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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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05-01-2012 дата публикации

Turbine nozzles and methods of manufacturing the same

Номер: US20120003086A1

Автор: Daniel Ryan, Donald G. Godfrey, Jason Smoke, Mark C. Morris

Принадлежит: Honeywell International Inc

A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.

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Номер записи: 1

20-11-2011 дата публикации

Модуль для паровой турбины

Номер: RU0000110410U1

Автор: Жак МИЗЕРА, Жюльен РОЖЕ

Принадлежит: АЛЬСТОН ТЕКНОЛОДЖИ ЛТД

1. Модуль (1) для паровой турбины, содержащий внутренний кожух (5) турбины с, по меньшей мере, одним комплектом неподвижных лопаток, ротор (6), оснащенный, по меньшей мере, одним комплектом лопаток, и плиту (16), при этом внутренний кожух (5) турбины опирается на плиту (16) посредством, по меньшей мере, двух поперечин (20), закрепленных на упомянутом внутреннем кожухе (5) турбины, а соединение между упомянутыми поперечинами (20) и плитой (16) выполнено в виде нескольких механических средств соединения (23), каждое из которых обеспечивает предотвращение подъема внутреннего кожуха (5) турбины относительно плиты (16), а также обеспечивает скольжение упомянутого внутреннего кожуха (5) турбины по подобной плите (16). ! 2. Модуль по п.1, отличающийся тем, что место (22) сопряжения между поперечиной (20) и плитой (16) является, по существу, горизонтальным, при этом каждое средство (23) соединения содержит вертикальную штангу (24), неподвижно закрепленную в плите (16), и оснащено шайбой (30), каждая поперечина (20) опирается на плиту (16) посредством упомянутых штанг (24), проходящих через нее с зазором вдоль места (22) сопряжения, а шайбы (30) расположены над каждой поперечиной (20). ! 3. Модуль по п.2, отличающийся тем, что каждое средство (23) соединения содержит управляющие устройства (27), закрепленные на плите (16) и обеспечивающие локальное регулирование по высоте внутреннего кожуха (5) турбины, при этом каждая поперечина (20) опирается на управляющее устройство (27). ! 4. Модуль по п.3, отличающийся тем, что управляющее устройство является вращательным приводом (27), приводимым в действие в месте (22) сопряжения, после того как поперечина (20) установлена на упомянутое управляющее ус� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 110 410 (13) U1 (51) МПК F01D 25/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ТИТУЛЬНЫЙ ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21)(22) Заявка: 2011114266/28, 12.04.2011 (24) Дата начала отсчета ...

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Номер записи: 2

20-02-2015 дата публикации

Система для компрессора турбонагнетателя (варианты)

Номер: RU0000150653U1

Автор: Гарольд Хойминь СУНЬ, Даниэль Уильям КЕНТРОУ, Дейв Р. ХАННА, Лянцзюнь ХУ, Томас ПОЛЛЕЙ

Принадлежит: ФОРД ГЛОУБАЛ ТЕКНОЛОДЖИЗ, ЭлЭлСи

1. Система для компрессора турбонагнетателя, содержащая:приводимый в движение кольцеобразный диск, содержащий дроссельные отверстия в нем;наружный кольцеобразный диск, содержащий дроссельные отверстия в нем; ипривод для поворачивания приводимого в движение кольцеобразного диска относительно наружного кольцеобразного диска, чтобы менять совмещение дроссельных отверстий приводимого в движение кольцеобразного диска и наружного кольцеобразного диска.2. Система по п. 1, в которой каждое из дроссельных отверстий расположено смежно впуску дроссельного канала, открытого к впуску компрессора, когда дроссельные отверстия совмещены, при этом выпуск дроссельного канала находится в сообщении по текучей среде с крыльчаткой в положении ниже по потоку от передней кромки разделяющих лопастей и передней кромки полных лопастей крыльчатки.3. Система по п. 2, дополнительно содержащая стравливающий канал, выпуск которого постоянно открыт к впуску компрессора, и впуск которого находится в сообщении по текучей среде с крыльчаткой выше по потоку от передней кромки разделяющих лопастей и ниже по потоку от передней кромки полных лопастей.4. Система по п. 3, в которой стравливающий канал расположен аксиально внутри дроссельного канала.5. Система по п. 1, в которой привод является вакуумным приводом.6. Система по п. 1, дополнительно содержащая контроллер двигателя с командами, хранимыми в нем, для управления приводом на основании условий работы компрессора турбонагнетателя.7. Система по п. 1, в которой наружный кольцеобразный диск содержит вставную часть на своей внутренней окружности, причем периферия вставной части совмещена с вне� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 150 653 U1 (51) МПК F02B 37/12 (2006.01) F02D 23/00 (2006.01) F04B 39/08 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ТИТУЛЬНЫЙ (21)(22) Заявка: ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ 2014125533/06, 24.06.2014 (24) Дата начала отсчета срока действия патента: 24.06.2014 Приоритет(ы): (30) Конвенционный ...

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Номер записи: 3

27-08-2015 дата публикации

Двигатель внутреннего сгорания с наддувом

Номер: RU0000154639U1

Автор: Андреас КУСКЕ, Арнд Арнд ЗОММЕРХОФФ, Ванко СМИЛЯНОВСКИ, Йорг КЕММЕРЛИНГ, Норберт Андреас ШОРН, Хельмут Маттиас КИНДЛЬ

Принадлежит: ФОРД ГЛОУБАЛ ТЕКНОЛОДЖИЗ, ЭлЭлСи

1. Двигатель внутреннего сгорания с наддувом, содержащий по меньшей мере одну головку блока цилиндров с по меньшей мере двумя цилиндрами и по меньшей мере один турбонагнетатель с приводом от выхлопных газов с по меньшей мере одной турбиной (1, 11), причемкаждый цилиндр имеет по меньшей мере один выходной проем для выпуска выхлопных газов из цилиндра, причем к каждому выходному проему примыкает выпускная магистраль,по меньшей мере два цилиндра выполнены с образованием по меньшей мере двух групп, в каждом случае с по меньшей мере одним цилиндром,выпускные магистрали цилиндров из каждой группы цилиндров соединены с образованием соответствующей общей выпускной магистрали, таким образом образуя выпускной коллектор,по меньшей мере две общих выпускных магистрали присоединены к многоканальной сегментированной турбине (1, 11), которая содержит по меньшей мере один ротор (3), установленный на вращающемся валу (4) в корпусе (2) турбины, и по меньшей мере два канала (8, 9) которой на виде в сечении, перпендикулярном валу (4) ротора (3), расположены друг над другом по меньшей мере вдоль дугообразного участка и окружают по меньшей мере один ротор (3) в форме спирали с разными радиусами, и открыты к по меньшей мере одному ротору (3) в каждом случае вдоль кругового дугообразного участка таким образом, что в каждом случае одна общая выпускная магистраль присоединена к одному из по меньшей мере двух каналов (8, 9) турбины (1, 11), в каждом случае два смежных канала (8, 9) отделены друг от друга по меньшей мере на участках и на продолжении общих выпускных магистралей в корпусе (2) турбины посредством стенки (5) корпуса, при этом на стороне ротора по меньш� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 154 639 U1 (51) МПК F02B 37/007 (2006.01) F02D 23/00 (2006.01) F01D 17/14 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ТИТУЛЬНЫЙ (21)(22) Заявка: ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ 2014127842/06, 08.07.2014 (24) Дата начала отсчета срока действия патента: 08.07.2014 ...

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Номер записи: 4

12-01-2012 дата публикации

Split flow valve arrangement

Номер: US20120006433A1

Автор: Antony Morgan

Принадлежит: Rolls Royce PLC

A split flow valve arrangement comprising a first valve portion having an inlet, a first outlet and a second outlet; and a second valve portion having a first inlet coupled to the first outlet, a second inlet coupled to the second outlet, a main outlet and a secondary outlet. The inlet is selectively coupled to none, one or both of the first and second outlets; the first inlet is selectively coupled to the main outlet and the second inlet is selectively coupled to the secondary outlet. The first and second valve portions are constrained to move in synchronicity to therefore selectively direct fluid to flow from the inlet to none, one or both of the main and secondary outlets.

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Номер записи: 5

12-01-2012 дата публикации

Axially angled annular seals

Номер: US20120007317A1

Автор: Alexander R. Beeck

Принадлежит: Siemens Energy Inc

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

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Номер записи: 6

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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Номер записи: 7

19-01-2012 дата публикации

High-Flow-Capacity Centrifugal Hydrogen Gas Compression Systems, Methods and Components Therefor

Номер: US20120011857A1

Автор: Alexander Gofer, Francis A. DiBella, Frederick E. Becker, Jamin J. Bitter, Karl D. Wygant, Kerry N. Oliphant, Robert J. Pelton, Sharon E. Wight

Принадлежит: Concepts ETI Inc

Hydrogen gas compression systems that each include a multistage centrifugal compressor in which each stage has an inlet-to-outlet pressure rise ratio of about 1.20 or greater. In one embodiment, the multistage compressor includes six high-speed centrifugal compressors driven at a speed of about 60,000 rpm. The compressor has an output of more than 200,000 kg/day at a pressure of more than 1,000 psig. The compressors for the compression stages are distributed on both sides of a common gear-box, which has gearing that allows axial thrusts from the compressors to be handled effectively. Each stage's compressor has a unique impeller, which is secured to a support shaft using a tension-rod-based attachment system. In another embodiment, the multistage compressor is driven by a combustion turbine and one or more intercoolers are provided between compression stages. Each intercooler is cooled by coolant from an absorption chiller utilizing exhaust gas from the combustion turbine.

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Номер записи: 8

19-01-2012 дата публикации

High pressure turbine vane cooling hole distrubution

Номер: US20120014809A1

Автор: Franco Di Paola, Francois Doyon, Larry Lebel

Принадлежит: Pratt and Whitney Canada Corp

A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y Cartesian coordinate values set forth in Table 3.

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Номер записи: 9

26-01-2012 дата публикации

Seal assembly for controlling fluid flow

Номер: US20120017594A1

Автор: Burkhard Voss, Christian Kowalski, Fan Zhang, Robert W. Sunshine, Uwe Lohse

Принадлежит: SIEMENS AG, Siemens Energy Inc

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

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Номер записи: 10

26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1

Автор: Brian Patrick Hansen, Christopher Edward LaMaster, David August Snider, Timothy Edward DeJoris

Принадлежит: General Electric Co

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.

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Номер записи: 11

26-01-2012 дата публикации

Fluid Machine

Номер: US20120019010A1

Автор: Hirofumi Wada, Shinji Nakamura

Принадлежит: Sanden Corp

Purpose: To provide a fluid machine, the production efficiency and maintenance characteristics of which can be improved while performance is ensured. Means to attain the purpose: A fluid machine ( 14, 102, 108 ) has a plurality of fluid units ( 16, 20 ) that include rotating bodies ( 40, 66 ) and suck/discharge a working fluid along with the rotation of the rotating bodies, and a drive shaft ( 72 ) connected with the rotating bodies of the fluid units; and an Oldham's coupling ( 85 ) is mounted on a shaft portion between each two adjacent rotating bodies of the drive shaft.

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Номер записи: 12

02-02-2012 дата публикации

Systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel

Номер: US20120023894A1

Автор: Paul Joseph Martin

Принадлежит: General Electric Co

Certain embodiments of the invention may include systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel. According to an example embodiment of the invention, a method is provided for monitoring and predicting corrosion. The method can include monitoring corrosion or corrosive contaminants associated with liquid fuel in a fuel supply system of a gas turbine, predicting, based at least in part on the monitoring, a cumulative level of corrosion of one or more components associated with a gas turbine, and outputting information associated with the monitoring.

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Номер записи: 13

02-02-2012 дата публикации

Auxiliary power unit fire enclosure drain seal

Номер: US20120023897A1

Автор: Brian C. DeDe, Christine Ingrid Schade, David Lau, David Ronald Adair

Принадлежит: Hamilton Sundstrand Corp

A drain assembly for an auxiliary power unit having a hot zone formed by a combustor case comprises a fire enclosure, a drain fitting, a discharge port and a piston seal. The fire enclosure encapsulates the hot zone of the combustor case. The drain fitting connects to the fire enclosure. The discharge port extends from the combustor case into the drain fitting. The piston seal is positioned between the drain fitting and the discharge port.

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Номер записи: 14

02-02-2012 дата публикации

Exhaust manifold flange connection

Номер: US20120023968A1

Автор: Brian H. Terpos, Brian Micklos, Christopher Scogin, David Wiebe, James Marshall, Jonathan Leagon, Robert T. Brooks, Robert W. Spitzer, Scott Smith, Yevgeniy Shteyman

Принадлежит: Siemens Energy Inc

A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.

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Номер записи: 15

02-02-2012 дата публикации

Blade outer air seal and repair method

Номер: US20120027574A1

Автор: Philip R. Belanger, Susan M. Tholen

Принадлежит: United Technologies Corp

An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.

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Номер записи: 16

02-02-2012 дата публикации

Turbine nozzle segment and method of repairing same

Номер: US20120027617A1

Автор: Jose Abiel Garza, Marcin Trajer, Marcin Zak, Pawel Mankowski, Wayne Ray Grady

Принадлежит: General Electric Co

A method is provided for repairing a metallic turbine component which includes at least two airfoils interconnected by a mid-span shroud. The method includes: (a) applying a reinforcement plate to the mid-span shroud; (b) applying braze material to at least a portion of a perimeter of the reinforcement plate; (c) heating the component to melt and flow the braze material between the reinforcement plate and the mid-span shroud; and (d) allowing the braze material to cool and solidify so as to bond the reinforcement plate to the mid-span shroud.

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Номер записи: 17

09-02-2012 дата публикации

Thermal control system for fault detection and mitigation within a power generation system

Номер: US20120031581A1

Автор: Adil Ansari, Eric J. Kauffman, Julio E. Mestroni, Rahul Jaikaran Chillar

Принадлежит: General Electric Co

A system includes a radiation sensor configured to direct a field of view toward at least one conduit along a fluid flow path into a heat exchanger. The radiation sensor is configured to output a signal indicative of a temperature of the at least one conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, to compare the temperature to a threshold range, and to adjust a fluid flow through the fluid flow path or the at least one conduit if the temperature deviates from the threshold range.

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Номер записи: 18

09-02-2012 дата публикации

Low deflection bi-metal rotor seals

Номер: US20120032404A1

Автор: David C. Seib, Mark Joseph Kuzdzal

Принадлежит: Dresser Rand Co

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

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Номер записи: 19

09-02-2012 дата публикации

Ventilation inlet

Номер: US20120034068A1

Автор: Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone.

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Номер записи: 20

09-02-2012 дата публикации

Actuation mechanism for a convertible gas turbine propulsion system

Номер: US20120034080A1

Автор: Gregory E. Reinhardt, Rajendra K. Agrawal

Принадлежит: Agrawal Rajendra K, Reinhardt Gregory E

A method of powering a rotary-wing aircraft includes selectively coupling and uncoupling a first power turbine to change a power distribution between the rotor system and the secondary propulsion system.

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Номер записи: 21

16-02-2012 дата публикации

Method for compensating for combustion efficiency in fuel control system

Номер: US20120036861A1

Автор: Michael John Hughes, William Forrester Seely

Принадлежит: General Electric Co

Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency differences between the starting and ending operating mode that otherwise can lead to severe swings in combustion reference temperature and lean blowout.

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Номер записи: 22

16-02-2012 дата публикации

Methods and systems for adaptively cooling combustion chambers in engines

Номер: US20120037100A1

Автор: Melvin J. Larsen, Roy E. McAlister, Roy Edward McAlister

Принадлежит: McAlister Technologies LLC

The present disclosure is directed to various embodiments of systems and methods for cooling a combustion chamber of an engine. One method includes introducing fuel into the combustion chamber of an engine having an energy transfer device that moves through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The method further includes monitoring a temperature of the combustion chamber. When the temperature reaches a predetermined value, the method also includes introducing coolant into the combustion chamber only during at least one of the power stroke and the exhaust stroke of the energy transfer device.

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Номер записи: 23

23-02-2012 дата публикации

Fuel supply system for gas turbine combustor and fuel supply method for gas turbine combustor

Номер: US20120042658A1

Автор: Ken Ugai, Ryo Higashi, Takeo Hirasaki, Yoshikiyo Okamoto, Yosuke Eto

Принадлежит: Mitsubishi Heavy Industries Ltd

A consumption amount of high-calorific gas such as coke oven gas (COG) during operation of a gas turbine is reduced, halt of the gas turbine due to clogging of a pilot system, a malfunction of a compressor which compresses high-calorific gas is prevented, and reliability of the gas turbine is improved. When operation of the gas turbine ( 11 ) starts, with use of both a first fuel supply system ( 31 ) which supplies a high-calorific fuel for a first nozzle constituting a combustor ( 17 ), and a second fuel supply system ( 32 ) which supplies a low-calorific fuel for a second nozzle constituting the combustor ( 17 ), the high-calorific fuel and the low-calorific fuel are supplied to the combustor ( 17 ), and at a time when the gas turbine ( 11 ) reaches output power which enables continuous operation with only the low-calorific fuel, supply of the high-calorific fuel to the combustor ( 17 ) is shut off, and only the low-calorific fuel is supplied to the combustor ( 17 ).

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Номер записи: 24

23-02-2012 дата публикации

Air turbine starter inlet housing assembly airflow path

Номер: US20120042659A1

Автор: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter

Принадлежит: Hamilton Sundstrand Corp

An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.

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Номер записи: 25

23-02-2012 дата публикации

Air turbine starter turbine blade airfoil

Номер: US20120045342A1

Автор: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter

Принадлежит: Hamilton Sundstrand Corp

A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

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Номер записи: 26

01-03-2012 дата публикации

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

Номер: US20120047905A1

Автор: Marc Rauch, Peter Oskar Baldischweiler

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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Номер записи: 27

01-03-2012 дата публикации

Variable geometry turbine

Номер: US20120051882A1

Автор: John Frederick Parker

Принадлежит: Individual

A variable geometry turbine comprising a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.

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Номер записи: 28

01-03-2012 дата публикации

Retaining ring arrangement for a rotary assembly

Номер: US20120051918A1

Автор: Bruno Chatelois, David F. GLASSPOOLE

Принадлежит: Pratt and Whitney Canada Corp

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

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Номер записи: 29

01-03-2012 дата публикации

Blade for use with a rotory machine and method of assembling same rotory machine

Номер: US20120051921A1

Автор: Kyle William Reno

Принадлежит: Individual

A method for assembling a rotary machine includes providing a rotor including a plurality of rotor wheels. The method also includes positioning the rotor such that at least a portion of a stationary portion of the rotary machine extends at least partially about the rotor. The method further includes providing a blade that includes a blade platform that is formed with a substantially double-C shape. The method also includes coupling the blade to the rotor.

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Номер записи: 30

01-03-2012 дата публикации

Minimizing blockage of holes in turbine engine components

Номер: US20120052200A1

Автор: Benjamin Joseph Zimmerman

Принадлежит: Individual

An airfoil for use in a gas turbine engine is provided, the airfoil having a hole therein. A ceramic plug is inserted in the hole so that the plug extends above a depth of a thermal barrier coating, such as a ceramic, to be placed on the airfoil. The airfoil is then coated by non-line of sight vapor deposition and the plugs are then removed.

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Номер записи: 31

08-03-2012 дата публикации

Fan array fan section in air-handling systems

Номер: US20120057962A1

Автор: Lawrence G. Hopkins

Принадлежит: Huntair Inc

A fan array fan section in an air handling system includes a plurality of fan units arranged in a fan array and positioned within an air handling compartment. One preferred embodiment may include an array controller program to operate the plurality of the fan units at peak efficiency. The plurality of fan units may be arranged in a true array configuration, a space pattern array configuration, a checker board array configuration, rows slightly offset configuration, columns slightly offset configuration, or a staggered array configuration.

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Номер записи: 32

08-03-2012 дата публикации

Axial locking seals for aft removable turbine blade

Номер: US20120057980A1

Автор: Axel Buschmann, Guido Ahaus, Harald Hoell, Peter Schroeder

Принадлежит: SIEMENS AG

A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving the turbine casing cover.

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Номер записи: 33

15-03-2012 дата публикации

Air-oil heat exchanger

Номер: US20120060466A1

Автор: Frederick L. Elsaesser, Frederick M. Schwarz

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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Номер записи: 34

15-03-2012 дата публикации

Apparatus and method for cooling a combustor cap

Номер: US20120060511A1

Автор: Baifang Zuo, Chunyang Wu, Roy Marshall Washam

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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Номер записи: 35

15-03-2012 дата публикации

Energy efficient ips blower assembly

Номер: US20120063879A1

Автор: Leo J. Veilleux, Jr.

Принадлежит: Hamilton Sundstrand Corp

According to the invention a method and apparatus relating to a blower that is used in an environment of particle contaminated air, as with a helicopter engine, is disclosed. The blower has a power input, a fan, a power output attaching to the fan, and a clutch disposed between the power input and the power output whereby the power input may be selectively coupled to the power output to move the fan to vent the particle contaminated air. The clutch, which may be electrically, mechanically or hydraulically engaged, is activated by a user, a particle or altitude sensor, or by a full authority digital electronic controller (“FADEC”).

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Номер записи: 36

15-03-2012 дата публикации

Low-pressure turbine

Номер: US20120063914A1

Автор: Gerald Gillant Gregory Nicolas, OLIVIER Belmonte

Принадлежит: SNECMA SAS

A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

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Номер записи: 37

22-03-2012 дата публикации

Exhaust washed structure and associated composite structure and method of fabrication

Номер: US20120066882A1

Автор: Buddhadev Chakrabarti, Gopal P. Mathur, Leanne L. Lehman, Michael L. Hand

Принадлежит: Boeing Co

A composite structure and an associated exhaust washed structure are provided which may be formed of ceramic matrix composite (CMC) materials. A method of fabricating a composite structure which may include the CMC material is also provided. A composite structure may include a corrugated septum extending in a lengthwise direction. The composite structure may also include a flute within which the corrugated septum is disposed to form, for example, a partitioned flute assembly.

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Номер записи: 38

22-03-2012 дата публикации

Assembly facilitation apparatus and method

Номер: US20120066906A1

Автор: Bernd P. Daeschner

Принадлежит: General Electric Co

An assembly apparatus that includes a frame and a load plate operatively connected to the frame. The load plate is configured to support a workpiece and is selectively extendable from a first position in which at least a portion of the load plate is positioned over the frame, to a second position in which the load plate is extended from the frame such that the workpiece is transferable from the load plate to a sub-assembly.

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Номер записи: 39

22-03-2012 дата публикации

Wireless sensor for an aircraft propulsion system

Номер: US20120068003A1

Автор: Nicholas Charles Soldner, Peter G. Smith, Sanjay Bajekal, Vijaya Ramaraju Lakamraju

Принадлежит: United Technologies Corp

A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

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Номер записи: 40

29-03-2012 дата публикации

Cooled turbine blades for a gas-turbine engine

Номер: US20120076665A1

Автор: Erik Janke, Heinz-Peter SCHIFFER, Jens Taege, Knut Lehmann, Nils WINTER, Sebastian Meier, Thomas SCHIESSL

Принадлежит: Rolls Royce Deutschland Ltd and Co KG

The present invention relates to a cooled turbine blade for a gas-turbine engine having at least one cooling duct ( 14 ) extending radially, relative to a rotary axis of the gas-turbine engine, inside the airfoil and air-supply ducts ( 12 ) issuing into said cooling duct, characterized in that the cooling duct ( 14 ) extends into the blade root ( 6 ) in order to generate close to the wall a cooling airflow moved at high circumferential velocity and radially in helical form and that in the area of the blade root ( 6 ) at least one nozzle-shaped air-supply duct ( 12 ) issues into the cooling duct ( 14 ) tangentially or with a tangential velocity component.

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Номер записи: 41

05-04-2012 дата публикации

Reduced gulp fluid reservoir

Номер: US20120080272A1

Автор: Larry W. Spires, Paul A. Dickie

Принадлежит: United Technologies Corp

An assembly includes a reservoir for holding a fluid, and a scavenge passage connected to the reservoir at a reservoir inlet. The scavenge passage returns the fluid from a delivery location to the reservoir. A bleed passage is connected in fluid communication between the reservoir and the scavenge passage.

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Номер записи: 42

05-04-2012 дата публикации

Variable geometry turbine

Номер: US20120082539A1

Автор: Khimani Mohiki

Принадлежит: Cummins Turbo Technologies Ltd

A variable geometry turbine for a turbocharger has a plurality of vanes disposed in an inlet passageway of a turbine housing outboard of the turbine wheel. The vanes are movable so as to adjust the effective cross-section area of the inlet between a first position in which the area of the inlet is a minimum and a second position in which the area of the inlet is a maximum. The movement of one end of the vanes is supported by a plurality of first guide tracks, such as slots, defined in a guide member. A vane actuator such as, for example a unison ring, effects movement of the vanes. The vane actuator has a plurality of actuation tracks (e.g. slots) for engagement with the vanes and is rotatably disposed in the housing. When it rotates the vane actuator induces sliding translation of the vanes relative to the first guide tracks in a first direction and sliding translation of the vanes relative to the actuation tracks in a second direction so as to adjust the cross-section area of the inlet. The swirl angle changes between the first and second positions.

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Номер записи: 43

05-04-2012 дата публикации

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

Номер: US20120082542A1

Автор: Masato Misawa

Принадлежит: Individual

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

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Номер записи: 44

05-04-2012 дата публикации

Apparatus and methods for cooling platform regions of turbine rotor blades

Номер: US20120082550A1

Автор: Adrian Lional Scott, John Wesley Harris, JR., Scott Edmond Ellis, Xiaoyong Fu

Принадлежит: General Electric Co

A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.

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Номер записи: 45

05-04-2012 дата публикации

Cooed IBR for a micro-turbine

Номер: US20120082563A1

Автор: Jack W. Wilson, Jr., James P. Downs, John E. Ryznic

Принадлежит: Florida Turbine Technologies Inc

A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

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Номер записи: 46

05-04-2012 дата публикации

Cooled rotor blade

Номер: US20120082567A1

Автор: Ian Tibbott, Oliver C.T. TIBBOTT

Принадлежит: Rolls Royce PLC

A cooled turbine rotor blade for a gas turbine engine is provided. The engine has an annular flow path for conducting working fluid though the engine. The blade has an aerofoil section for extending across the annular flow path. The blade further has a root portion radially inward of the aerofoil section for joining the blade to a rotor disc of the engine. The blade further has a platform between the aerofoil section and the root portion. The platform extends laterally relative to the radial direction of the engine to form an inner boundary of the annular flow path and to provide a rear overhang portion which projects in use towards a corresponding platform of a downstream nozzle guide vane. The platform contains at least one internal elongate plenum chamber for receiving cooling air. The longitudinal axis of the plenum chamber is substantially aligned with the circumferential direction of the engine. The plenum chamber supplies the cooling air to a plurality of exit holes formed in the external surface of the rear overhang portion to cool that portion.

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Номер записи: 47

05-04-2012 дата публикации

Method for installing heat shielding on a fixed internal structure of a jet engine nacelle

Номер: US20120082808A1

Автор: Laurence Lemains, Pascal Mer

Принадлежит: Aircelle SA

The invention relates to a method for installing heat shielding ( 31 ), including a heat cushion ( 33 ) covered with a ply ( 35 a ) made from a structural material, on a fixed internal structure ( 29 ) of a jet engine nacelle, including the following consecutive steps: spreading an adhesive ( 43 ) that guarantees good mechanical strength at high temperatures on at least one of the elements selected from said ply ( 35 a ) and an internal skin ( 39 ) of the fixed internal structure; applying said ply ( 35 a ) to said internal skin ( 39 ); and, if necessary, setting said adhesive ( 43 ).

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Номер записи: 48

12-04-2012 дата публикации

Turbofan jet engine

Номер: US20120087787A1

Автор: Dewain Ray Brown

Принадлежит: Individual

There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet engine includes a nacelle. The nacelle includes a forward extension proximate the fan and extending forward therefrom. The forward extension is funnel shaped to impart radial momentum to intake air during operation. The nacelle includes a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. The vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. The vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan.

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Номер записи: 49

12-04-2012 дата публикации

Rotor For Turbomachines With Shrouded Blades

Номер: US20120087794A1

Автор: Paolo Calza, Rosario Grillo, Sergio Salvano

Принадлежит: Avio SpA

A rotor for turbomachines with shrouded blades comprising a row of a plurality of blades covered by an external ring, coaxial to said row of blades; the external ring being composed of a plurality of sectors, commonly referred to as shrouds, which are adjacent to one another and transversely and circumferentially attached to the end of respective blades; a damping member being arranged so as to straddle a respective pair of adjacent sectors and being pushed, in use, against radially internal surfaces of the sectors of the pair of adjacent sectors.

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Номер записи: 50

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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Номер записи: 51

19-04-2012 дата публикации

Combustion chamber comprising a condensation-proof barrier on a regenerative circuit

Номер: US20120090292A1

Автор: Daniel Cornu

Принадлежит: SNECMA SAS

The invention concerns a combustion chamber ( 10 ) comprising a neck ( 15 ) downstream of the injection ( 11 ) of gases, and downstream of this neck a divergent section ( 20 ) whereof the outer face of the wall ( 30 ), when in operation, is cooled by a cooling system using a cryogenic product and surrounding this outer face. This divergent section ( 20 ), on the inner face ( 32 ) of its wall ( 30 ), comprises a coating ( 40 ) acting as temperature compensator so that the temperature of the inner face ( 42 ) of the coating ( 40 ) is higher than the condensation temperature of the combustion gases on this inner face ( 42 ) under operating conditions, such that no condensation is formed on this inner face ( 42 ).

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Номер записи: 52

19-04-2012 дата публикации

Clustered inlet particle separator

Номер: US20120090468A1

Автор: Philip Harold Snyder

Принадлежит: Individual

A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

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Номер записи: 53

19-04-2012 дата публикации

Aircraft nacelle including a continue joint area between an outer wall and a front frame

Номер: US20120091285A1

Автор: Alain Porte, Frederic Chelin

Принадлежит: AIRBUS OPERATIONS SAS

An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip.

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Номер записи: 54

19-04-2012 дата публикации

Isentropic compression inlet for supersonic aircraft

Номер: US20120091286A1

Автор: Donald C. Howe, Preston A. Henne, Timothy R. Conners

Принадлежит: Gulfstream Aerospace Corp

A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

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Номер записи: 55

19-04-2012 дата публикации

Systems and methods for providing ac power from multiple turbine engine spools

Номер: US20120091716A1

Автор: Farhad Nozari, Richard A. Cote

Принадлежит: Boeing Co

Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.

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Номер записи: 56

19-04-2012 дата публикации

Turbine casing

Номер: US20120093641A1

Автор: Stephen Christopher Chieco

Принадлежит: General Electric Co

A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points.

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Номер записи: 57

19-04-2012 дата публикации

Thermally insulating turbine coupling

Номер: US20120093661A1

Автор: Keith R. Pullen, Michael J. Vick

Принадлежит: IMPERIAL INNOVATIONS LTD

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

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Номер записи: 58

19-04-2012 дата публикации

Method and coating for protecting and repairing an airfoil surface

Номер: US20120094099A1

Автор: Shek C. Hong

Принадлежит: Hontek Corp

This invention relates to the repair and removal of erosion or impact damage using hand sandable elastomeric coatings on a curved substrate, particularly such surfaces as the leading edge of the airfoil. Specialized applicators and methods of use are also disclosed.

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Номер записи: 59

19-04-2012 дата публикации

Distributed small engine fadec

Номер: US20120095661A1

Автор: Kevin P. Roy, Thaddeus J. Zebrowski

Принадлежит: Hamilton Sundstrand Corp

A full authority digital engine controller (FADEC) controls an engine attached to an airframe. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital data bus electrically connecting the ADC to the EEC. The ADC is electrically connected to a plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data. The digital bus conducts the airframe sensor digital data to the EEC.

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Номер записи: 60

26-04-2012 дата публикации

Twelve-hour structure for thrust reverser, in particular with grids

Номер: US20120097761A1

Автор: Georges Laurent Valleroy, Jean-Bernard Vache, Julien Vache

Принадлежит: Aircelle SA

The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam ( 1 ) capable of holding a reverser half cowling and including a plurality of hinge yokes ( 9 c ) for rotatingly mounting said half beam ( 1 ) on a nacelle-holding mast. The half beam ( 1 ) is at least partially made of a composite material.

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Номер записи: 61

26-04-2012 дата публикации

Seal apparatus

Номер: US20120098211A1

Автор: Bhaskar Mani, DONKADA Santhosh, Upendra Prabhu Nath Vemula Gopinath, Vishwas Kumar Pandey

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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Номер записи: 62

26-04-2012 дата публикации

Rotary machine having non-uniform blade and vane spacing

Номер: US20120099961A1

Автор: Brian Denver Potter, John McConnell Delvaux

Принадлежит: General Electric Co

A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.

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Номер записи: 63

26-04-2012 дата публикации

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

Номер: US20120099988A1

Автор: Francois Gallet, Gilles Alain Charier

Принадлежит: SNECMA SAS

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

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Номер записи: 64

26-04-2012 дата публикации

Blade

Номер: US20120100006A1

Автор: Nicholas M. MERRIMAN, Simon Read

Принадлежит: Rolls Royce PLC

A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.

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Номер записи: 65

26-04-2012 дата публикации

Annular flow channel section for a turbomachine

Номер: US20120100008A1

Автор: Fathi Ahmad

Принадлежит: SIEMENS AG

An annular flow channel section for a turbomachine is provided. The annular flow channel includes a guide vane ring having a number of guide vanes which are arranged next to each other in the circumferential direction, each guide vane including a vane base, a platform and an airfoil that projects into the flow channel in a radiating pattern. The flow channel is delimited on the platform side by shielding elements, each of which being disposed between two immediately adjacent airfoils, wherein the shielding elements are arranged on the platforms for creating a particularly space-saving flow channel section while creating a gap, and impingement-cooling openings are provided in the platform.

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Номер записи: 66

26-04-2012 дата публикации

Control system

Номер: US20120100011A1

Автор: Curtis Christian Crane, Eric J. Smyder, Florin Iancu, Gregory K. Beaverson, John Trevino, JR., Patrick C. Marks, Robert E. Stabley, Rudy Chervil, Steven T. Sommer

Принадлежит: Johnson Controls Technology Co

A control system is provided that can identify the occurrence of a single surge cycle in centrifugal compressor using various methods and devices. Once the occurrence of a single surge cycle is identified, the control system can take remedial action to respond to the surge cycle, such as by adjusting the position of a variable geometry diffuser, and restore the centrifugal compressor to stable operation.

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Номер записи: 67

03-05-2012 дата публикации

Systems, methods, and apparatus for compensating fuel composition variations in a gas turbine

Номер: US20120102914A1

Автор: Denis Michel Martin, Joseph Kirzhner, Matthieu Paul Frederic Vierling, Nicolas Pourron, Predrag Popovic

Принадлежит: General Electric Co

Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

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Номер записи: 68

03-05-2012 дата публикации

Gas turbine engine bifurcation located fan variable area nozzle

Номер: US20120102915A1

Автор: Constantine Baltas

Принадлежит: Individual

A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, a fan, and a variable area flow system. The gear system defines a gear reduction ratio of greater than or equal to about 2.3. The fan is driven by the gear system about the axis to generate a bypass flow. The variable area flow system operates to effect the bypass flow.

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Номер записи: 69

03-05-2012 дата публикации

Radial gas expander

Номер: US20120107108A1

Автор: Hideki Nagao, Hirotaka Higashimori, Katsuki Yagi, Katsuya Yamashita, Masahiro Kobayashi, Yasushi Mori

Принадлежит: Mitsubishi Heavy Industries Compressor Corp

Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections ( 11 A, 11 B) formed of two-or-more-stage impeller vanes ( 14 a to 14 h ) arranged between bearings ( 21 a, 21 b ) on a rotor shaft ( 13 ) consisting of a single shaft are housed in a signal casing ( 10 ).

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Номер записи: 70

03-05-2012 дата публикации

Bearing retention assembly for and method of assembling turbochargers

Номер: US20120107112A1

Автор: Daniel J. Barlog

Принадлежит: Precision Turbo and Engine Rebuilders Inc

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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Номер записи: 71

03-05-2012 дата публикации

Partial coarse pitch start ram air turbine with enhanced spring support

Номер: US20120107119A1

Автор: David G. Bannon

Принадлежит: Hamilton Sundstrand Corp

A Ram Air Turbine (RAT) is provided and includes a turbine hub having an end plate and a nose cone attached thereto at trailing and leading ends, respectively, a governor shaft, to which turbine blades are connected, which is coupled to the end plate and supported within the nose cone to be rotatable with the turbine blades about a central axis thereof and axially movable from a first position relative to the turbine hub to a second position relative to the turbine hub and a hub assembly operably coupled to the turbine hub, the governor shaft and the turbine blades whereby the hub assembly biases the governor shaft toward the first position at low rotational speeds such that the turbine blades assume a partial coarse pitch angle, and the second position at high rotational speeds such that the turbine blades assume a fine pitch angle.

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Номер записи: 72

10-05-2012 дата публикации

Variable area fan nozzle fan flutter management system

Номер: US20120110980A1

Автор: Robert J. Morris, Zbigniew M. Grabowski

Принадлежит: Individual

A system and method of controlling a fan blade flutter characteristic of a gas turbine engine includes adjusting a variable area fan nozzle in response to a neural network.

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Номер записи: 73

10-05-2012 дата публикации

Turbocharger overheating protection device and method of its manufacture

Номер: US20120110997A1

Автор: Karlheinz Wienand, Mario Bachmann

Принадлежит: HERAEUS SENSOR TECHNOLOGY GMBH

A housing between mineral-insulated cable and connecting wire in a turbocharger overheating protection device may include the following characteristics: coiled regions of springs ( 10 ) arranged point-symmetrically to each other; or the springs ( 10 ) are not placed on axes; or the coil regions of the coil springs ( 10 ) for cushioning the film resistor are shorter than its substrate length and longer than its substrate width; or the connecting wires of the film resistor are shorter than its substrate length and longer than its substrate width; or the springs are arranged staggered in their longitudinal direction adjacent to each other; or coil springs ( 10 ) are used, in which the coils are located only in one half of the spring ( 10 ) and the coils of one spring are arranged staggered in the longitudinal direction to the coils of the other spring ( 10 ).

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Номер записи: 74

10-05-2012 дата публикации

Control method for cooling a turbine stage in a gas turbine

Номер: US20120111020A1

Автор: Federico Bonzani, Luca Bozzi, Marco Mantero

Принадлежит: Ansaldo Energia SpA

A control method for cooling a turbine stage of a gas turbine, whereby cooling air is bled from combustion air flowing in a compressor of the gas turbine, and is fed to a cooling circuit staring from a stator of the turbine stage; and cooling airflow is adjusted as a function of the pressure at the inlet of the cooling circuit, and as a function of the combustion air pressure at the exhaust of the compressor; more specifically, there is a feedback control setting a setpoint, which is predetermined as a function of the power output of the turbine to reduce contaminating emissions.

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Номер записи: 75

10-05-2012 дата публикации

Turbine assembly and method for securing a closure bucket

Номер: US20120114490A1

Автор: Manish Joshi, Vivekanandhan Thiruvettipuram Madhivanan

Принадлежит: General Electric Co

According to one aspect of the invention, a turbine assembly is provided, wherein the turbine assembly includes a drum rotor comprising a slot and a closure bucket configured to be placed in the slot, the closure bucket including a lock pin disposed in a base member of the closure bucket. In addition, a portion of the lock pin is configured to rotatably extend into a cavity in the slot thereby securing the closure bucket within the slot.

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Номер записи: 76

17-05-2012 дата публикации

Gas turbine engine with pylon mounted accessory drive

Номер: US20120117940A1

Автор: Michael Winter

Принадлежит: United Technologies Corp

A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment.

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Номер записи: 77

17-05-2012 дата публикации

Power plant and method of operation

Номер: US20120119512A1

Автор: Samuel David Draper

Принадлежит: General Electric Co

A main air compressor delivers a compressed ambient gas flow with a compressed ambient gas flow rate to a turbine combustor. A fuel stream with a flow rate is delivered to the turbine combustor and mixed with the compressed ambient gas flow and an exhaust gas flow and burned with substantially stoichiometric combustion to form the exhaust gas flow and drive a turbine, thus operating the power plant at a first load. A portion of the exhaust gas flow is recirculated from the turbine to the turbine compressor and a portion is delivered to an exhaust path. The fuel stream flow rate and the compressed ambient gas flow rate are reduced, and substantially stoichiometric combustion is maintained and the power plant is operated at a second load. The fuel stream flow rate is further reduced and lean combustion is achieved and the power plant is operated at a third load.

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Номер записи: 78

17-05-2012 дата публикации

Exhaust Hood Diffuser

Номер: US20120121404A1

Автор: Joshy John, Sudhakar Neeli

Принадлежит: General Electric Co

The present application provides a diffuser for an exhaust hood of a steam turbine. The diffuser may include a first end adjacent to a last bucket and a second end downstream of a steam guide and adjacent to a bearing cone. An exhaust flow path extends therethrough. The second end may include an axial extension enlarging the exhaust flow path.

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Номер записи: 79

17-05-2012 дата публикации

Turbine blade assembly including a damper

Номер: US20120121434A1

Автор: Hyun Dong Kim, Yong Weon Kim, Yungmo Kang

Принадлежит: Solar Turbines Inc

A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper may have a forward plate. The damper may further have an aft plate including a larger surface area than the forward plate. The aft plate may have at least one aperture for regulating a flow of gas through the aft plate. The damper may also have a longitudinal structure connecting the forward plate and the aft plate.

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Номер записи: 80

17-05-2012 дата публикации

Anisotropic bearing supports for turbochargers

Номер: US20120121446A1

Автор: Gerald D. Larue, Kostandin Gjika, Mohsiul Alam, Walter Lee Meacham

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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Номер записи: 81

24-05-2012 дата публикации

Variable area fan nozzle fan flutter management system

Номер: US20120124965A1

Автор: Ray W. Carmichael, Robert J. Morris, Zbigniew M. Grabowski

Принадлежит: Individual

A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.

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Номер записи: 82

24-05-2012 дата публикации

Repair of turbine components and solder alloy therefor

Номер: US20120125979A1

Автор: Bernd Daniels, Michael Hillen

Принадлежит: MTU AERO ENGINES GMBH

A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated.

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Номер записи: 83

24-05-2012 дата публикации

Variable geometry turbine

Номер: US20120128471A1

Автор: Arun Tamil Selvan Vijayakumar, David Andrew Luck, Stephen Edward Garrett

Принадлежит: Cummins Turbo Technologies Ltd

A variable geometry turbine comprises a turbine wheel mounted within a housing for rotation about a turbine axis; and a gas flow control passage upstream of said turbine wheel, the gas flow control passage being defined at least in part between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member also comprising second and third surfaces which oppose the first surface. The movable wall member is movable in an axial direction so as to vary the size of the gas flow control passage. There is a first gas region of the turbine, a portion of which is upstream of the gas flow control passage, the first gas region including at least a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage which contains the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface.

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Номер записи: 84

24-05-2012 дата публикации

Turbine engine compressor stator

Номер: US20120128497A1

Автор: Carl S. Richardson, Edwin M. Worth, Hope C. Rowley, Paul W. Baumann

Принадлежит: Individual

A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.

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Номер записи: 85

24-05-2012 дата публикации

Bladed disk assembly

Номер: US20120128498A1

Автор: Matthew Peter Basiletti, Michelle Lynn Tucker, Richard Christopher Uskert

Принадлежит: Rolls Royce Corp

A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.

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Номер записи: 86

24-05-2012 дата публикации

Abradable layer including a rare earth silicate

Номер: US20120128879A1

Автор: Kang N. Lee, Michael Cybulsky, Raymond J. Sinatra

Принадлежит: Rolls Royce Corp

An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia.

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Номер записи: 87

31-05-2012 дата публикации

Gas turbine of the axial flow type

Номер: US20120134779A1

Автор: Alexander Anatolievich Khanin, Valery Kostege

Принадлежит: Individual

In an axial flow gas turbine ( 30 ), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices ( 43 - 48 ) to direct cooling air that has already been used to cool, especially the airfoils of the vanes ( 31 ) of the turbine stage (TS), into a first cavity ( 41 ) located between the outer blade platforms ( 34 ) and the opposed stator heat shields ( 36 ) for protecting the stator heat shields ( 36 ) against the hot gas and for cooling the outer blade platforms ( 34 ).

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Номер записи: 88

31-05-2012 дата публикации

Mechanism for modulating diffuser vane of diffuser

Номер: US20120134784A1

Автор: Cheng-Chung Yen, Ching-Fu Chen, Chung-Ping Chiang, Yung-Lo Chow

Принадлежит: Industrial Technology Research Institute ITRI

A mechanism modulates a fluid flow in a diffuser flow path of a compressor diffuser, including: a shroud disposed on the diffuser flow path and having a cam and a driving wheel fixed base; a diffuser vane having a diffuser guide vane disposed in the diffuser flow path and a diffuser vane shaft fixedly disposed on the diffuser vane that penetrates from the diffuser flow path through the shroud; a driving ring sleeved on the cam and having a moving bar; a sliding block having one end connected with one end the diffuser vane shaft that penetrates through the shroud, and the other end sleeved on a sliding groove formed on the moving bar; a driving wheel disposed in the driving wheel fixed base and having a driving shaft connected to an actuator outside of the compressor; and a driving cable connected to the driving wheel and the driving ring.

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Номер записи: 89

31-05-2012 дата публикации

Multi-stage radial turbine

Номер: US20120134797A1

Автор: Hirotaka Higashimori, Katsuki Yagi

Принадлежит: Mitsubishi Heavy Industries Compressor Corp

A multi-stage radial turbine that is capable of reducing the number of bearings and of improving the conversion efficiency is provided. Provided are a plurality of radial turbine rotor blades ( 5 ) that are attached at intervals to a single rotating shaft ( 3 ); a plurality of nozzles ( 19 ) that are individually installed on an upstream side of each of the radial turbine rotor blades and that accelerate a flow of fluid; a connecting channel portion ( 9 ) that connects gas an outlet portion ( 23 ) of the radial turbine rotor blade ( 5 ) on the front stage side and an upstream side of the nozzle ( 19 ) on the rear stage side, the connecting channel portion ( 9 ) being provided with a U-shaped bent portion ( 25 ) that deflects outward in the radial direction the flow of fluid that is made to flow out from the radial turbine rotor blade ( 5 ) in the shaft direction; a vane portion having a plurality of deflecting vanes ( 27 ) that deflect the flow of fluid inward in a rotation direction (R) while guiding the flow of fluid from the U-shaped bent portion ( 25 ) outward in the radial direction; and a return bent portion ( 31 ) that deflects inward in the radial direction the flow that is made to flow out from the vane portion ( 29 ) while swirling outward in the radial direction.

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Номер записи: 90

31-05-2012 дата публикации

Fluid Turbine Having Optimized Blade Pitch Profiles

Номер: US20120134820A1

Автор: Jason Daniel Cormey, Robert Clifton Vance

Принадлежит: Broadstar Investment Co LLC, Broadstar Wind Systems Group LLC

A fluid turbine comprising a rotor, having an axis of rotation, comprising at least two rotor blades disposed at a radius from the axis of rotation, each rotor blade having a pitch axis and a variable pitch angle. The fluid turbine comprises a mechanism operable to control the pitch angle of at least one rotor blade about its pitch axis and to vary the pitch angle of the rotor blade between various pitch angles as the blade moves radially about the axis of rotation of the rotor.

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Номер записи: 91

31-05-2012 дата публикации

method of manufacturing a component

Номер: US20120135198A1

Автор: Oliver M. Strother

Принадлежит: Rolls Royce PLC

A method of manufacturing a component having first and second layers, the first and/or second layers including one or more depressions provided on a surface of the respective layer. The method including: arranging the first and second layers so that they face one another and with the depressions on inner facing surfaces of the layers; diffusion bonding the first and second layers together about their edges; applying a first differential pressure across each of the first and second layers to evacuate an inner space defined by the layers, thereby forming one or more depressions on an outer facing surface of the first or second layer; and applying a second differential pressure across each of the first and second layers to expand the inner space defined by the layers.

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Номер записи: 92

07-06-2012 дата публикации

Fluid impingement arrangement

Номер: US20120137650A1

Автор: Andrew J. Mullender, Brian A. Handley, Christopher T.J. SHEAF, David Macmanus, Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

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Номер записи: 93

07-06-2012 дата публикации

Vacuum pump

Номер: US20120143390A1

Автор: Katsuhide Machida, Keiichi Ishii, Tooru Miwata, Tsutomu Takaada, Yasushi Maejima, Yoshinobu Ohtachi

Принадлежит: Edwards Japan Ltd

To provide a vacuum pump capable of performing temperature control using one or more heating devices or cooling devices fewer than the number of temperature sensors arranged in the pump. One temperature sensor is arranged for each target in the pump, while only one set consisting of a heater 147 and a magnetic valve 163 is arranged. One set consisting of a heater and a magnetic valve is controlled based on output signals from a plurality of temperature sensors, based on the priorities set for the temperature sensors. As stated above, by setting priorities for the temperature sensors, the temperature of a target provided with a temperature sensor given a higher priority is settled within a control range by performing quick ON/OFF control, and then the temperature of a target provided with a temperature sensor given a lower priority is settled within the control range.

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Номер записи: 94

14-06-2012 дата публикации

Passive air-fuel mixing prechamber

Номер: US20120144832A1

Автор: Fengfeng Tao, Giridhar Jothiprasad, Grover Andrew Bennett, John Thomas Herbon, Matthew Patrick Boespflug

Принадлежит: General Electric Co

A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range.

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Номер записи: 95

14-06-2012 дата публикации

Gas turbine engine and cooling system

Номер: US20120144843A1

Автор: Eric Sean Donovan, Steven Wesley Tomlinson, William Daniel Feltz

Принадлежит: Rolls Royce North American Technologies Inc

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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Номер записи: 96

14-06-2012 дата публикации

Annulus filler

Номер: US20120148388A1

Автор: Kristofer J. Bottome

Принадлежит: Rolls Royce PLC

An annulus filler for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion including a lid which has a leading edge, a trailing edge and opposing side edges which connect respective ends of the leading and trailing edges. The lid defines an airflow surface for air being drawn through the engine. The annulus filler further has one or more attachment formations which, in use, connect the body portion to the rotor disc. The lid is configured such that the stiffness of the lid under compressive loading exerted on the opposing side edges by sideways blade movement is greater at the leading edge than at the trailing edge.

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Номер записи: 97

14-06-2012 дата публикации

Method of fabricating a component using a two-layer structural coating

Номер: US20120148769A1

Автор: Don Mark Lipkin, Ronald Scott Bunker

Принадлежит: General Electric Co

A method of fabricating a component is provided. The fabrication method includes depositing a first layer of a structural coating on an outer surface of a substrate. The substrate has at least one hollow interior space. The fabrication method further includes machining the substrate through the first layer of the structural coating, to define one or more openings in the first layer of the structural coating and to form respective one or more grooves in the outer surface of the substrate. Each groove has a respective base and extends at least partially along the surface of the substrate. The fabrication method further includes depositing a second layer of the structural coating over the first layer of the structural coating and over the groove(s), such that the groove(s) and the second layer of the structural coating together define one or more channels for cooling the component. A component is also disclosed.

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Номер записи: 98

14-06-2012 дата публикации

Gas turbine engine control using acoustic pyrometry

Номер: US20120150413A1

Автор: Richard H. Bunce, Upul P. Desilva

Принадлежит: Individual

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

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Номер записи: 99

21-06-2012 дата публикации

Hot gas path component cooling for hybrid pulse detonation combustion systems

Номер: US20120151896A1

Автор: Adam Rasheed, Brian Gene Brzek, Douglas Carl Hofer, Fuhua Ma, Narendra Digamber Joshi, Thomas Michael Lavertu, Venkat Eswarlu Tangirala

Принадлежит: General Electric Co

The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.

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Номер записи: 100