a bearing bush () whose outer diameter is larger or smaller than the outer diameter of the turbine-side bearing bush ().51910. The exhaust-gas turbocharger () as claimed in claim 4 , wherein the inner diameter of the compressor-side bearing bush () is larger or smaller than the inner diameter of the turbine-side bearing bush ().6112131417910. The exhaust-gas turbocharger () as claimed in claim 1 , wherein the inner and/or outer bearing widths ( claim 1 , claim 1 , claim 1 , ) of the bearing bushes ( claim 1 , ) differ.711117910. The exhaust-gas turbocharger () as ...

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09-05-2013 дата публикации

Gearbox deoiler with pre-pressuring component

Номер: US20130112029A1
Принадлежит: Hamilton Sundstrand Corp

A gearbox includes an inlet configured to receive a mixture of air and oil from an external source and a deoiler. The deoiler includes a shaft including an inlet passage and an outlet passage, both formed on an inner portion of the shaft and separated from one another, a separator unit coupled to and surrounding a portion of the shaft and including an inlet and an outlet and a pre-pressuring component coupled to the shaft that increases the pressure of the mixture of oil and air to form a pressurized mixture and provides the pressurized mixture to the inlet of the separator unit.

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16-05-2013 дата публикации

Drive of a tail rotor of a helicopter

Номер: US20130121831A1
Принадлежит: SIEMENS AG

The invention relates to a drive ( 1 ) of a tail rotor ( 12 ) of a helicopter ( 10 ) by a permanently excited transversal flux machine in duplex arrangement in such a way that between two stators ( 4 ), which each have a toroidal winding system ( 8 ), there is arranged a disc-shaped impeller ( 5 ), which has permanent magnets ( 15 ) and on the outer circumference of which propeller blades ( 14 ) of the tail rotor ( 12 ) are arranged.

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23-05-2013 дата публикации

BEARING DEVICE AND TURBOMACHINE HAVING A BEARING DEVICE

Номер: US20130129504A1
Автор: HELDNER Sebastian
Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

A bearing device with an arrangement of at least two bearings is provided. A filling made of an amorphous/solid active medium as a mechanism of compensating for axial loads is arranged between a bearing race of at least one of the bearings and a surrounding component of the bearing arrangement. 1. A bearing device comprising:an arrangement of at least two bearings, each having a bearing race;a filling made of an amorphous/solid active medium as a mechanism of compensating for axial loads, the filling operatively arranged between the bearing race of at least one of the bearings and an adjacent component of the bearing arrangement.2. The bearing device in accordance with claim 1 , wherein the filling includes a plurality of balls.3. The bearing device in accordance with claim 1 , wherein the plurality of balls are a same size.4. The bearing device in accordance with claim 1 , wherein the bearing race of at least one of the at least two bearings is an outer race and the adjacent component of the bearing arrangement is a casing.5. The bearing device in accordance with claim 1 , wherein the bearing race of at least one of the at least two bearings is an inner race and the adjacent component is a part of a shaft connected to the inner race.6. The bearing device in accordance with claim 1 , wherein the bearing races claim 1 , each have a defined pressure surface in operative connection with the filling for exerting an axial pressure force on the filling.7. The bearing device in accordance with claim 6 , wherein the bearing races are outer races.8. The bearing device in accordance with claim 6 , wherein the defined pressure surface of a first of the bearing races claim 6 , and the defined pressure surface of a second of the bearing races claim 6 , have different sizes.9. The bearing device in accordance with claim 8 , wherein the first and second of the bearing races are outer races.10. The bearing device in accordance with claim 1 , wherein at least a part of the amorphous ...

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23-05-2013 дата публикации

BEARING DEVICE AND TURBOMACHINE HAVING A BEARING DEVICE

Номер: US20130129505A1
Автор: HELDNER Sebastian
Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

A bearing device, for example in a turbomachine is provided. Between bearing races of the anti-friction bearings and a casing component positioned adjacent the bearing races is arranged a device for converting an axial force between the anti-friction bearings into a torque at the bearing races in the manner of a ball screw or planetary screw assembly. The bearing races are connected to one another by a feedback mechanism such that a torque at one bearing race can be converted into an opposite torque at the other bearing race. 1. A bearing device , comprising:a two-row arrangement of anti-friction bearings, each having a bearing race,a casing component positioned adjacent the bearing races; a screw mechanism connecting the casing component to the bearing races;', 'a feedback mechanism connecting the bearing races to one another such that a torque at one bearing race can be converted into an opposite torque at an other bearing race., 'a converting device for converting an axial force between the anti-friction bearings into a torque at the bearing races, the converting device operatively positioned between the bearing races and the casing component and including2. The bearing device in accordance with claim 1 , wherein the screw mechanism includes a ball screw assembly having first grooves with a type of thread pitch in the bearing races and a second groove with a type of thread pitch in the casing component claim 1 , with compensating rolling elements being arranged in the grooves.3. The bearing device in accordance with claim 1 , wherein the feedback mechanism includes a compensating rocker claim 1 , where a torque of the one bearing race can be converted using the compensating rocker into a leverage to apply an opposite torque at the other bearing race.4. The bearing device in accordance with claim 3 , wherein the compensating rocker includes a beam-like element which engages a counter bearing on the casing component acting as a pivot point for the leverage effect ...

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23-05-2013 дата публикации

EXHAUST GAS TURBOCHARGER WITH PLAIN BEARING FOR REDUCING FLUID TURBULENCE

Номер: US20130129506A1
Принадлежит: Bosch Mahle Turbo Systems GmbH & Co. KG

An exhaust-gas turbocharger may include a rotor shaft arranged with at least one bearing-shaft portion in a radial bearing. The radial bearing may be a plain bearing configured to slide on a fluid film. The at least one bearing-shaft portion may be subdivided into two outer segments by an inner segment. The two outer segments may be arranged on the respective axial end region of the radial bearing and the inner segment may be positioned between the outer segments. The inner segment may be arranged in the area of an opening of a fluid channel. The turbocharger may include at least one transverse groove running inclined relative to the circumferential direction of the rotor shaft arranged in at least in one of the outer segments. The at least one transverse groove may include a groove depth having a continuously decreasing development in a fluid flow direction. 1. An exhaust-gas turbocharger comprising: a rotor shaft being arranged with at least one bearing-shaft portion in a radical bearing , the radial bearing being a plain bearing being rotationally moveable and configured to slide on a fluid film , whereinthe at least one bearing-shaft portion is subdivided into two outer segments by an inner segment, the two outer segments arranged on the respective axial end region of the radial bearing and the inner segment positioned between the outer segments,further wherein the inner segment is arranged in the area of an opening of a fluid channel of the radial bearing, andat least one transverse groove running inclined relative to the circumferential direction of the rotor shaft arranged in at least in one of the outer segments, wherein the at least one transverse groove includes a groove depth including a continuously decreasing development in a fluid flow direction.2. The exhaust-gas turbocharger according to claim 1 , wherein the at least one transverse groove runs along a direction of rotation of the rotor shaft from the respective outer segment to the inner segment and ...

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30-05-2013 дата публикации

EXHAUST-GAS TURBOCHARGER

Номер: US20130136579A1
Автор: Högg Andreas, Koch Silvio
Принадлежит: BORGWARNER INC.

An exhaust-gas turbocharger (), having a shaft () on which are arranged a compressor wheel () and a turbine wheel (), a bearing housing () in which are arranged a compressor-side bearing arrangement () and a turbine-side bearing arrangement () for the shaft (), an oil inflow line () and an oil outflow line (), and an additional oil accumulator () for the bearing arrangements () of the shaft (). The oil accumulator () is a pressure accumulator arranged in a branch line () of the oil inflow line (), and a controllable valve () is arranged between the oil accumulator () and the opening-in point () of the branch line () into the oil inflow line (). 11. An exhaust-gas turbocharger () , having{'b': 2', '3', '4, 'a shaft () on which are arranged a compressor wheel () and a turbine wheel (),'}{'b': 5', '6', '7', '2, 'a bearing housing () in which are arranged a compressor-side bearing arrangement () and a turbine-side bearing arrangement () for the shaft (),'}{'b': 8', '9, 'an oil inflow line () for supplying oil to the bearing arrangements and an oil outflow line (), and'}{'b': 10', '6', '7', '2, 'an additional oil accumulator () for the bearing arrangements (, ) of the shaft (),'}{'b': 10', '11', '8, 'wherein the oil accumulator () is a pressure accumulator arranged in a branch line () of the oil inflow line (), and'}{'b': 13', '10', '12', '11', '8, 'wherein a controllable valve () is arranged between the oil accumulator () and an opening-in point () of the branch line () into the oil inflow line ().'}21413810. The exhaust-gas turbocharger as claimed in claim 1 , including a control device () for opening and closing the controllable valve () as a function of received pressure signals (DS) from the inflow line () and the oil accumulator ().31581211. The exhaust-gas turbocharger as claimed in claim 1 , wherein a check valve () is arranged in the oil inflow line () upstream of the opening-in point () of the branch line ().481211. The exhaust-gas turbocharger as claimed in ...

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30-05-2013 дата публикации

AEROFOIL COOLING ARRANGEMENT

Номер: US20130136599A1
Автор: HARDING Adrian Lewis
Принадлежит: ROLLS-ROYCE PLC

An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall and a suction wall, at least one of the pressure and suction walls comprise corrugations and a coolant hole on an inner surface, the corrugations define a downstream surface and the coolant hole having an inlet defined in the downstream surface. 1. An aerofoil for a gas turbine engine ,the aerofoil comprises a pressure wall and a suction wall,at least one of the pressure and suction walls comprise corrugations and a coolant hole on an inner surface,the corrugations define a downstream surface with respect to a coolant flow and the coolant hole having an inlet defined in the downstream surface.2. The aerofoil of wherein the corrugations define an upstream surface.3. The aerofoil of wherein the wall defines a passage therein and the coolant hole connects between the inlet and the passage.4. The aerofoil of wherein the coolant flows through the aerofoil and the downstream surface is angled between 20° and 90° relative to the direction of coolant flow.5. The aerofoil of wherein the coolant flows through the aerofoil and the downstream surface is angled α is approximately 45° relative to the direction of coolant flow.6. The aerofoil of wherein the coolant flows through the aerofoil and the upstream surface is angled θ between 20° and 70° relative to the direction of coolant flow.7. The aerofoil of wherein the coolant flows through the aerofoil and the upstream surface is angled θ is approximately 45° relative to the direction of coolant flow.8. The aerofoil of wherein the corrugations define any one or more the sectional profiles generally sinusoidal claim 1 , rounded triangular claim 1 , trapezoidal or saw-toothed.9. The aerofoil of wherein the corrugations define a peak and a cross-section of the passage has an apex which is adjacent the peak.10. The aerofoil of wherein the corrugations define an amplitude or height of the corrugations approximately 0.7 mm.11. The aerofoil of ...

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06-06-2013 дата публикации

BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER

Номер: US20130142465A1
Принадлежит: BORGWARNER INC.

A bearing housing () of an exhaust-gas turbocharger, having a compressor-side housing flange (), a central housing section () which is integrally connected to the housing flange () and in which is arranged a first partial section () of an oil chamber () which has an oil inlet () and an oil outlet (), and a turbine-side housing section () which has a turbine-side housing flange () and in which is arranged a second partial section () of the oil chamber (). The central and turbine-side housing sections () are provided with an oil cooling duct (). 11. A bearing housing () of an exhaust-gas turbocharger , including{'b': '2', 'a compressor-side housing flange (),'}{'b': 3', '2', '4', '5', '20', '21, 'a central housing section () which is integrally connected to the housing flange () and in which is arranged a first partial section () of an oil chamber () which has an oil inlet () and an oil outlet (), and'}{'b': 6', '7', '8', '5, 'a turbine-side housing section () which has a turbine-side housing flange () and in which is arranged a second partial section () of the oil chamber (),'}{'b': 3', '6', '13', '13, 'wherein the central and turbine-side housing sections (, ) are provided with an oil cooling duct (; ′).'}2113105. The bearing housing () as claimed in claim 1 , wherein the oil cooling duct () is connected via an overflow () to the oil chamber ().31131313131021. The bearing housing () as claimed in claim 2 , wherein the oil cooling duct () has three duct sections (A claim 2 , B claim 2 , C) which run in a meandering fashion from the overflow () to the oil outlet ().41132021. The bearing housing () as claimed in claim 1 , wherein the oil cooling duct (′) branches off from the oil inlet () and opens out into the oil outlet ().5113. The bearing housing () as claimed in claim 1 , wherein the oil cooling duct (′) is arranged annularly around the oil chamber.6113131313. The bearing housing () as claimed in claim 1 , wherein the throughflow rate in the oil cooling duct ( ...

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06-06-2013 дата публикации

STEAM TURBINE ARRANGEMENT OF A THREE CASING SUPERCRITICAL STEAM TURBINE

Номер: US20130142618A1
Принадлежит:

A steam turbine arrangement is provided and includes a first steam turbine with a first steam outlet, wherein the first steam turbine exhibiting a first sealing leakage, a second steam turbine exhibiting a second sealing leakage, and a third steam turbine with a cooling steam inlet, a functional device and a cooling arrangement. The cooling arrangement is coupled to the cooling steam inlet. The cooling arrangement is adapted for guiding a cooling steam to the functional device for cooling purposes. A steam pipe is coupled to the first steam turbine and to the second steam turbine such that a first steam being provided by the first sealing leakage and a second steam being provided by the second sealing leakage is gathered to a cooling steam in the steam pipe. The steam pipe is coupled to the cooling steam inlet such that the cooling steam is injectable to the cooling arrangement. 1. A steam turbine arrangement , comprisinga first steam turbine with a first steam outlet, the first steam turbine exhibiting a first sealing leakage;a second steam turbine exhibiting a second sealing leakage;a third steam turbine with a cooling steam inlet, a functional device and a cooling arrangement;a steam pipe, coupled to the first steam turbine and to the second steam turbine such that a first steam provided by the first sealing leakage and a second steam provided by the second sealing leakage is gathered to a cooling steam in the steam pipe; andan extraction control valve,wherein the cooling arrangement is coupled to the cooling steam inlet,wherein the cooling arrangement is adapted for guiding a cooling steam to the functional device for cooling purposes,wherein the steam pipe is coupled to the cooling steam inlet such that the cooling steam is injectable to the cooling arrangement, andwherein the extraction control valve which is coupled between the first steam outlet of the first steam turbine and the steam pipe such that an extraction of a first control steam from the first ...

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06-06-2013 дата публикации

EXHAUST GAS HOUSING FOR A GAS TURBINE AND GAS TURBINE HAVING AN EXHAUST GAS HOUSING

Номер: US20130142631A1
Принадлежит: ALSTOM Technology Ltd

An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts. 1: An exhaust gas housing for a gas turbine , the exhaust gas housing comprising:an annular gas passage, configured to discharge an exhaust gas from the gas turbine to the outside, wherein the annular gas passage is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance,wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and include in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the annular gas passage,wherein the radial struts include a third heat-resistant lining, the outer casing includes a first heat-resistant lining, and the inner casing include a second heat-resistant lining, in each case towards the annular gas passage,wherein the third heat-resistant lining of the struts is at least partially mechanically decoupled from (i) the first heat-resistant lining, (ii) the second heat-resistant lining, or (iii) the first heat-resistant lining and the second heat-resistant lining for reducing thermal stress on a ...

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06-06-2013 дата публикации

BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER

Номер: US20130142647A1
Принадлежит: BORGWARNER INC.

A bearing housing () of an exhaust-gas turbocharger, having a compressor-side housing flange (), a central housing section () which is integrally connected to the housing flange () and in which a first partial section () of an oil chamber () is arranged; and a turbine-side housing section () which has a turbine-side housing flange () and in which a second partial section () of the oil chamber () is formed. The central housing section () and the turbine-side housing section () are formed in one piece. A bearing housing () which forms a separate component is inserted into the central housing section () and into the turbine-side housing section (), with these delimiting the oil chamber (). 11. A bearing housing () of an exhaust-gas turbocharger , with{'b': '2', 'a compressor-side housing flange (),'}{'b': 3', '2', '4', '5, 'a central housing section () which is integrally connected to the housing flange () and in which a first partial section () of an oil chamber () is arranged; and'}{'b': 6', '7', '8', '5, 'claim-text': [{'b': 3', '6, 'the central housing section () and the turbine-side housing section () are formed in one piece, and'}, {'b': 9', '3', '6', '5, 'a bearing housing () as a separate component is inserted into the central housing section () and into the turbine-side housing section () and, with these, delimits the oil chamber ().'}], 'a turbine-side housing section () which has a turbine-side housing flange () and in which a second partial section () of the oil chamber () is formed, wherein'}2110569. The bearing housing () as claimed in claim 1 , further comprising a water chamber () which is separate from the oil chamber () and which is delimited by the turbine-side housing section () and the bearing sleeve ().3191112. The bearing housing () as claimed in claim 1 , wherein the bearing sleeve () is provided with oil inflow ducts ( claim 1 , ).41936. The bearing housing () as claimed in claim 1 , wherein the bearing sleeve () is divided into two sleeve ...

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06-06-2013 дата публикации

TURBINE BLADE AND GAS TURBINE HAVING THE SAME

Номер: US20130142667A1
Автор: Ito Ryuta
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A turbine blade of the present invention includes a blade body mounted on a rotor body so as to extend outward from the rotor body in a radial direction of the rotor body and a chip shroud fixed to the outside of the blade body in the radial direction. A cooling passage which extends in the radial direction of the rotor body and in which a cooling medium circulates is formed in the blade body. The chip shroud includes a shroud body where a recess opened to the outside in the radial direction and communicating with the cooling passage is formed on an outer peripheral end face, and a plug that includes a plurality of plug pieces closing an opening of the recess in cooperation with each other by being inserted into mounting grooves formed on side surfaces of the recess. 1. A turbine blade comprising:a blade body that is mounted on a rotor body so as to extend outward from the rotor body in a radial direction of the rotor body; anda chip shroud that is fixed to the outside of the blade body in the radial direction,wherein a cooling passage which extends in the radial direction of the rotor body and in which a cooling medium circulates is formed in the blade body, andthe chip shroud includes a shroud body where a recess opened to the outside in the radial direction and communicating with the cooling passage is formed on an outer peripheral end face, and a plug that includes a plurality of plug pieces closing an opening of the recess in cooperation with each other by being inserted into mounting grooves formed on side surfaces of the recess.2. The turbine blade according to claim 1 ,wherein the recess extends in a direction along the outer peripheral end face as a longitudinal direction thereof,the mounting grooves are formed on the pair of side surfaces along the longitudinal direction, andthe plurality of plug pieces close the opening of the recess by lining up in the longitudinal direction so as to come into contact with each other.3. The turbine blade according to ...

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06-06-2013 дата публикации

Cooled turbine blade for gas turbine engine

Номер: US20130142668A1
Принадлежит: SNECMA SAS

A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall.

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13-06-2013 дата публикации

GAS TURBINE OUTER CASE ACTIVE AMBIENT COOLING INCLUDING AIR EXHAUST INTO A SUB-AMBIENT REGION OF EXHAUST FLOW

Номер: US20130149107A1
Принадлежит:

A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end. 1. A gas turbine engine comprising:an outer case defining a central longitudinal axis, and an outer surface of said outer case extending circumferentially around the central longitudinal axis;a cooling channel associated with said outer surface of said outer case, said cooling channel having a channel inlet and a channel outlet;an air duct including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of said gas turbine engine; andan exit structure at said air duct outlet end, said exit structure providing a sub-ambient pressure at said air duct outlet end to induce a flow from said air duct inlet end to said air duct outlet end.2. The gas turbine engine of claim 1 , wherein said exit structure interacts with a portion of said exhaust gas flow passing over said exit structure for effecting a reduced pressure at said outlet end to draw air from said cooling channel into said air duct.3. The gas turbine engine of claim 2 , wherein said exit structure partially covers said air duct outlet end claim 2 , shielding an upstream side of said outlet end and defining a downstream facing opening adjacent a downstream side of said outlet end.4. The gas turbine engine of claim 1 , wherein said exit structure produces a jet ...

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13-06-2013 дата публикации

Bearing arrangement

Номер: US20130149141A1
Принадлежит: Rolls Royce PLC

A bearing arrangement 2 comprising an outer race 10 , a shaft 4 arranged to rotate with respect to the outer race 10 thereby defining an axis of rotation 8 of the shaft 4 . The shaft 4 and the outer race 10 are arranged to define a region of overlap between the shaft 4 and the outer race 10 along the axis of rotation. An inner race 12 is disposed between the outer race 10 and the shaft 4 in the region of overlap and coupled for rotation with the shaft 4 , the inner race 12 and the shaft 4 defining an annular reservoir 40 between them for accommodating radial expansion of the shaft 4 or radial displacement of the shaft 4 with respect to the axis of rotation 8.

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13-06-2013 дата публикации

COMPONENT HAVING COOLING CHANNEL WITH HOURGLASS CROSS SECTION

Номер: US20130149169A1
Принадлежит:

A cooling channel (B, -) cools inner surfaces () of exterior walls () of a component (). Interior side surfaces () of the channel converge to a waist (W), forming an hourglass shaped transverse profile (). The inner surfaces () may have fins () aligned with the coolant flow (). The fins may have a transverse profile (A, B) highest at mid-width of the inner surfaces (). Turbulators () may be provided on the side surfaces () of the channel, and may urge the coolant flow toward the inner surfaces (). Each turbulator () may have a peak () that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (). 1. A component comprising an interior cooling channel , the cooling channel further comprising:first and second inner surfaces of respective first and second exterior walls of the component; andfirst and second side surfaces spanning between the inner surfaces,wherein a transverse section of the channel has an hourglass-shaped profile in which the side surfaces taper toward each other to a waist that is narrower than a width of each of the first and second inner surfaces; andwherein an overall direction of a coolant flow in the channel is normal to the hourglass-shaped profile.2. The component of claim 1 , wherein the first and second inner surfaces are parallel to respective first and second portions of exterior surfaces of the respective exterior walls.3. The component of claim 1 , wherein the first and second exterior walls are respectively pressure and suction sides of a turbine airfoil.4. The component of claim 1 , wherein the waist comprises a width of 80% or less than the width of at least one of the inner surfaces.5. The component of claim 1 , wherein the each of the side surfaces has a taper angle in the profile of at least −1 degrees toward the waist relative to a straight line between ...

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20-06-2013 дата публикации

System and method for warming up a steam turbine

Номер: US20130152587A1
Принадлежит: General Electric Co

A system for warming up a steam turbine includes a gas turbine and a controller operably connected to the gas turbine. The controller is programmed to receive a plurality of measured input signals and control the gas turbine to produce an exhaust having a desired energy. A first measured input signal is reflective of a measured operating parameter of the gas turbine and a second measured input signal is reflective of an operating parameter of the steam turbine. A method for warming up a steam turbine includes sending a plurality of measured input signals to a controller, wherein a first measured input signal reflects a measured operating parameter of a gas turbine and a second measured input signal reflects an operating parameter of the steam turbine. The method further includes controlling the gas turbine based on the plurality of measured input signals and producing an exhaust from the gas turbine, wherein the exhaust has a desired energy.

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20-06-2013 дата публикации

FAN

Номер: US20130156573A1
Автор: KAJI Yasuyuki
Принадлежит: NIDEC CORPORATION

A fan includes a stationary portion, a rotating portion, and a plurality of blades. The stationary portion includes a stator, an integral one-piece molded metal bearing housing, a bearing portion in the bearing housing, and a molded resin base portion supporting the bearing housing. The rotating portion includes a rotor holder, a rotor magnet, and a shaft. The bearing housing includes a cylindrical portion, and a protruding portion extending radially outwards from a lower portion of the cylindrical portion. The cylindrical portion includes a groove portion extending in an axial direction and arranged in a circumferential direction. The groove portion is joined to a region on the lower side of the protruding portion along a connecting position between the cylindrical and protruding portions. A resin on an upper side of the protruding portion, a resin on a lower side, and a resin in the groove portion are continuous. 1. A fan comprising:a stationary portion;a rotating portion rotatably supported by the stationary portion; anda plurality of blades arranged on an outer circumference of the rotating portion to generate a flow of air by rotation of the rotating portion; wherein a stator;', 'a bearing housing arranged on an inside of the stator, and defined by a molded metal integral one-piece member;', 'a bearing portion arranged in the bearing housing; and', 'abase portion made of molded resin and arranged to support the bearing housing;, 'the stationary portion includes a rotor holder having a cylindrical or substantially cylindrical shape with a cover;', 'a rotor magnet arranged on a radially outer side of the stator and on an inner side of an inner circumferential surface of the rotor holder; and', 'a shaft connected to the cover of the rotor holder and inserted into the bearing portion;, 'the rotating portion includes a cylindrical portion; and', 'a protruding portion expanding radially outwards from a lower portion of the cylindrical portion;, 'the bearing housing ...

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20-06-2013 дата публикации

ROLLING BEARING FOR AIRCRAFT TURBOJET FITTED WITH IMPROVED MEANS OF AXIAL RETENTION OF ITS OUTER RING

Номер: US20130156574A1
Принадлежит: SNECMA

A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring. 17-. (canceled)8. A structure for an aircraft turbojet comprising:a rolling bearing including an outer ring;a bearing bracket surrounding the outer ring;a retaining ring interposed between the outer bearing ring and the bearing bracket; an attaching flange installed on the bearing bracket; and', 'flexible means for connection attached to the outer bearing ring and to the attaching flange;, 'means for connecting the outer ring to the bearing bracket, wherein the means for connecting includesmeant for allowing axial retention of the outer bearing ring, if the flexible connection means fracture,wherein the means enabling axial retention of the outer ring includes:first stop means securely attached to the retaining ring, and capable of axially retaining the retaining ring relative to the bearing bracket in event that the flexible connection means fracture; andsecond stop means securely attached to the retaining ring, and capable of axially retaining the outer ring relative to the retaining ring, in the event that the flexible connection means fracture,wherein the second stop means includes multiple slugs spaced circumferentially relative to one another, wherein each slug is held in a slug insertion opening made in the ...

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20-06-2013 дата публикации

AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING

Номер: US20130156579A1
Принадлежит:

A gas turbine engine including: an ambient-air cooling circuit () having a cooling channel () disposed in a turbine blade () and in fluid communication with a source () of ambient air: and an pre-swirler (), the pre-swirler having: an inner shroud (); an outer shroud (); and a plurality of guide vanes (), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes () define respective nozzles () there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls () of the pre-swirler may be contoured. 1. A gas turbine engine , comprising:an ambient-air cooling circuit comprising a cooling channel disposed in a turbine blade and in fluid communication with a source of ambient air that provides cooling fluid: and an inner shroud;', 'an outer shroud; and', 'a plurality of guide vanes, each spanning from the inner shroud to the outer shroud,', 'wherein circumferentially adjacent guide vanes define respective nozzles there between, the nozzles defining a portion of the cooling circuit, each nozzle defined by a pressure side of a first guide vane, a suction side of the adjacent guide vane, an outer end wall defined by the outer shroud, and an inner end wall defined by the inner shroud;, 'a pre-swirler, comprisingwherein forces created by a rotation of the turbine blade motivate the cooling fluid through the cooling circuit; andwherein the pre-swirler is configured to impart swirl to the cooling fluid drawn through the nozzles and to direct the swirled cooling fluid toward a base of the turbine blade.2. The gas turbine engine of claim 1 , wherein the inner shroud is formed as a monolithic body.3. The gas turbine engine of claim 1 , wherein the outer shroud is formed as a monolithic body.4. The gas turbine engine of ...

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20-06-2013 дата публикации

BLADE FOR A TURBO MACHINE

Номер: US20130156598A1
Автор: Davis Anthony
Принадлежит:

A blade for a turbomachine, for example a gas turbine, is provided. The blade is arranged on a turbine rotor of the gas turbine. The blade includes a root portion having two narrow sides and two broad sides, a cooling air supply passage in the root portion, and a cooling air bleed which is arranged in the root portion and is in fluid connection with the cooling air supply passage. The cooling air bleed includes a nozzle on one of the narrow sides of the root portion, wherein the nozzle is formed by a hole and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade. 113-. (canceled)14. Blade for a turbomachine , comprising:a root portion with two narrow sides and two broad sides;a cooling air supply passage in the root portion; anda cooling air bleed arranged in the root portion and in fluid connection with the cooling air supply passage;wherein the cooling air bleed comprises a nozzle on one of the narrow sides of the root portion, and wherein the nozzle is formed by a hole,wherein the blade further comprises an upper blade platform and a lower blade platform,wherein the upper blade platform and the lower blade platform are embodied as parts of a labyrinth-sealing when assembled in the turbomachine, andwherein the nozzle is arranged between the upper blade platform and the lower blade platform, andwherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.15. The blade according to claim 14 , wherein the hole of the nozzle is machined into the root portion.16. The blade according to claim 14 , wherein the nozzle is arranged on a front surface of the blade.17. The blade according to claim 14 , wherein the nozzle is arranged for generating an air flow which is directed towards a platform region of an adjacent nozzle guide vane when assembled in the turbomachine.18. The blade according to claim 17 , wherein the air flow ...

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20-06-2013 дата публикации

TURBINE BLADE FOR A GAS TURBINE

Номер: US20130156599A1
Автор: Ahmad Fathi
Принадлежит:

A turbine blade for a gas turbine is provided. The quantity of coolant flowing off the rear edge thereof is set relatively simply and exactly directly upon casting the turbine blade, without reworking the cast turbine blade with respect to the setting of coolant consumption being necessary. Raised areas are situated on the inner surfaces of the intake side wall or pressure side wall, between which a throttle element is present, by means of which the quantity of coolant flowing out is set. This arrangement allows a core tool to be produced simply, by means of which the casting cores required for casting the turbine blade are produced having the desired precision in great quantities. 16-. (canceled)7. A turbine blade for a gas turbine , comprising:a main blade part, around which a hot gas flows and which comprises a suction-side wall and a pressure-side wall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge,wherein an opening for blowing out a coolant which cools the main blade part beforehand is arranged on the trailing edge, which opening is fluidically connected to a cavity arranged in the main blade part by means of a channel,wherein the channel is also delimited by an inwardly facing face of the suction-side wall and by an inwardly facing face of the pressure-side wall and a throttling element is provided for setting the quantity of coolant emerging from the opening,wherein the throttling element comprises two elevations, upstream in relation to the throughflow direction of the channel, of the opening, which are arranged offset in relation to one another, as seen in the throughflow direction of the cooling channel, and between which there is arranged the minimum throughflow cross section of the channel, andwherein the two throttling elements are each arranged each on one of the two inwardly facing faces.8. The turbine blade as claimed in claim 7 , wherein a first elevation which is arranged on the inwardly facing ...

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20-06-2013 дата публикации

AEROFOIL BLADE OR VANE

Номер: US20130156603A1
Принадлежит: ROLLS-ROYCE PLC

An aerofoil blade or vane for the turbine of a gas turbine engine is provided. The blade or vane includes an aerofoil portion which, in use, extends radially across a working gas annulus of the engine. A coolant inlet is formed at an end of the aerofoil portion for the entry of a cooling air flow into the portion. A corresponding coolant exhaust is formed at the trailing edge of the aerofoil portion for spent cooling air to flow from the portion. A passage within the aerofoil portion connects the inlet to the exhaust. A fence within the aerofoil portion extends radially and forwardly from a start position at the end of the aerofoil portion adjacent the trailing edge to an end position. The passage forms a loop which extends along one side of the fence, wraps around the end position, and extends along the other side of the fence. 1. An aerofoil blade or vane for the turbine of a gas turbine engine , the blade or vane including:an aerofoil portion which, in use, extends radially across a working gas annulus of the engine, a coolant inlet being formed at an end of the aerofoil portion for entry of a flow of cooling air into the aerofoil portion, a corresponding coolant exhaust being formed at the trailing edge of the aerofoil portion for the flow of spent cooling air from the aerofoil portion, and a passage within the aerofoil portion connecting the inlet to the exhaust, anda fence within the aerofoil portion, the fence extending radially and forwardly from a start position at said end of the aerofoil portion adjacent the trailing edge to an end position;wherein the passage forms a loop which extends along one side of the fence, wraps around the end position, and extends along the other side of the fence to connect the inlet to the exhaust.2. An aerofoil blade or vane according to which has a plurality of coolant inlets formed at the end of the aerofoil portion for entry of respective flows of cooling air into the aerofoil portion claim 1 , a plurality of corresponding ...

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27-06-2013 дата публикации

Connecting module between a drive shaft of an engine fan and a rolling-element bearing

Номер: US20130163911A1
Принадлежит: SNECMA SAS

A connecting module interposed between a drive shaft of an aircraft engine fan and a rolling-element bearing, wherein the module includes an inner structure attached to the shaft and including a bonnet, and an outer structure attached to the bearing, which is radially supported on a mechanism installed on the inner structure and delimiting a raceway which is complementary to the bonnet so as to form a ball-joint connection kept in a blocked state by a blocking device installed on the inner structure and protruding radially from the bonnet, wherein a mechanism forming a mechanical fuse provides a junction between the device and the bonnet, such that the ball-joint connection is released following fracture of this mechanism forming a mechanical fuse. The radial support mechanism is added to the device.

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04-07-2013 дата публикации

Methods and systems for cooling a transition nozzle

Номер: US20130167543A1
Принадлежит: Individual

A transition nozzle for use with a turbine assembly is provided. The transition nozzle includes a liner defining a combustion chamber therein, a wrapper circumscribing the liner such that a cooling duct is defined between the wrapper and the liner, a cooling fluid inlet configured to supply a cooling fluid to the cooling duct, and a plurality of ribs coupled between the liner and the wrapper such that a plurality of cooling channels are defined in the cooling duct.

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04-07-2013 дата публикации

Vehicular power transmitting system

Номер: US20130170953A1

A vehicular power transmitting system including an oil pump constructed to sufficiently reduce a required drive torque. A high-pressure-port discharge amount of first and second high-pressure passages of the oil pump is determined such that an amount of consumption of working oil of relatively high pressure can be afforded only by the high-pressure-port discharge amount, during steady-state running of a vehicle in which engine speed is not lower than a predetermined threshold value corresponding to a predetermined lowest target input shaft speed of a continuously variable transmission for its shifting control. The pressure of the working oil discharged from first and second low-pressure discharge passages is kept at a predetermined low level, and the required drive torque of the oil pump is sufficiently reduced.

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04-07-2013 дата публикации

LOW EMISSION DRY GAS SEAL SYSTEM FOR COMPRESSORS

Номер: US20130170961A1
Принадлежит:

Systems and methods according to these exemplary embodiments provide sealing mechanisms for centrifugal compressors. A sealing mechanism includes first, second and third dry gas seals arranged in series. Each seal receives its own sealing gas and has its own venting mechanism. Sealing gas pressures remain low enough that a dedicated compressor for supplying the sealing gases is not needed. Additionally, the risk of process gas being released into the atmosphere in case of seal failure is limited. 1. A turbo machine comprising:a rotor assembly including at least one impeller;a bearing connected to, and for rotatably supporting, the rotor assembly;a stator; anda sealing mechanism disposed between the rotor assembly and the bearing, said sealing mechanism including:a first dry gas seal, disposed proximate an inboard side of said sealing mechanism, and having a primary seal gas supplied thereto at a first pressure;a second dry gas seal, disposed adjacent to said first dry gas seal and having a primary buffer gas supplied thereto at a second pressure; anda third dry gas seal, disposed adjacent to said second dry gas seal and having a buffer gas supplied thereto at a third pressure.2. The turbo machine of claim 1 , wherein said primary seal gas is a process gas which is being pressurized by said turbo machine claim 1 , said primary buffer gas is fuel gas claim 1 , and said buffer gas is nitrogen.3. The turbo machine of claim 1 , further comprising:a first venting mechanism which is configured to vent primary seal gas which is recovered downstream of said first dry gas seal to a recovery system within said turbo machine;a second venting mechanism which is configured to vent primary buffer gas and buffer gas which is recovered downstream of said second dry gas seal to a flare associated with said turbo machine; anda third venting mechanism which is configured to vent buffer gas which is recovered downstream of said third dry gas seal into the atmosphere.412345671243657. The ...

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04-07-2013 дата публикации

Turbine assembly and method for reducing fluid flow between turbine components

Номер: US20130170983A1
Принадлежит: General Electric Co

According to one aspect of the invention, a turbine assembly includes a stator and a rotor adjacent to the stator. The turbine assembly also includes a passage formed in a projection from the rotor to form a fluid curtain between the rotor and stator, wherein the fluid curtain reduces a flow of fluid into a hot gas path.

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11-07-2013 дата публикации

Method for cooling a thermal protection floor of an aft aerodynamic fairing of a structure for mounting an aircraft propulsion system

Номер: US20130174572A1
Принадлежит: AIRBUS OPERATIONS SAS

A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle.

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11-07-2013 дата публикации

TURBINE ENGINE SHAFT

Номер: US20130177390A1
Автор: COT Serge, Lalanne Clement
Принадлежит: MICROTURBO

A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet. 1. A turbine engine shaft comprising at least:a cavity axially subdivided into first and second chambers for feeding lubricating fluid at least to a first bearing and to a second bearing that is axially offset relative to the first bearing; and an axial duct with an open first end at a lubricating fluid inlet and a second end that is closed in the axial direction;', 'at least one first radial orifice connecting the second end of the axial duct to the first chamber in order to feed the first bearing with lubricating fluid; and', 'at least one second radial orifice connecting the second end of the axial duct to the second chamber in order to feed the second bearing with lubricating fluid, the at least one first radial orifice and the at least one second radial orifice of the distributor member being at substantially equal axial distances from the lubricating fluid inlet., 'a distributor member comprising at least2. A turbine engine shaft according to claim 1 , wherein the second end of the axial duct is connected to the first chamber by a plurality of radial orifices.3. A turbine engine shaft according to claim 1 , wherein the second end of the axial duct is connected to the second chamber by a plurality of radial orifices.4 ...

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11-07-2013 дата публикации

SYSTEM FOR PRESSURING THE BEARING CHAMBERS OF TURBINE ENGINES MACHINES USING AIR TAKEN FROM THE INTAKE DUCT

Номер: US20130177398A1
Принадлежит: SNECMA

A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor. 111-. (canceled)12. A system for pressurizing at least one chamber for lubricating bearings of a turbomachine , comprising:a circuit for supplying the chamber with pressurized air; anda circuit for recovering oil mist formed in the chamber and for returning the recovered mist to an oil reservoir of the turbomachine,wherein the supply circuit supplies the chamber with air bled from upstream of a low-pressure compressor.13. The pressurizing system as claimed in claim 12 , wherein the supply circuit is supplied both with air bled from upstream of the low-pressure compressor and with air bled from downstream of a compressor stage that is air being returned to a pressure of the air bled from upstream of the compressor by being passed through a labyrinth14. The pressurizing system as claimed in claim 12 , wherein the recovery circuit comprises claim 12 , downstream of the chamber claim 12 , means for suction of the mist.15. The pressurizing system as claimed in claim 14 , wherein the suction means is arranged downstream of an oil separator for separating the air and oil forming the mist claim 14 , such that a suction acts on oil-free air.16. The pressurizing system as claimed in claim 15 , wherein the suction means is fitted to the oil reservoir.17. The pressurizing system as claimed in claim 14 , wherein the suction means comprises a jet pump.18. The pressurizing system as claimed in claim 17 , wherein the jet pump is supplied with air bled from a stage of a compressor.19. The pressurizing system as claimed in claim 17 , wherein the circuit for supplying air to the jet pump comprises a valve ...

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11-07-2013 дата публикации

GAS TURBINE ENGINE BEARING CHAMBER SEALS

Номер: US20130177406A1
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine sealing air system including a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air. The system includes an air vent duct coupled to the bearing chamber seal. An ejector is located within the air vent duct to pump sealing air from the bearing chamber seal and through the air vent duct. A first duct is coupled between a starter air system of the gas turbine engine and the ejector to provide motive fluid to the ejector during gas turbine engine starting. 1. A gas turbine engine sealing air system comprising:a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air;an air vent duct coupled to the bearing chamber seal;a starter air system of the gas turbine engine;an ejector located within the air vent duct to pump sealing air from the bearing chamber seal and through the air vent duct; anda first duct coupled between the starter air system and the ejector to provide motive fluid to the ejector during gas turbine engine starting.2. A sealing air system as claimed in further comprising a second air source and a second duct coupled between the second air source and the ejector to provide the motive fluid during other periods of gas turbine engine operation.3. A sealing air system as claimed in wherein the second air source comprises a compressor bleed of the gas turbine engine and the second duct comprises a bleed duct.4. A sealing air system as claimed in wherein the ejector is configured as a restriction of the air vent duct.5. A sealing air system as claimed in further comprising a restriction of the air vent duct.6. A sealing air system as claimed in further comprising an air/oil separator located in the air vent duct.7. A sealing air system as claimed in wherein the air/oil separator is located between the bearing chamber seal and the ejector.8. A sealing air system as claimed in further comprising a switching ...

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11-07-2013 дата публикации

Coupling system for a star gear train in a gas turbine engine

Номер: US20130178327A1
Принадлежит: United Technologies Corp

A star gear train for use in a gas turbine engine includes a sun gear, a ring gear, a plurality of star gears and a coupling system. The sun gear is rotatable by a shaft. The ring gear is secured to a ring gear shaft. Each of the plurality of star gears is rotatably mounted in a star carrier and meshes with the sun gear and the ring gear. The coupling system comprises a sun gear flexible coupling, a carrier flexible coupling and a deflection limiter. The sun gear flexible coupling connects the sun gear to the shaft. The carrier flexible coupling connects the carrier to a non-rotating mechanical ground. The deflection limiter is connected to the star carrier to limit excessive radial and circumferential displacement of the star gear train.

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18-07-2013 дата публикации

ARRANGEMENT FOR THE GUIDING OF THE FLOW OF A LIQUID IN RELATION TO THE ROTOR OF A TURBOMACHINE

Номер: US20130183142A1
Принадлежит: SNECMA

An arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine, which includes an intermediary disc and a downstream disc of which the internal diameter and the axial position of the discs are defined in such a way that the tank is arranged inside the discs. The rotor supports a guide flange with an element of revolution of which the diameter of the section increases in the downstream direction, according to the direction of flow of the gases in the turbomachine. The downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and the upstream axial end of the flange is connected to the internal radial end of the intermediate disc. 1. An arrangement for guiding a flow of liquid , wherein said liquids from a tank of liquid mounted on a stator of a turbomachine , in relation to a rotor of the turbomachine , to a space separating a downstream end of the rotor from the stator ,wherein the rotor comprises an intermediary disc and a downstream disc, located downstream of the intermediate disc, adjacent of revolution of which an external radial end edge of each disc carries vanes, of which an internal diameter and an axial position of the discs are defined in such a way that the tank is arranged inside said intermediary and downstream discs,and wherein a guide flange for the liquid is arranged between the tank and the discs,wherein the flange comprises an element of revolution supported by the rotor, of which a diameter of a section increases in a downstream direction, according to a direction of flow of gases in the turbomachine, and wherein said flange extends axially at least starting from the intermediate disc to the downstream disc.2. The arrangement as claimed in claim 1 , wherein the downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and an upstream axial end of the flange is connected to an internal radial end of the ...

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18-07-2013 дата публикации

BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER

Номер: US20130183144A1
Принадлежит: BORGWARNER INC.

A bearing housing () of an exhaust-gas turbocharger, having a housing body () in which an axial bearing () is arranged, and a compressor-side housing cover () which can be fixed in a compressor-side housing opening () by means of a fastening device (). The fastening device () is a non-positively locking fastening device. 11. A bearing housing () of an exhaust-gas turbocharger , having{'b': 2', '3, 'a housing body () in which an axial bearing () is arranged, and'}{'b': 4', '6', '5', '5, 'a compressor-side housing cover () which can be fixed in a compressor-side housing opening () by means of a fastening device (), wherein the fastening device () is a non-positively locking fastening device.'}246. The bearing housing as claimed in claim 1 , wherein the outer diameter (□) of the housing cover () is larger than the inner diameter (□) of the housing opening ().341263. The bearing housing as claimed in claim 1 , wherein the housing cover () bears against the abutment surface () claim 1 , which faces toward the housing opening () claim 1 , of the axial bearing ().44131416. The bearing housing as claimed in claim 3 , wherein the housing cover () has a retaining ring () and a concentric inner shaft passage ring () claim 3 , which rings are connected to one another via an end wall ().513141617. The bearing housing as claimed in claim 4 , wherein the retaining ring () claim 4 , the shaft passage ring () and the end wall () delimit an oil free space ().613. The bearing housing as claimed in or claim 4 , wherein the retaining ring () is provided with a friction-increasing structure on the outside.74. The bearing housing as claimed in claim 1 , wherein the housing cover () is a sheet-metal part.81824. The bearing housing as claimed in claim 1 , wherein a sealing element () is provided between the bearing housing body () and the housing cover ().924. The bearing housing as claimed in claim 1 , wherein a positively locking fastening device is additionally provided between the ...

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01-08-2013 дата публикации

Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine

Номер: US20130192251A1
Принадлежит: United Technologies Corp

A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.

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01-08-2013 дата публикации

WAVE-DRIVEN BLOWER AND ELECTRIC MOTOR/GENERATOR

Номер: US20130195616A1
Автор: Epstein Richard
Принадлежит:

The present invention provides a wave-driven blower and a wave-driven generator. Embodiments can accelerate fluid flows with waves requiring with no or minimal moving parts. The waves driving the flow can be surface-thermal waves on the walls of the device. The velocity of the surface-thermal wave entrains the fluid near the surface and imparts a velocity to the fluid. Other types of waves can generate fluid flow. These other waves can be produced by variations in chemical composition, ionic concentration, chemical potential, total pressure, partial pressure and surface texture. Operating as a generator, the device extracts energy from a flowing fluid to amplify wave motions. The wave motions in turn generate electrical power or some other form of useable power 1. An apparatus for affecting fluid flow , comprising: (a) a first surface comprising a plurality of regions , each region characterized by a controllable property; (b) a control system configured to control the regions of the first surface such that the controllable properties change in a manner such that the regions in the first surface exert a force along the first surface on a fluid proximal the first surface.2. An apparatus as in claim 1 , wherein the control system is configured to change the controllable properties such that the controllable properties establish a wave moving along the first surface.3. An apparatus as in claim 1 , wherein the controllable property comprises the temperature of the region.4. An apparatus as in claim 1 , wherein the controllable property comprises the surface texture of the region.5. An apparatus as in claim 1 , wherein the controllable property comprises permeability of the region to fluid pressure.6. An apparatus as in claim 1 , wherein the controllable property comprises heat transfer between the region and fluid proximal the region.7. An apparatus as in claim 6 , wherein the controllable property comprises one or more of: ohmic heating of the region claim 6 , ...

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01-08-2013 дата публикации

Geared turbofan engine with counter-rotating shafts

Номер: US20130195624A1
Принадлежит: United Technologies Corp

A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. A plurality of vanes redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine.

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01-08-2013 дата публикации

SPIRAL-GROOVED THRUST BEARING

Номер: US20130195631A1
Автор: Omori Naomichi
Принадлежит:

A thrust-bearing () disposed to face a thrust collar provided on a rotary shaft, including: grooves () formed at a bearing-surface (b); a first-groove-group (A) constituted by a plurality of first-spiral-grooves () formed at an inner circumferential side of the bearing-surface (b); a second-groove-group (A) constituted by a plurality of second-spiral-grooves () formed at an outer circumferential side more than the first-groove-group (A) and wound in the same direction as the first-spiral-groove (); and an annular-land-section () formed at the side, to which a fluid is drawn, among the inner circumferential more than the first-groove-group (A) and the outer circumferential more than the second-groove-group (A), wherein some of the first-spiral-grooves () of the first-groove-group (A) and some of the second-spiral-grooves () of the second-groove-group (A) are in communication with each other via a partial-communication-section (), at least one side of which is in partial communication with the other side. 1. A thrust bearing disposed to oppose a thrust collar installed at a rotary shaft , comprising:a groove section formed at a bearing surface disposed to oppose the thrust collar;a first groove group constituted by a plurality of first spiral grooves formed at an inner circumferential side of the bearing surface;a second groove group formed at an outer circumferential side of the bearing surface more than the first groove group and constituted by a plurality of second spiral grooves wound in the same direction as the first spiral grooves, and the groove section having the first groove group and the second group; andan annular land section formed at a side to which a fluid is drawn, among the inner circumferential side more than the first groove group and the outer circumferential side more than the second groove group,wherein some of the first spiral grooves of the first groove group and some of the second spiral grooves of the second groove group are in communication ...

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08-08-2013 дата публикации

Gas turbine engine thermal management system

Номер: US20130202406A1
Принадлежит: United Technologies Corp

A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

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08-08-2013 дата публикации

TURBINE VANE HOLLOW INNER RAIL

Номер: US20130202409A1
Автор: Jones Richard, Pacey Andy
Принадлежит:

A guide vane device for a turbine has an inner platform with a through hole forming a fluid channel for a cooling fluid, wherein the inner platform extends in a circumferential direction around a shaft of the turbine. The guide vane device further includes a hollow aerofoil with a cooling opening for exchanging the cooling fluid passing the through hole into or from the hollow aerofoil, wherein the hollow aerofoil is fixed to a first surface of the inner platform, and a rail with a recess with a cooling fluid passage forming a passage for the cooling fluid to the through hole, wherein the rail is fixed to a second surface of the inner platform and the rail extends along the second surface in the circumferential direction around the shaft. The cooling fluid passage has in the circumferential direction at least the dimension of the through hole. 18.-. (canceled)9. Guide vane device for a turbine , the guide vane device comprising:an inner platform with a through hole forming a fluid channel for a cooling fluid, wherein the inner platform extends in a circumferential direction around a shaft of the turbine,a hollow aerofoil with a cooling opening for exchanging the cooling fluid passing the through hole into or from the hollow aerofoil, wherein the hollow aerofoil is fixed to a first surface of the inner platform, anda rail comprising a recess with a cooling fluid passage forming a passage for the cooling fluid to the through hole, wherein the rail is fixed to a second surface of the inner platform and the rail extends along the second surface in the circumferential direction around the shaft,wherein the cooling fluid passage comprises in the circumferential direction at least the dimension of the through hole.10. The guide vane device of claim 9 , wherein the recess is larger than the through hole.11. The guide vane device of claim 9 , wherein the rail is integrally formed with the inner platform.12. The guide vane device of claim 9 , wherein the hollow aerofoil is ...

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08-08-2013 дата публикации

ROLLING ELEMENT BEARING CARTRIDGE WITH AXIAL THRUST DAMPING AND ANTI-ROTATION ASSEMBLIES

Номер: US20130202432A1
Принадлежит: BORGWARNER INC.

To solve both axial and rotational constraint problems in turbochargers with rolling element bearings (REBs), a REB sleeve or outer race is mounted to the bearing housing in a way that is not axially and radially rigid, thus allowing for oil damping films both radially and axially. At the same time, the REB sleeve or outer race is held so that the REB sleeve or outer race does not rotate relative to the bearing housing. This dual purpose is achieved using an anti-rotation ring and a damping ring. The anti-rotation ring includes at least one anti-rotation feature for engaging the bearing housing and at least one anti-rotation feature for engaging the REB cartridge, preventing rotation of the REB cartridge sleeve or outer race. The damping ring axially locates the REB cartridge and dampens axial movement and cushions axial thrust. 1. A turbocharger including:a shaft having a rotation axis, a compressor end and a turbine end;{'b': '3', 'a bearing housing () including a bearing bore and having a compressor side and a turbine side;'}{'b': 65', '64', '64, 'a rolling element bearing (REB) cartridge supported in said bearing bore, the REB cartridge comprising at least one inner race (), at least one outer race (), and a series of rolling elements, each rolling element in contact with a track in an inner race and a track in an outer race, and optionally an outer sleeve in frictional contact with the at least one outer race ();'}{'b': 121', '123', '124, 'an anti-rotation ring () having an outer surface () and a generally cylindrical inner surface, the inner surface having one or more sections () deviating from a circle with constant radius about the shaft axis,'}wherein the REB outer race or sleeve has a compressor end and a turbine end, and having on the outer circumference of at least one end at least one non-round circumferentially outer surface section adapted for engaging the non-round section of the anti-rotation ring and securing the REB outer race or sleeve against ...

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15-08-2013 дата публикации

Nozzle guide vane with cooled platform for a gas turbine

Номер: US20130209231A1
Принадлежит: SIEMENS AG

A platform for supporting a nozzle guide vane for a gas turbine is provided. The platform has a gas passage surface arranged to be in contact with a streaming operation gas, and a cooling channel for guiding a cooling fluid within the cooling channel formed in an inside of the platform. A cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface. The platform is an integrally formed part representing a segment in a circumferential direction of the gas turbine. The cooling channel has a first cooling channel portion and a second cooling channel portion arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas. The first cooling channel portion and the second cooling channel portion are interconnected.

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15-08-2013 дата публикации

Set of rotor disks for a turbine engine

Номер: US20130209238A1
Принадлежит: SNECMA SAS

A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk.

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15-08-2013 дата публикации

Cooling device for electric motor

Номер: US20130209239A1
Принадлежит: BAE Systems Hagglunds AB

The invention relates to a device for cooling of electric motor ( 10 ), which electric motor comprises a stator ( 30 ) with a jacket surface/stator back ( 35 ), wherein a housing ( 40 ) is arranged to surround the stator ( 30 ), the device comprising at least one cooling channel ( 50 ) in which a liquid cooling medium is intended to stream for cooling of the electric motor ( 10 ), wherein the housing ( 40 ) is arranged to run separated from the stator ( 30 ) along a main part of the thermoset cased jacket surface ( 35 ) of the stator ( 30 ) for forming of said cooling channel ( 50 ) between the housing ( 40 ) and said jacket surface ( 50 ), wherein the stator winding ( 32 ) of the stator is arranged to run along and axially project from and turn outside of said jacket surface ( 35 ), wherein the stator ( 30 ) including the projecting stator winding ( 32 ) is embedded with said thermoset (E), wherein said cooling channel ( 50 ) also is formed between the housing ( 40 ) and the thus projecting stator winding ( 32 ). The invention also relates to an electric motor with a device for cooling, and a vehicle comprising an electric motor.

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22-08-2013 дата публикации

Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals

Номер: US20130213057A1
Принадлежит: UNITED TECHNOLOGIES CORPORATION

Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal segment for a set of rotatable blades includes: a blade arrival end; and a blade departure end; each of the blade arrival end and the blade departure end being angularly offset with respect to a longitudinal axis about which the blades rotate. 1. A blade outer air seal assembly for a gas turbine engine , the engine having a longitudinal axis and rotatable blades , each of the blades having a blade tip , the blade outer air seal assembly comprising:an annular arrangement of outer air seal segments, each of the segments having ends, the segments being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being angularly offset with respect to a longitudinal axis of the gas turbine engine.2. The assembly of claim 1 , wherein an angular offset of each of the ends of the segments is between approximately 5° and approximately 70°.3. The assembly of claim 2 , wherein the angular offset of each of the ends is between approximately 20° and approximately 60°.4. The assembly of claim 1 , wherein an angular offset of each of the ends corresponds to an angular offset exhibited by a chord of a blade tip of at least one of the blades.5. The assembly of claim 4 , wherein the angular offset of each of the ends corresponds to a mean camber line of a blade tip of at least one of the blades.6. The assembly of claim 5 , wherein:each intersegment gap has a blade passage region adjacent to which the blades transit during rotation; andeach blade passage region exhibits a curvature corresponding to the mean camber line of a blade tip of at least one of the blades.7. The assembly of claim 6 , wherein:each intersegment gap has a leading edge portion extending forward from a corresponding blade passage region; andeach leading edge portion is linear in shape.8. The ...

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29-08-2013 дата публикации

Counter-rotating low pressure turbine with gear system mounted to mid turbine frame

Номер: US20130219856A1
Принадлежит: Individual

A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. The gear system is mounted to a mid-turbine frame.

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29-08-2013 дата публикации

Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing

Номер: US20130219884A1
Принадлежит: Williams International Corp

An internal combustion engine cylinder head is based upon a one-piece structure including a number of exhaust runners, an exhaust collector, and a turbocharger exhaust turbine housing, all formed as one-piece.

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29-08-2013 дата публикации

Geared turbofan architecture for improved thrust density

Номер: US20130219907A1
Принадлежит: United Technologies Corp

A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

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