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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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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: 1
16-04-2019 дата публикации

Конструкция крепления рычага поворотной лопатки направляющего аппарата компрессора турбомашины

Номер: RU0000188554U1
Автор: Алексей Васильевич Пестов, Николай Николаевич Шумягин, Олег Григорьевич Миллер, Юрий Александрович Крючков
Принадлежит: Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК")

Полезная модель относится к области авиадвигателестроения и ГТУ наземного применения, а именно к компрессорам высокого давления двухконтурных турбореактивных двигателей, преимущественно с большой степенью двухконтурности.Конструкция крепления рычага поворотной лопатки направляющего аппарата компрессора турбомашины, включающей рычаг, один конец которого закреплен на цапфе лопатки, а второй связан с синхронизирующим кольцом, причем рычаг установлен на цапфе поворотной лопатки по лыскам с поджатием крепежным элементом, причем между частью рычага и наружной поверхностью цапфы лопатки имеется зазор. Дополнительно на цапфе установлена втулка, при этом рычаг, втулка и цапфа поджаты крепежным элементом. Благодаря такой конструкции повышается технологичность конструкции за счет ремонтопригодности и обеспечения замены соединительных элементов без разборки синхронизирующего кольца. 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 188 554 U1 (51) МПК F01D 17/16 (2006.01) F04D 29/56 (2006.01) F01D 9/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F01D 17/162 (2019.02); F04D 29/563 (2019.02); F01D 9/02 (2019.02) (21) (22) Заявка: 2018139943, 29.08.2017 (24) Дата начала отсчета срока действия патента: 29.08.2017 16.04.2019 Приоритет(ы): (22) Дата подачи заявки: 29.08.2017 (45) Опубликовано: 16.04.2019 Бюл. № 11 (56) Список документов, цитированных в отчете о поиске: US 5024580 A, 18.06.1991. US 2003/ (54) КОНСТРУКЦИЯ КРЕПЛЕНИЯ РЫЧАГА ПОВОРОТНОЙ ЛОПАТКИ НАПРАВЛЯЮЩЕГО АППАРАТА КОМПРЕССОРА ТУРБОМАШИНЫ (57) Реферат: Полезная модель относится к области рычаг установлен на цапфе поворотной лопатки авиадвигателестроения и ГТУ наземного по лыскам с поджатием крепежным элементом, применения, а именно к компрессорам высокого причем между частью рычага и наружной давления двухконтурных турбореактивных поверхностью цапфы лопатки имеется зазор. двигателей, преимущественно с большой Дополнительно на цапфе установлена втулка, ...

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Номер записи: 2
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: 3
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: 4
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: 5
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: 6
07-06-2012 дата публикации

Valve device and a steam turbine system incorporating said valve device

Номер: US20120137688A1
Автор: Nihar Ranjan De, Prince Mittal, Yashwant Batwal
Принадлежит: SIEMENS AG

A valve device incorporating two valves is provided. For example the two valves could be a stop valve and a control valve, housed in the same side of a common casing. The proposed valve device includes an inlet port and an outlet port connected by a fluid flow channel. The valve device further includes a first valve and a second valve housed in a common casing. The first valve includes a first valve head mounted on an annular-shaped first spindle. The second valve includes a second valve head mounted on a second spindle, the second spindle extending concentrically and slidably through the annular-shaped first spindle. The first and second valves are displaceable along a common axis and operable to influence fluid flow between the inlet port and the outlet port through the flow channel.

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Номер записи: 7
05-07-2012 дата публикации

Gas turbine engine and system for modulating secondary air flow

Номер: US20120167589A1
Автор: Theodore Joseph Fritsch
Принадлежит: Rolls Royce North American Technologies Inc

One embodiment of the present invention is a unique gas turbine system having a system for modulating secondary air flow. Another embodiment is a compressor vane stage with a plenum employed in providing secondary air flow. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for secondary air flow systems. 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: 8
12-07-2012 дата публикации

Guide vane for a turbo-compressor, guide vane arrangement, turbo-compressor, motor vehicle and method

Номер: US20120177482A1
Автор: Holger Faeth, Ralf Boening
Принадлежит: Continental Automotive GmbH

A guide vane of a turbo-compressor has variable turbine geometry, in particular for a motor vehicle. The guide vane has a profile with a lower side, an upper side and a front edge. The guide vane is characterized by a nose which extends along the front edge of the vane, from the front edge of the vane to the upper side of the vane and forms a low pressure on the upper side of the vane when waste gas impacts the guide vane. A guide vane configuration, a turbo-compressor, a motor vehicle and a method for operating this type of turbo-compressor are further disclosed.

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Номер записи: 9
30-08-2012 дата публикации

Method for mounting and setting an actuator of an exhaust gas turbocharger, and an actuator intended for a charging device

Номер: US20120216534A1
Автор: Alexander Schäffner, Daniel Dobernig, Eike Werstat, Martijn De Graaff, Reinhold Gracner, Tim Lowak, Torsten Jäckel
Принадлежит: IHI Charging Systems International GmbH, MAHLE International GmbH, VOLKSWAGEN AG

A method for mounting and setting an actuator of an exhaust gas turbocharger and a suitable electric actuating device are provided. The actuating device has an axially movable actuating rod which is connected to a coupling element which for its part is connected via a pivot pin to an actuation section of a bypass valve, the actuation section being configured as a lever arm. In order to set the desired closed position of the bypass valve during a predefined actuation of the actuating device, the coupling element is first connected to the actuating rod while still being displaceable. Before the fixing, the position of the actuating device which corresponds to the closed position is set by application of the corresponding voltage to the electric actuating device. Subsequently, a prestressing force is applied to the coupling element coaxially with respect to the actuating rod via a pneumatic actuator.

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Номер записи: 10
06-09-2012 дата публикации

Gas turbine engine with low fan pressure ratio

Номер: US20120222397A1
Автор: Frederick M. Schwarz, Peter G. Smith, Stuart S. Ochs
Принадлежит: Individual

A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

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Номер записи: 11
20-09-2012 дата публикации

Turbocharger

Номер: US20120237343A1
Автор: Yoshimitsu Matsuyama
Принадлежит: IHI Corp

A variable geometry turbocharger includes a bearing housing rotatably supporting a turbine impeller; and an exhaust nozzle changing the flow rate of an exhaust gas supplied to the turbine impeller, wherein the exhaust nozzle has an exhaust inlet wall disposed at the bearing housing side, the turbocharger has a seal member exhibiting a ring shape and sealing a gap formed between the bearing housing and the exhaust inlet wall, and an inner circumferential edge of the seal member firmly contacts the bearing housing and an outer circumferential edge of the seal member firmly contacts the exhaust inlet wall.

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Номер записи: 12
06-12-2012 дата публикации

Engine for thrust or shaft output and corresponding operating method

Номер: US20120304619A1
Автор: Michael Alan Beachy Head
Принадлежит: Individual

An engine and a method of operating the engine are provided. The engine includes a gas turbine and fan that rotate together to provide an exhaust gas flow stream, which flows over a free turbine that is connected to a power take-off. The free turbine can extract energy from the exhaust gas flow stream and transfer it as shaft power to the power take-off and the amount of energy extracted by the free turbine is controlled by varying the pitch of the free turbine's blades and/or by varying the pitch or stator vanes of a stator upstream of the free turbine. The control over the amount of energy extracted by the free turbine allows the engine to be used to provide thrust from the gas turbine and fan or to provide shaft power at the power take-off, or a combination of thrust and shaft power.

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Номер записи: 13
13-12-2012 дата публикации

Waste gate valve device

Номер: US20120312010A1
Автор: Takeshi Yasoshima
Принадлежит: Mitsubishi Heavy Industries Ltd

A waste gate valve device in which a waste gate valve 100 is fully closed when a valve body of the waste gate valve 100 moves from an exhaust outlet passage 18 s side toward an exhaust bypass passage 5 side and touches a seat face 12 a of a valve seat part 12 , wherein the valve body of the waste gate valve is provided with a protrusion 2 of a prescribed height on a touching side where the valve body of the waste gate valve touches the seat face 12 a , the protrusion being configured so as to reduce an exhaust gas passage area of the exhaust gas.

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Номер записи: 14
31-01-2013 дата публикации

Method and device for adjusting an end position of a turbine for a charging device having a variable turbine geometry

Номер: US20130025275A1
Автор: Markus Deissler, Michael Baeuerle, Michael Nau
Принадлежит: ROBERT BOSCH GMBH

In a method for adjusting an end position of guide vanes in a turbine of a charging device in an engine system, the guide vanes are adjusted with the aid of an actuator, the end position depending on a position at a structurally determined end stop, and corresponding to a position of the guide vanes of the turbine at a predetermined gas flow rate. The actuator is activated for adjusting the guide vanes to the end position using a predetermined position value, which holds the guide vanes in the end position.

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Номер записи: 15
14-02-2013 дата публикации

Variable vane actuation system and method

Номер: US20130039735A1
Автор: Andy Eifert
Принадлежит: Rolls Royce Corp

A variable vane actuation system and method is disclosed herein. The variable vane actuation system includes a first ring member disposed for pivoting movement about a centerline axis. The first ring member is operably connected with at least one vane such that the at least one vane pivots in response to the pivoting movement of the first ring member. The variable vane actuation system also includes a first pin engaged with the first ring member. The variable vane actuation system also includes a ring moving device operably engaged with the first pin to move the first ring member about the centerline axis. The ring moving device includes at least one plate having a first slot and an actuator operable to move the at least one plate. The first pin is received in the first slot and is a cam follower to a cam defined at least in part by a surface of the first slot.

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Номер записи: 16
14-02-2013 дата публикации

Variable Stator Vane Control System

Номер: US20130039736A1
Автор: Brian Allen Rittenhouse, Daniel Richard Waugh
Принадлежит: General Electric Co

The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane.

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Номер записи: 17
21-02-2013 дата публикации

Control of load rejection

Номер: US20130043680A1
Автор: Martin Liebau, Peter Marx, Sami Hashmi
Принадлежит: Alstom Technology AG

A control system is provided for a power generating system having a gas turbine, a flue gas exhaust stage and a blow-off valve assembly. The gas turbine includes a compression stage, a combustion stage and a driveshaft. The blow-off valve assembly is configured to selectively provide fluid communication between the combustion stage and the flue gas exhaust stage. The control system includes a controller configured to output a signal causing the blow-off valve assembly to provide the fluid communication in response to a sudden de-loading of the gas turbine.

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Номер записи: 18
28-02-2013 дата публикации

Turbocharger

Номер: US20130051988A1
Автор: Leif Heidingsfelder, Thomas Ramb
Принадлежит: BorgWarner Inc

A turbocharger ( 1 ) with variable turbine geometry (VTG), having a blade bearing ring ( 6 ), which has a multiplicity of guide blades ( 7 ), and which has a stop ( 25 ) at least for adjusting the minimum throughflow through the nozzle cross sections formed by the guide blades ( 7 ), wherein the stop ( 25 ) has a fixing peg ( 32 ) on which a deformable, arched adjusting section ( 26 ) is arranged. Since the stop is formed as a deformable component which can be fixed in the guide grate, it is possible after the assembly of the guide grate to rework said stop in a simple manner in order to precisely set the required stop position, since said stop is not integrally connected to the guide grate.

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Номер записи: 19
07-03-2013 дата публикации

Limit stop device and charging unit

Номер: US20130056325A1
Автор: Volkhard Ammon
Принадлежит: Bosch Mahle Turbo Systems GmbH and Co KG

A limit stop device for limiting an adjustment path of a mobile component relative to a stationary component may include a sleeve body configured to be inserted into an opening formed in the stationary component. The sleeve body may include a retaining segment disposed in the interior of the opening. A core body may be disposed in the interior of the sleeve body and be configured to radially brace the retaining segment against an inner wall of the stationary component thereby axially fixing the sleeve body on the stationary component. A stop surface may protrude into the adjustment path of the mobile component and be configured to limit the adjustment path of the mobile component.

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Номер записи: 20
28-03-2013 дата публикации

Turbocharger variable-nozzle assembly with vane sealing arrangement

Номер: US20130078082A1
Автор: Chris Groves, Denis Jeckel, Dominique Petitjean, Emmanuel Severin, Karl-Heinz Bauer, Nicolas Morand, Philippe Arnold, Pierre Barthelet
Принадлежит: Honeywell International Inc

A variable-nozzle assembly for a turbocharger includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. A unison ring engages vane arms that are affixed to axles of the vanes, such that rotation of the unison ring causes the vanes to pivot between a closed position and an open position. The vanes have proximal ends that are adjacent a face of the nozzle ring. A vane sealing member is supported on the nozzle ring and has a portion disposed between the proximal ends of the vanes and the face of the nozzle ring. The unison ring includes cams that engage cam followers. Rotational movement of the unison ring causes the cam followers to be moved axially and thereby urge the vane sealing member against the proximal ends of the vanes.

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Номер записи: 21
04-04-2013 дата публикации

Variable vane angular position sensor

Номер: US20130084179A1
Автор: Dustin Frame, Joseph V. Mantese, Richard A. Poisson, William E. Rhoden
Принадлежит: Hamilton Sundstrand Corp

A variable vane control system for use with a gas turbine engine includes an actuator, a mechanical linkage assembly, and a vane position sensor. The gas turbine engine has a plurality of variable vanes each having an airfoil disposed in a gas flow path of the gas turbine engine. The plurality of variable vanes includes a first variable vane. The mechanical linkage assembly operably connects the actuator to at least the first variable vane. The vane position sensor is connected to one of the first variable vane or a portion of the mechanical linkage assembly proximate the first variable vane for sensing angular position of the first variable vane.

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Номер записи: 22
25-04-2013 дата публикации

Multi-fluid turbine engine

Номер: US20130097994A1
Автор: Zhiqiang Wang
Принадлежит: Wisdom Energy Technology Co Ltd

A multi-fluid turbine engine includes a turbine, a first working fluid inlet passage, and a second working fluid inlet passage. The turbine may include a first working fluid portion and a second working fluid portion. The first working fluid passage may be configured to introduce a first working fluid to the first working fluid portion to perform work on the first working fluid portion, and the second working fluid inlet passage may be configured to introduce a second working fluid to the second working fluid portion to perform work on the second working fluid portion. The first working fluid inlet passage and the second working fluid passage may be independent of each other.

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Номер записи: 23
02-05-2013 дата публикации

Axial-flow fluid machinery, and variable vane drive device thereof

Номер: US20130108415A1
Автор: Kenichi Arase, Shinya Hashimoto, Takuro Kameda
Принадлежит: Mitsubishi Heavy Industries Ltd

A variable vane drive device includes a movable ring disposed at an outer circumferential side of a casing of an axial-flow compressor and having an annular shape, four ring support mechanisms disposed at intervals in a circumferential direction of the movable ring and rotatably supporting the movable ring around a rotor, and a link mechanism for connecting the movable ring to a variable vane such that a direction of the variable vane is varied by rotation of the movable ring. The ring support mechanisms have inner rollers, outer rollers, and roller support bases for rotatably supporting the inner rollers and the outer rollers in a state in which the movable ring is sandwiched between the inner roller and the outer rollers.

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Номер записи: 24
23-05-2013 дата публикации

DEVICE FOR CONTROLLING PIVOTABLE VANES OF A TURBO-MACHINE

Номер: US20130129487A1
Автор: Colette Christophe, Lalanne Bernard
Принадлежит: TURBOMECA

A control device for controlling pivotable vanes of a turbo-machine, including: a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; and a control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links; wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with other links being connected to the ring portion via respective sliding pivot connections. 16-. (canceled)7. A control device for controlling pivotable vanes of a turbo-machine , comprising:a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; anda control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links;wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with each of other links being connected to the ring portion via respective sliding pivot connections.8. A control device according to claim 7 , wherein the two ball-joint connections are spaced apart in azimuth by about 90°.9. A control device according to claim 7 , wherein the two of the links connected to the ring portion via a respective ball-joint connection are rigid claim 7 , while the other links connected to the ring portion via respective sliding pivot connections are more flexible so as to be capable of deforming elastically.10. A control device according to claim 9 , wherein the more flexible links are elastically deformable in torsion ...

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Номер записи: 25
30-05-2013 дата публикации

Method for monitoring the clearance of a kinematic link between a control member and a receiving member

Номер: US20130136575A1
Автор: Hichem Belghagi, Nicolas Potel
Принадлежит: SNECMA SAS

The method consists, based on an operating parameter of the turbojet engine, in: displacing said control member ( 11 ) in a direction as far as a first position (P 1 ) for which the receiving members ( 5 ) are rotated so as to take up the clearance of the kinematic link ( 12 ), then displacing said control member in the direction opposing the previous direction, as far as a second position (P 2 ) when a variation of the selected operating parameter is observed, and in ascertaining the travel of the control member ( 11 ) between the two positions corresponding to the total clearance of the kinematic link ( 12 ), and comparing the ascertained value of said travel of the control member with a predetermined limit value and, if it is observed that the ascertained value of the travel of the control member is greater than said limit value, to carry out monitoring of the kinematic link ( 12 ).

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Номер записи: 26
30-05-2013 дата публикации

VARIABLE TURBINE GEOMETRY

Номер: US20130136581A1
Автор: Ammon Volkhard
Принадлежит: Bosch Mahle Turbo Systems GmbH & Co. KG

A variable turbine geometry may have guide blades rotatably mounted in a blade bearing ring. An adjusting ring may be arranged on the bearing ring and an actuator may be configured to adjust the adjusting ring via a link lever. An adjustable eccentric may be arranged on the link lever and guided in a groove arranged on the blade bearing ring. The eccentric may be configured to stop on at least one end of the groove to limit at least one minimal flow through the variable turbine geometry. 1. A variable turbine geometry , comprising: guide blades rotatably mounted in a blade bearing ring , an adjusting ring arranged on the bearing ring an actuator configured to adjust the adjusting ring via a link lever ,an adjustable eccentric arranged on the link lever and guided in a groove arranged on the blade bearing ring,wherein the eccentric is configured to stop on at least one end of the groove to limit at least one minimal flow through the variable turbine geometry.2. The variable turbine geometry according to claim 1 , wherein the eccentric is designed as an axial extension on a link lever head claim 1 , and wherein the link lever head is configured to interact with the adjusting ring.3. The variable turbine geometry according to claim 1 , wherein the groove on the blade bearing ring is open towards a face end and to the outside of the bearing ring.4. The variable turbine geometry according to claim 2 , wherein the eccentric is at least one of caulked claim 2 , riveted and spread to the link lever head.5. The variable turbine geometry according to claim 1 ,wherein the eccentric comprises includes a sleeve body, which can be inserted into an opening formed in the link lever head, and a holding portion of the sleeve body is arranged in the interior of the opening,wherein a core body is arranged in the interior of the sleeve body to radially brace the holding portion in the opening and fix the eccentric on the link lever head at least one of axially and rotationally.6. The ...

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Номер записи: 27
06-06-2013 дата публикации

Method of positioning a control surface to reduce hysteresis

Номер: US20130142620A1
Автор: Jonathan Michael Moore, Simon Kenneth Haydn-Smith
Принадлежит: Rolls Royce PLC

A method of determining the actual position of a control surface ( 27 ). The method comprises receiving a signal ( 34 ) representative of a required position of the control surface ( 27 ), repositioning the control surface ( 27 ) in response to the signal ( 34 ) by moving an actuator ( 26 ), measuring a secondary position indicator, calculating the actual position of the control surface ( 27 ) on the basis of the secondary position indicator and, comparing the actual position with the required position.

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Номер записи: 28
13-06-2013 дата публикации

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

Номер: US20130145745A1
Автор: Frederick M. Schwarz, Gregory A. Kohlenberg, Sean P. Zamora
Принадлежит: Individual

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

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Номер записи: 29
13-06-2013 дата публикации

Turbomachinery Having Self-Articulating Blades, Shutter Valve, Partial-Admission Shutters, and/or Variable-Pitch Inlet Nozzles

Номер: US20130145753A1
Автор: Becker Frederick E., DiBella Francis A., Fairman Kevin D., Gofer Alexander
Принадлежит: CONCEPTS ETI, INC.

An axial-flow turbine assembly that includes one or more features for enhancing the efficiency of the turbine's operation. In one embodiment, the turbine assembly includes a turbine rotor having blades that adjust their pitch angle in direct response to working fluid pressure on the blades themselves or other part(s) of the rotor. In other embodiments, the turbine assembly is deployable in an application, such as an oscillating water column system, in which the flow of working fluid varies over time, for example, as pressure driving the flow changes. In a first of these embodiments, the turbine assembly includes a valve that allows the pressure to build so that the flow is optimized for the turbine's operating parameters. In a second of these embodiments, one or more variable-admission nozzle and shutter assemblies are provided to control the flow through the turbine to optimize the flow relative to the turbine's operating parameters. 1. A turbomachine , comprising: a blade support designed and configured to rotate about said rotational axis; and', a blade having a leading edge and a pivot axis extending substantially parallel to said leading edge; and', 'an articulation mechanism engaged with said blade in a manner that controls pivoting of said blade about said pivot axis in response to changes in pressure of the working fluid., 'a plurality of self-articulating-blade assemblies engaged with said blade support and each including], 'a turbine comprising a rotor having a rotational axis and designed and configured to be driven by a working fluid, said turbine comprising a rotor that includes2. A turbomachine according to claim 1 , wherein said articulation mechanism is designed and configured to directly respond to pressure of the working fluid on said blade.3. A turbomachine according to claim 2 , wherein said articulation mechanism includes a rotation biaser designed and configured to:bias rotation of said blade about said pivot axis to a base position; andpermit ...

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Номер записи: 30
11-07-2013 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20130177403A1
Автор: Olmstead James Charles
Принадлежит: Cummins Ltd.

A variable geometry turbine comprise a housing; a turbine wheel supported in the housing for rotation about a turbine axis: and an annular inlet passage upstream of said turbine wheel defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud. The nozzle ring and shroud are axially movable relative to one another to vary the size of the inlet passage; the nozzle ring having a circumferential array of inlet vanes extending across the inlet passage. The shroud covers the opening of a shroud cavity and defines a circumferential array of vane slots, each vane slot corresponding to an inlet vane, the vane slots and shroud cavity being configured to receive said inlet vanes to accommodate axial movement of the nozzle ring. At least one vane slot has a first side corresponding to a first side of the corresponding inlet vane and a second side corresponding to a second side of the corresponding inlet vane, the first side of the vane slot being located a shorter radial distance from the turbine wheel than the second side of the vane slot. The at least one vane slot has a leading end corresponding to a leading end of a corresponding inlet vane, and a trailing end downstream of the leading end, the trailing end corresponding to a trailing end of the inlet vane. A vane chord extends in a straight line between the a leading end tip and a trailing end tip of the inlet vane. The at least one vane slot has an increased clearance portion, the clearance between a portion of the at least one vane slot, which forms part of the increased clearance portion, and an adjacent portion of the inlet vane being greater than the clearance between a further portion of the at least one vane slot, which does not form part of the increased clearance portion, and an adjacent portion of the inlet vane. The increased clearance portion is located at the second side of the vane slot and extending from a trailing end tip of the trailing end of the vane slot to a ...

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Номер записи: 31
25-07-2013 дата публикации

Actuator

Номер: US20130186080A1
Автор: Kazuhito Kawamura, Masaki Hata, Toshinari Nishimura
Принадлежит: Mitsubishi Heavy Industries Ltd

An actuator related to the present invention includes a cylinder that has a tubular shape and is filled with a fluid; a piston that divides the inside of the cylinder into a first chamber and a second chamber in an axial direction of the cylinder, is reciprocable inside the cylinder, and opens and closes a main valve; a fluid supplying device for supplying the fluid to the second chamber; biasing device for biasing the piston in the axial direction toward the second chamber; a flow passage that communicates between the first chamber and the second chamber; and a pilot valve that cuts off the flow passage communicating between the first chamber and the second chamber.

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Номер записи: 32
08-08-2013 дата публикации

Wastegate valve

Номер: US20130199175A1
Автор: Isao Tomita, Noriyuki Hayashi, Takao Yokoyama, Toru Hoshi
Принадлежит: Mitsubishi Heavy Industries Ltd

In a wastegate valve which is provided in the bypass path bypassing the turbine of the turbocharger in the exhaust gas path and which opens and closes the bypass path, the wastegate valve is provided with a valve seat which is formed in a plane perpendicular to or tilted with an inclination angle with respect to an axial direction of the bypass path, and a valving element which is pivotable around a pivot point which has a relationship of 0°<β<90° with respect to the plane including the valve seat where β is an inclination angle, the valving element being moved away from or closer to the valve seat by pivotation of the valving element to open or close the valve.

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Номер записи: 33
08-08-2013 дата публикации

METHODS AND APPARATUS FOR DEPLOYABLE SWIRL VANES

Номер: US20130202404A1
Автор: Shah Parthiv N.
Принадлежит: ATA ENGINEERING, INC.

An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream. 1. An aircraft control structure comprising:a nozzle structure configured to exhaust a swirling fluid stream, the nozzle structure having an inner surface;a plurality of swirl vanes positioned within the nozzle structure; andan actuation subsystem configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state;wherein, while in the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure; andwherein, while in the deployed state, the plurality of swirl vanes produce the swirling fluid stream.2. The aircraft control structure of claim 1 , wherein the plurality of swirl vanes are deployed to assist in drag management of an aircraft.3. The aircraft control structure of claim 1 , wherein the nozzle structure is part of a bypass nozzle of a turbofan engine.4. The aircraft control structure of claim 1 , further including an inner nozzle structure claim 1 , and wherein claim 1 , while in the deployed state claim 1 , the plurality of swirl vanes make contact with the inner nozzle structure.5. The aircraft control structure of claim 1 , wherein the plurality of swirl vanes are hingedly coupled to the nozzle structure at a non-zero angle with respect to the centerline of the nozzle structure.6. The aircraft control structure of claim 1 , wherein the nozzle structure includes a plurality of recesses configured to respectively accept the ...

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Номер записи: 34
22-08-2013 дата публикации

Compressor

Номер: US20130216359A1
Автор: Achim Schirrmacher, Bernward Mertens, Daniel Ecke, Frank Mildner, Hubertus Michael Wigger, Markus Hofmann, Markus Paus, Thomas Brandenburg, Torsten Matthias, Uwe Sieber, Vadim Shevchenko
Принадлежит: SIEMENS AG

An axial compressor is provided. The compressor has an annular flow channel, in which adjustable blades of a blade ring that extend through the flow channel are rotatably mounted. Each blade has a lug on the rotor-side of the vane for mounting an inner ring. In order to provide a wear-free, self-centering inner ring, the ring is designed as a split ring with two opposing ends and a spring element for spreading the split ring.

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Номер записи: 35
22-08-2013 дата публикации

Vane assembly for a gas turbine engine

Номер: US20130216361A1
Автор: Tracy A. Propheter-Hinckley
Принадлежит: Individual

A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform.

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Номер записи: 36
29-08-2013 дата публикации

Variable area turbine

Номер: US20130223974A1
Автор: Daniel Bernard Kupratis, Frederick M. Schwarz
Принадлежит: Individual

A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

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Номер записи: 37
24-10-2013 дата публикации

Gas turbine inlet system and method

Номер: US20130276458A1
Автор: Michael Corey Mullen, Rex Allen Morgan
Принадлежит: General Electric Co

A gas turbomachine inlet system includes a duct member having an inlet portion fluidically coupled to an outlet portion through an intermediate portion. The inlet portion, outlet portion, and intermediate portion define a fluid flow zone. A throttling system is arranged in the duct member at one of the inlet portion, outlet portion and intermediate portion. The throttling system is configured and disposed to selectively establish a pressure drop through the fluid flow zone. A method of controlling inlet pressure drop through an inlet system for a gas turbomachine is also described herein.

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Номер записи: 38
07-11-2013 дата публикации

Jet Engine With Deflector

Номер: US20130294894A1
Автор: Kline Michael J.
Принадлежит:

A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

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Номер записи: 39
07-11-2013 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20130294895A1
Автор: Ebisu Motoki, Suzuki Hiroshi, Yokoyama Takao, YOSHIDA Toyotaka
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position.

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Номер записи: 40
14-11-2013 дата публикации

Inner turbine shell axial movement

Номер: US20130302147A1
Автор: Kenneth Black, Pradeep GHUTE, Rohit Pruthi, Sanjay Shankar Jadhav
Принадлежит: General Electric Co

A clearance control system for a turbine having a stator assembly and a rotor assembly includes a hydraulic or pneumatic controller that axially drives, through a shaft, one or more actuators connected to the stator assembly casing. The controller causes relative movement between the stator and rotor assemblies to adjust the clearances between portions of the stator and rotor in accordance with the varying operating conditions of the turbine. More particularly, the controller moves the stator relative to the rotor in first and second axial directions to compensate for thermal expansion and contraction during the operating conditions of the turbine.

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Номер записи: 41
14-11-2013 дата публикации

Turbine Exhaust Housing

Номер: US20130302185A1
Автор: Arnaud Gerard, Aurelien Tingaud, Mohan Rao JAVVADI, Shankar Pandurangasa SOLANKI
Принадлежит: Honeywell International Inc

A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall at an obtuse angle where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

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Номер записи: 42
05-12-2013 дата публикации

Protecting operating margin of a gas turbine engine

Номер: US20130319009A1
Автор: Wayne P. PARENTE
Принадлежит: Individual

A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject to a control parameter. The control parameter is selectively modified in response to the aerodynamic distortion.

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Номер записи: 43
05-12-2013 дата публикации

Cast superalloy pressure containment vessel

Номер: US20130323522A1
Автор: Daniel Frederick Purdy, Robin Carl Schwant
Принадлежит: General Electric Co

A large volume, cast superalloy pressure containment vessel is disclosed. The vessel includes a hollow body portion having a volume of at least about 4 cubic feet and a substantially porosity-free cast microstructure. The containment vessel configured for operation at an operating temperature of at least about 1,200° F. and an operating pressure of at least about 1,500 psi. A large volume, cast superalloy article is also disclosed. The article has a volume of at least about 4 cubic feet and a substantially porosity-free cast microstructure, the article configured for operation at an operating temperature of at least about 1,400° F.

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Номер записи: 44
12-12-2013 дата публикации

INSERT ELEMENT FOR A TURBINE OF AN EXHAUST GAS TURBOCHERGER, EXHAUST GAS TURBOCHARGER AND TURBINE FOR AN EXHAUST GAS TURBOCHARGER

Номер: US20130330178A1
Автор: Hirth Torsten, SCHAAL Benjamin, SUMSER Siegfried
Принадлежит: DAIMLER AG

In a turbine of an exhaust gas turbocharger an insert element which is provided for insertion into a turbine housing has a spiral port which extends in the circumferential direction of the insert element over at least part of the circumference thereof and by which the exhaust gas flow through the turbine is controlled. The insert element is open in the axial direction on at least at one end face thereof which end face is biased in sealing contact with the turbine housing. The insert element has a central axial opening with a spiral port for accommodating a turbine wheel. 1363636363636361210101010101010101214384042444836363636363636122049828420. An insert element ( , , , , , , ) for a turbine () of an exhaust gas turbocharger ( , , , , , , , ) , the turbine () including a housing () into which the insert element can be inserted , the insert element being provided with at least one spiral port ( , , , ) which extends in the circumferential direction () of the insert element ( , , , , , , ) over at least part of the circumference thereof and by which exhaust gas flowing through the turbine () is directed onto a turbine wheel () , the insert element being open in the axial direction () at least one end face ( , ) thereof for accommodating the turbine wheel ():236363636363636363636363636363840424448363636363636361220. The insert element ( claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , ) according to claim 1 , wherein the insert element ( claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , ) has at least one further spiral port ( claim 1 , claim 1 , claim 1 , ) which extends in the circumferential direction () of the insert element ( claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , ) over at least part of the circumference thereof and by which exhaust gas flowing through the turbine () is directed to the turbine wheel ().336363636363636384042444836363636363636. The insert element ( claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , claim 1 , ...

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Номер записи: 45
26-12-2013 дата публикации

Exhaust-gas turbocharger having a water-cooled turbine housing with an integrated electric wastegate actuator

Номер: US20130340426A1
Автор: Marc Hiller, Mathias Bogner, Ralf Böning, Ralph-Maurice KÖMPEL, Roland Herfurth
Принадлежит: Continental Automotive GmbH

An exhaust-gas turbocharger includes a turbine housing and a wastegate which is disposed in the turbine housing. The turbine housing is water-cooled. An electric wastegate actuator is an integrated constituent part of the turbine housing.

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Номер записи: 46
26-12-2013 дата публикации

Four bar drive mechanism for bleed system

Номер: US20130341547A1
Автор: Kevin J. Cummings, Ryan Edward LeBlanc
Принадлежит: Individual

An actuation system for a bleed valve includes first and second bell cranks connected by a connecting link. The first bell crank has a first arm that is coupled to a bleed valve and a second arm that is coupled to the connecting link. The connecting link has a first end coupled to the second arm of the first bell crank and a second end coupled to a first arm of the second bell crank. A second arm of the second bell crank is coupled to an actuating element. Input is communicated through the actuating element to move the bleed valve between open and closed positions via the first and second bell cranks.

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Номер записи: 47
26-12-2013 дата публикации

Turbine engine variable area vane

Номер: US20130343873A1
Автор: Brandon W. Spangler, Tracy A. Propheter-Hinckley
Принадлежит: United Technologies Corp

A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.

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Номер записи: 48
26-12-2013 дата публикации

Spherical-link end damper system with near constant engagement

Номер: US20130343876A1
Автор: Kevin J. Cummings, Ryan Edward LeBlanc
Принадлежит: United Technologies Corp

A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

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Номер записи: 49
02-01-2014 дата публикации

NON-LINEAR ASYMMETRIC VARIABLE GUIDE VANE SCHEDULE

Номер: US20140003909A1
Автор: Maier Mark Stefan, Wassynger Stephen Paul
Принадлежит: GENERAL ELECTRIC COMPANY

A variable inlet guide vane arrangement for a compressor includes a case defining an inlet of the compressor; at least one vane support coaxially disposed within the case; a plurality of vanes circumferentially disposed around the circumference of the case, each vane being pivotally mounted between the case and the at least one vane support; an actuator mechanism configured to pivot at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. A method of controlling a variable inlet guide vane arrangement for a compressor includes pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. 1. A method of controlling a variable inlet guide vane arrangement for a compressor comprising a case defining an inlet of the compressor , at least one vane support coaxially disposed within the case , a plurality of vanes circumferentially disposed around the circumference of the case , each vane being pivotally mounted between the case and the at least one vane support , and an actuator mechanism configured to pivot at least some of the plurality of vanes , the method comprising:pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case.2. A method according to claim 1 , wherein pivoting the vanes in an asymmetrical pattern comprises pivoting at least some of the plurality of vanes according to a non-linear schedule or alternating linear schedules during a portion of pivoting of the plurality of vanes from a fully closed to a fully open position.3. A method according to claim 2 , wherein at least some of the plurality of vanes are pivoted according to the non-linear schedule or alternating linear schedules at an onset of separation of a flow from said at least some of the plurality of vanes.4. A method according to claim 3 , further comprising pivoting at least some of the plurality of vanes according to a linear schedule to ...

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Номер записи: 50
09-01-2014 дата публикации

Turbomachine with variable-pitch vortex generator

Номер: US20140010638A1
Автор: Agnes Claire Marie Pesteil, Vincent Paul Gabriel Perrot
Принадлежит: SNECMA SAS

The present invention relates to a turbomachine comprising at least one bladed disk, be it mobile or static, and vortex generators ( 17 ) positioned upstream of the blading ( 1 ) of said disk, wherein the vortex generators ( 17 ) are of variable pitch.

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Номер записи: 51
20-02-2014 дата публикации

Turbine for an exhaust gas turbocharger

Номер: US20140050568A1
Автор: Nils Brinkert, Siegfried Sumser
Принадлежит: DAIMLER AG

In a turbine for an exhaust gas turbocharger having a turbine housing including a turbine wheel with blades, each having a leading edge and a trailing edge, an adjusting device is provided controlling the flow to the leading blade edges of the turbine wheel and also a device for controlling the flow from the trailing edges of the turbine wheel blades, both devices are coupled to one another so as to be adjustable by a single actuator.

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Номер записи: 52
06-03-2014 дата публикации

Method, apparatus and system for controlling swirl of exhaust in a gas turbine

Номер: US20140060062A1
Автор: Mahendhra Muthuramalingam, Nachiket Chilhatey, Thangaraj Subbareddyar
Принадлежит: General Electric Co

Change in swirl of gas turbine exhaust gases at off-design conditions is a key driver of exhaust diffuser inefficiency that adversely impact the gas turbine performance. Conventional ways to control swirl such as blowing, suction, and vortex generation are undesirable since they require parasitic power, are complex to design, and dilute the exhaust gas energy. To address such short comings, shape memory devices are incorporated into struts of an exhaust diffuser of a gas turbine. The shape memory devices change shape in accordance with heat, which can be applied through memory device heaters. By controlling the memory device heaters, the heat applied to the shape memory devices can be controlled. The shapes of the struts can be altered through altering the shapes of the memory device in consideration of load conditions to increase the efficiency.

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Номер записи: 53
06-03-2014 дата публикации

Drive lever arrangement

Номер: US20140064875A1
Автор: Philip Twell
Принадлежит: SIEMENS AG

A drive lever arrangement is provided. The drive lever arrangement includes a unison ring which has a groove; a drive lever having connection means for connecting the drive lever to the unison ring; a drive lever pin having a transversal throughbore hole; and a clip, wherein the drive lever pin connects the drive lever to the unison ring, and wherein the clip is inserted in the groove through the throughbore hole of the drive lever pin, and engages with the groove of the unison ring.

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Номер записи: 54
06-03-2014 дата публикации

Device and system for harvesting the energy of a fluid stream

Номер: US20140064918A1
Автор: Allan Hurup, Claus Burchardt
Принадлежит: COMPOENERGY APS

Device for harvesting the energy of a fluid stream comprising a turbine with a rotation axis at right-angle to the fluid stream, the turbine comprising a plurality of blades that during its rotation sweeps an annular area around the rotation axis which has an inner and outer perimeter with a first and second radial distance to the rotation axis, and first and second fluid guide located opposite each other, with the plurality of blades arranged for rotation there between and arranged for guiding the fluid stream towards the at least one blade, wherein the first and second fluid guide are formed each with a guide foil section having a suction side, a pressure side and a guide foil incidence angle, wherein each fluid guide is arranged such that the suction sides of the guide foil sections are facing each other, wherein an open central area around the rotation axis is provided.

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Номер записи: 55
13-03-2014 дата публикации

TURBINE WASTEGATE

Номер: US20140072411A1
Автор: Gonzalez Manuel, Marques Manuel, Toussaint Lionel
Принадлежит: HONEYWELL INTERNATIONAL INC.

An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing configured for receipt by the bore; a rotatable wastegate shaft configured for receipt by the bushing; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug includes a profile, defined in part by a portion of a torus, for contacting the wastegate seat to cover the wastegate passage and, for example, defined in part by a portion of a modified sphere or a portion of a cone. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. 1. An assembly comprising:a turbine housing that comprises a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat;a bushing configured for receipt by the bore;a rotatable wastegate shaft configured for receipt by the bushing;a wastegate arm extending from the wastegate shaft; anda wastegate plug extending from the wastegate arm wherein the wastegate plug comprises a profile, defined in part by a portion of a torus, for contacting the wastegate seat to cover the wastegate passage in a closed state, and defined in part by a portion of a modified sphere, for defining a clearance with respect to the wastegate seat in an open state.2. The assembly of wherein the wastegate shaft claim 1 , the wastegate arm and the wastegate plug comprise a unitary component.3. The assembly of wherein the portion of the modified sphere comprises a cross-section defined at least in part by a portion of an ellipse.4. The assembly of wherein the cross-section is defined at least in part by a portion of a circle.5. The assembly of wherein the wastegate plug comprises a shaft side and a front side and wherein the cross-section is defined by the portion of the ellipse over a span that includes the wastegate shaft side of the wastegate plug and defined by the portion of the circle over a ...

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Номер записи: 56
13-03-2014 дата публикации

TURBINE WASTEGATE

Номер: US20140072412A1
Автор: Alves Jose, Laissus Jean-Jacques, Marques Manuel
Принадлежит:

An assembly can include a turbine housing that includes a bore, a wastegate seat and two wastegate passages that extend to the wastegate seat; a rotatable wastegate shaft configured for receipt by the bore; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug comprises a profile defined in part by a portion of a torus, for contacting the wastegate seat in a closed state, and defined in part by two plug portions, for defining clearances with respect to the wastegate seat in an open state. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. 1. An assembly comprising:a turbine housing that comprises a bore, a wastegate seat and two wastegate passages that extend to the wastegate seat;a rotatable wastegate shaft configured for receipt by the bore;a wastegate arm extending from the wastegate shaft; anda wastegate plug extending from the wastegate arm wherein the wastegate plug comprises a profile defined in part by a portion of a torus, for contacting the wastegate seat in a closed state, and defined in part by two plug portions, for defining clearances with respect to the wastegate seat in an open state.2. The assembly of wherein at least the wastegate arm and the wastegate plug comprise a unitary component.3. The assembly of wherein each of the two plug portions comprises a surface defined at least in part by a portion of a spherical lune.4. The assembly of wherein each of the two plug portions comprises a shape defined at least in part by a portion of a spherical wedge.5. The assembly of wherein the turbine housing comprises a divider wall disposed between the two wastegate passages.6. The assembly of wherein the wastegate plug comprises a gap between the two plug portions that accommodates the divider wall in the closed state.7. The assembly of wherein the divider wall is approximately orthogonal to a rotational axis of the wastegate shaft.8. The ...

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Номер записи: 57
13-03-2014 дата публикации

GAS TURBINE ENGINE SYNCHRONIZING RING WITH MULTI-AXIS JOINT

Номер: US20140072413A1
Автор: Do Logan H.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

An assembly includes a synchronizing ring, a vane arm, and a multi-axis joint. The multi-axis joint connects the synchronizing ring to the vane arm and provides the vane arm with movement about a first pivot axis and a second pivot axis. 1. An assembly comprising:a synchronizing ring;a vane arm; anda multi-axis joint connecting the synchronizing ring to the vane arm, the multi-axis joint providing the vane arm with movement about a first pivot axis and a second pivot axis.2. The assembly of claim 1 , wherein the multi-axis joint has a first trunnion that is held within the synchronizing ring by a cover plate.3. The assembly of claim 2 , wherein the cover plate is retained to the synchronizing ring by at least one of a fastener and/or grooves.4. The assembly of claim 1 , wherein the synchronizing ring has an I-beam cross-sectional shape.5. The assembly of claim 1 , wherein the multi-axis pivot joint has a first trunnion and a second trunnion claim 1 , and wherein the synchronizing ring is movable about an axis claim 1 , the first trunnion rotates about the first pivot axis claim 1 , and the second trunnion rotates about the second pivot axis.6. The assembly of claim 1 , wherein the multi-axis joint has a second trunnion that comprises a pin claim 1 , and wherein the first trunnion has a hole that receives the pin therein.7. The assembly of claim 1 , wherein the multi-axis joint has a first trunnion that defines the first pivot axis and a second trunnion that defines the second pivot axis claim 1 , and wherein the first pivot axis intersects with the second pivot axis.8. The assembly of claim 7 , wherein the first pivot axis is perpendicular to the second pivot axis.9. A kit comprising:a synchronizing ring;a vane arm; anda multi-axis joint adapted to be disposed in and extend from the synchronizing ring to connect the vane arm to the synchronizing ring.10. The kit of claim 9 , further comprising a cover plate adapted to hold the multi-axis joint within the ...

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Номер записи: 58
10-04-2014 дата публикации

TURBINE FOR AN EXHAUST GAS TURBOCHARGER

Номер: US20140099191A1
Автор: KOTZBACHER Thorben
Принадлежит: IHI Charging Systems International GmbH

In a turbine for exhaust gas turbocharger of a combustion engine with a turbine casing forming an installation space in which a turbine wheel is arranged so as to be rotatable about an axis of rotation and into which exhaust gas of the combustion engine may be supplied via at least one flow duct in which a guide vane structure is arranged, the guide vane structure includes vanes, which are pivotably supported relative to the turbine casing and form an axial inlet nozzle structure adjacent a wall portion of the turbine which extends along the guide vane structure, the wall portion comprising at least a first guide wall area which overlaps the guide vane structure, and which is set back relative to a second guide wall area in which the vanes are pivotably supported and which adjoins the first wall area. 1141820182238207238147218701272708072827080. A turbine for an exhaust gas turbocharger of a combustion engine , comprising a turbine casing () including an installation space () , a turbine wheel () arranged in the installation space () so as to be rotatable about an axis of rotation () at least one inlet flow duct () via which exhaust gas of the combustion engine may be supplied to the turbine wheel () , a guide vane structure () arranged in the inlet flow duct () and including vanes which are pivotably supported relative to the turbine casing () , the vane structure () being delimited in the axial direction of the installation space () at least partially by at least one wall portion () of the turbine () which is at least partially overlapping the guide vane structure () , the wall portion () comprising a first wall area () which is arranged adjacent the guide vane () , and which is set back relative to a second wall area () of the wall portion () adjoining the first wall area ().2708082725212. The turbine according to claim 1 , wherein the wall portion () with the first wall area () and the second wall area () is arranged at the side of the guide vane structure () ...

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Номер записи: 59
01-01-2015 дата публикации

Method for mounting and setting an actuator of an exhaust gas turbocharger, and an actuator intended for a charging device

Номер: US20150000127A1
Автор: Alexander Schäffner, Daniel Dobernig, Eike Werstat, Jaroslav Kierat, Martijn De Graaff, Reinhold Gracner, Tim Lowak, Torsten Jäckel
Принадлежит: IHI Charging Systems International GmbH, MAHLE International GmbH, VOLKSWAGEN AG

A method for mounting and setting an actuator of an exhaust gas turbocharger and a suitable electric actuating device are provided. The actuating device has an axially movable actuating rod which is connected to a coupling element which for its part is connected via a pivot pin to an actuation section of a bypass valve, the actuation section being configured as a lever arm. In order to set the desired closed position of the bypass valve during a predefined actuation of the actuating device, the coupling element is first connected to the actuating rod while still being displaceable. Before the fixing, the position of the actuating device which corresponds to the closed position is set by application of the corresponding voltage to the electric actuating device. Subsequently, a prestressing force is applied to the coupling element coaxially with respect to the actuating rod via a pneumatic actuator.

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Номер записи: 60
01-01-2015 дата публикации

VARIABLE GEOMETRY NOZZLE AND ASSOCIATED METHOD OF OPERATION

Номер: US20150000268A1
Автор: Clancy Cathal, Loringer Daniel Edward, Michelassi Vittorio, Rodriguez Erdmenger Rodrigo
Принадлежит:

The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support. 1. A method comprising:moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across a turbine, wherein the turbine includes a nozzle having the plurality of main blades and tandem blades; wherein the plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.2. The method of claim 1 , further comprising moving at least one of the first support and the second support along a circumferential direction relative to each other.3. The method of claim 1 , further comprising moving at least one of the first support and the second support along an axial direction relative to each other.4. The method of claim 1 , further comprising varying the position of the plurality of main blades and the tandem blades relative to each other to alter an effective compound throat area of the nozzle.5. The method of claim 1 , further comprising varying a position of the plurality of main blades and the tandem blades relative to each other depending on a load of an engine coupled to the turbine.6. The method of claim 1 , wherein the flow characteristics comprises a mass flow claim 1 , power claim 1 , and a pressure ratio across the turbine.7. A nozzle comprising:a plurality of main blades coupled to a first support; anda plurality of ...

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Номер записи: 61
06-01-2022 дата публикации

Turbine and turbocharger

Номер: US20220003151A1
Автор: Shun Okamoto, Yoshiaki Hirai
Принадлежит: IHI Corp

A turbine includes: a turbine impeller accommodated in an accommodation space; two turbine scroll flow paths connected to the accommodation space; a first wastegate flow path (wastegate flow path) opened to one of the turbine scroll flow paths (second turbine scroll flow path) and separated from the other turbine scroll flow path (first turbine scroll flow path), and a valve for opening and closing the first wastegate flow path.

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Номер записи: 62
03-01-2019 дата публикации

Mixing bleed and ram air using an air cycle machine with two turbines

Номер: US20190002110A1
Автор: Harold W. Hipsky, Louis J. Bruno
Принадлежит: Hamilton Sundstrand Corp

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

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Номер записи: 63
03-01-2019 дата публикации

MIXING BLEED AND RAM AIR USING AN AIR CYCLE MACHINE WITH TWO TURBINES

Номер: US20190002111A1
Автор: Bruno Louis J., Hipsky Harold W.
Принадлежит:

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine. 1. An air cycle machine for an environmental control system for an aircraft , the air cycle machine comprising:a compressor configured to compress a first medium;a turbine configured to receive second medium;a mixing point downstream of the compressor and downstream of the turbine;a shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.2. The air cycle machine of claim 1 , further comprising the fan on a second shaft.3. The air cycle machine of claim 2 , wherein the fan is located at a first end of the second shaft.4. The air cycle machine of claim 3 , wherein a third turbine is located at a first end of the shaft.5. The air cycle machine of claim 4 , further comprising the fan located at a second end of the shaft.6. The air cycle machine of claim 3 , wherein the second turbine is configured to receive a third medium claim 3 , andwherein the third medium is cabin discharge air.7. The air cycle machine of claim 1 , wherein the first medium comprises fresh air claim 1 , andwherein the second medium comprises bleed air.8. An air conditioning system for an aircraft comprising:a compressor configured to compress a first medium;a turbine configured to receive a second medium;a mixing point downstream of the compressor and downstream of the turbine; anda shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.9. The air conditioning system of claim 8 , further comprising the fan on a second shaft.10. ...

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Номер записи: 64
05-01-2017 дата публикации

ROTOR OFF-TAKE ASSEMBLY

Номер: US20170002678A1
Автор: N. Chandrasekaran, Pattnaik Santosh Kumar, Subramanian Sesha, Sundaran Swaroop
Принадлежит:

According to exemplary embodiments, a rotor off-take assembly is provided by positioning an angled hole or aperture in a stator assembly. This angled hole provides improved pressure recovery and utilizes higher dynamic pressure to drive the bleed air flow into the off-take cavity. 1. A rotor off-take assembly for improved pressure recovery , comprising:a first rotor disk, including at least one first blade connected to the first rotor disk and extending radially outwardly;a second rotor disk, including at least one second blade connected to the second rotor disk and extending radially outwardly;an at least one stator assembly disposed between the first rotor disk and the second rotor disk;the stator assembly including a flow surface generally extending from adjacent the first rotor disk toward the second rotor disk;the stator assembly including an off-take aperture extending downwardly at a non-perpendicular angle through the flow surface;wherein air passes through the off-take aperture of the stator assembly reducing swirl.2. The rotor off-take assembly of further comprising a bleed air passage in rotor structure.3. The rotor off-take assembly for improved pressure recovery of further comprising an impeller tube disposed radially inward of the stator.4. The rotor off-take assembly for improved pressure recovery of claim 3 , wherein the impeller tube is of reduced weight due to reduced height.5. The rotor off-take assembly for improved pressure recovery of claim 4 , wherein the offtake aperture and the impeller tube arrangement results in decreased pressure drop between the off-take aperture and impeller tube.6. The rotor off-take assembly for improved pressure recovery of claim 1 , wherein the offtake aperture is circular in cross-sectional shape.7. The rotor off-take assembly for improved pressure recovery of claim 1 , wherein the offtake aperture is oval in cross-sectional shape.8. The rotor off-take assembly for improved pressure recovery of claim 1 , wherein ...

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Номер записи: 65
05-01-2017 дата публикации

ELECTRIC ACTUATOR FOR ENGINE CONTROL

Номер: US20170002679A1
Автор: Balsiger Derick S., Bloxham Keith
Принадлежит:

An electric actuator for control of an engine includes an electric motor coupled to a drive shaft that extends to align a gear interface of the electric actuator with a variable geometry adjustment interface of the engine. A position feedback shaft extends coaxially with respect to the drive shaft. The position feedback shaft is coupled to an output shaft of the gear interface at a gear interface end of the position feedback shaft. A rotational position sensor is coupled to a motor end of the position feedback shaft proximate the electric motor. The drive shaft and the position feedback shaft are sized to position an output ring gear of the output shaft in contact with the variable geometry adjustment interface within a casing of the engine and to further position the electric motor and the rotational position sensor external to the casing of the engine. 1. An electric actuator for control of an engine , the electric actuator comprising:an electric motor coupled to a drive shaft that extends to align a gear interface of the electric actuator with a variable geometry adjustment interface of the engine;a position feedback shaft that extends coaxially with respect to the drive shaft, wherein the position feedback shaft is coupled to an output shaft of the gear interface at a gear interface end of the position feedback shaft; anda rotational position sensor coupled to a motor end of the position feedback shaft proximate the electric motor, wherein the drive shaft and the position feedback shaft are sized to position an output ring gear of the output shaft in contact with the variable geometry adjustment interface within a casing of the engine and to further position the electric motor and the rotational position sensor external to the casing of the engine.2. The electric actuator according to claim 1 , further comprising a retracting mechanism configured to selectively retract the drive shaft and a portion of the gear interface to decouple the drive shaft from the ...

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Номер записи: 66
05-01-2017 дата публикации

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

Номер: US20170002680A1
Автор: HARADA Naruhito, KATAGAKE Makoto, NAGAI Naoyuki, OKAMURA Tomoaki, TONAKA Hideki
Принадлежит:

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

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Номер записи: 67
05-01-2017 дата публикации

DETECTION METHOD OF SENSOR IN GAS TURBINE

Номер: US20170002682A1
Автор: LAU Ow, Neuenhahn Thomas, REN Chao, Zheng Jie
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A detection method of a sensor in a gas turbine includes adopting a pressure sensor to measure a pushing force of a push rod; measuring a first rotational angle of a guide vane where a first angle sensor is mounted; measuring a second rotational angle of the guide vane where a second angle sensor is mounted; obtaining a maximum measured rotational angle deviation from the absolute value of a difference value between the first and second rotational angles; calculating a maximum calculated deviation from the pushing force of the push rod; calculating the absolute value of a difference value between the maximum measured deviation and the maximum calculated deviation; and determining that the angle sensors and the pressure sensor have appropriate measurement accuracy; or, if the absolute value is greater than the standard value, determining that the angle and/or pressure sensors require calibration. 1. A method for sensors in a gas turbine , the gas turbine including a cylinder , a plurality of guide vanes , a first angle sensor , a second angle sensor , and a guide vane driving mechanism configured to drive the guide vanes to rotate , the guide vane driving mechanism including a driving ring , a push rod configured to push the driving ring to rotate relative to the cylinder , a pressure sensor configured to measure a thrust of the push rod , a plurality of connecting rods and adjusting rods connecting the guide vanes and the driving ring , and a plurality of elastic support bases connecting the cylinder and the driving ring , the method comprising:measuring thrust of the push rod via the pressure sensor;measuring a first rotation angle of the guide vanes in an installation position of the first angle sensor;measuring a second rotation angle of the guide vanes in an installation position of the second angle sensor;obtaining a measured maximum rotation angle offset according to an absolute value of a difference between said measured first rotation angle and said measured ...

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Номер записи: 68
05-01-2017 дата публикации

Activation Control Apparatus

Номер: US20170002690A1
Автор: IYANAGA Norihiro, SUZUKI Fumiyuki, Yamanaka Kazunori, YASHIKI Tatsuro, Yoshida Takuya, Yoshida Yasuhiro
Принадлежит:

An object of the invention is to provide an activation control apparatus by which a steam turbine can be activated safely at a high speed in response to a state of a power generation plant. In an activation control apparatus for a power generation plant including a heat source apparatus that heats low-temperature fluid by a heat source medium to generate high-temperature fluid; steam generation equipment that generates steam by thermal exchange with the high-temperature fluid; a steam turbine that is driven by the steam; and an adjustment apparatus that adjusts a plant operation amount, the activation control apparatus comprises: a thermal effect amount prediction calculation device that calculates at least a prediction value for a thermal effect amount for use for activation control of the steam turbine; a changeover device that decides, based on a state value of the power generation plant, the sensitivity of the thermal effect amount to a variation of the plant operation amount and outputs a changeover signal for a control mode for the thermal effect amount in accordance with the sensitivity; and an adjustment device that calculates, based on the changeover signal, the plant operation amount so as not to exceed a predetermined limit value. 1. An activation control apparatus for a power generation plant including:a heat source apparatus configured to heat low-temperature fluid by a heat source medium to generate high-temperature fluid;steam generation equipment configured to generate steam by thermal exchange with the high-temperature fluid;a steam turbine configured to be driven by the steam; andan adjustment apparatus configured to adjust a plant operation amount; the activation control apparatus comprising:a thermal effect amount prediction calculation device configured to calculate a prediction value for at least one thermal effect amount to be used for activation control of the steam turbine;a changeover device configured to decide, based on a state value of ...

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Номер записи: 69
05-01-2017 дата публикации

SYSTEM AND METHODS FOR CBV DIAGNOSTICS

Номер: US20170002762A1
Автор: Banker Adam Nathan, Ossareh Hamid-Reza, Xiao Baitao
Принадлежит:

Methods and systems are provided for diagnosing compressor bypass valve degradation. In one example, a method may include indicating degradation of a compressor bypass valve coupled in a compressor bypass based on intake aircharge temperature measured upstream of a compressor inlet via an air charge temperature sensor. 1. A method for diagnosing a continuously variable compressor bypass valve of an engine , comprising:adjusting continuously variable compressor bypass valve responsive to operating conditions of the engine; andindicating degradation of a compressor bypass valve coupled in a compressor bypass based on intake aircharge temperature being different then a threshold temperature measured upstream of a compressor inlet, and changing engine operating parameters due to the indication.2. The method of claim 1 , wherein if the compressor bypass valve is stuck open claim 1 , changing engine operation includes close a wastegate valve.3. The method of claim 1 , wherein if the compressor bypass valve is stuck closed claim 1 , changing engine operation include increasing flow through the compressor.4. The method of claim 3 , wherein increasing flow through the compressor includes adjusting a throttle position.5. The method of claim 3 , wherein increasing flow through the compressor includes adjusting an exhaust gas recirculation (EGR) rate.6. The method of claim 1 , wherein the intake aircharge temperature is measured by a temperature sensor coupled at a junction of the compressor bypass and an air intake passage at the compressor inlet.7. The method of claim 1 , wherein the compressor bypass is configured to recirculate boosted aircharge from downstream of the compressor and upstream of a charge air cooler to the compressor inlet.8. The method of claim 1 , wherein the indicating includes claim 1 , during higher boost conditions claim 1 , indicating degradation of the compressor bypass valve based on intake aircharge temperature being higher than a first threshold ...

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Номер записи: 70
07-01-2016 дата публикации

NACELLE INTERNAL AND EXTERNAL FLOW CONTROL

Номер: US20160003091A1
Автор: Malecki Robert E.
Принадлежит:

A nacelle () for a gas turbine engine () that extends along an engine centerline (CO includes an inner portion (), an outer portion (), and a nacelle flow control system (). The outer portion () surrounds the inner portion () and connects to the inner portion () at a leading edge (). The nacelle flow control system () includes an internal flow control () for the inner portion () and an external flow control () for the outer portion (). 1. A nacelle for a gas turbine engine , the nacelle including an inner portion , a surrounding outer portion , and a leading edge connecting therebetween; the nacelle comprising: an internal flow control for the inner portion for modifying a first airflow, the internal flow control including a first passage for flowing air; and', 'an external flow control for the outer portion for modifying a second airflow, the external flow control including a second passage for flowing air., 'a nacelle flow control system that includes2. The nacelle of claim 1 , wherein the nacelle flow control system further comprises:a pump that provides airflow through at least one of the first and second passages of the nacelle flow control system; anda control valve connected to at least one of the first and second passages and configured to direct flow through the nacelle flow control system.3. The nacelle of claim 2 , wherein the flow control valve is connected to the first and second passages and directs flow through the internal flow control or the external flow control or to neither the internal nor the external flow controls.4. The nacelle of claim 2 , wherein the nacelle flow control system further comprises:a manifold fluidly connected to the pump and to the control valve, wherein the control valve is fluidly connected to the internal flow control; anda second control valve fluidly connected to the manifold, wherein the second control valve is fluidly connected to the external flow control.5. The nacelle of claim 2 , wherein the internal flow control ...

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Номер записи: 71
01-01-2015 дата публикации

GAS TURBINE ENGINE VANE END DEVICES

Номер: US20150003963A1
Автор: Freeman Ted J., Munson John, Taketa Linnea
Принадлежит:

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two. 1. An apparatus comprising:a moveable airfoil member structured for use in a working fluid flow path of a gas turbine engine; anda brush seal disposed at an end of the moveable airfoil member, the brush seal having a plurality of extensions projecting outwardly and configured to discourage a flow of working fluid through the extensions as the working fluid traverses the working fluid flow path.2. The apparatus of claim 1 , which further includes the gas turbine engine claim 1 , the engine including a plurality of the moveable airfoil members claim 1 , wherein each of the plurality of moveable airfoil members is a rotatable vane that includes a range of travel claim 1 , and wherein the extensions contact the wall in the range of travel.3. The apparatus of claim 1 , wherein the plurality of extensions each have a first end and a second end both disposed toward a distal side of the plurality of extensions claim 1 , the first end and second end connected via a body that is looped around a central member.4. The apparatus of claim 3 , which further includes a crimp to couple the plurality of extensions to the central member claim 3 , the central member extending along a chord of the moveable airfoil member claim 3 , and wherein the moveable airfoil member is a rotatable turbine vane.5. The apparatus of claim 1 , wherein the plurality of extensions cover a ...

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Номер записи: 72
07-01-2016 дата публикации

GAS TURBINE ENGINE INLET

Номер: US20160003145A1
Автор: Hendricks Gavin, Lord Wesley K., Miller Robert M., Qiu Yuan J.
Принадлежит:

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

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Номер записи: 73
07-01-2016 дата публикации

QUAD LAYER PASSAGE VARIABLE GEOMETRY TURBINE FOR TURBOCHARGERS IN EXHAUST GAS RECIRCULATION ENGINES

Номер: US20160003196A1
Автор: Arnold Steven Don, Daojun Yuan, Hang Wang, Wuhai Sang, Yanzhao Li
Принадлежит:

A variable geometry turbine for turbochargers in exhaust gas recirculation engines incorporates a turbine housing having an exhaust inlet with a first side receiving exhaust from cylinders having exhaust gas recirculation (EGR) and a second side receiving exhaust from non-EGR cylinders. The first side has a first EGR-driving passage and a second EGR-driving passage and the second side having a first non-EGR-driving passage and a second non-EGR-driving passage. A first control valve is associated with the second EGR-driving passage and a second control valve is associated with the second non-EGR-driving passage. A controller is adapted to control the first and second control valves. 1. A variable geometry turbine for turbochargers in exhaust gas recirculation engines comprising:a turbine housing having an exhaust inlet with a first side receiving exhaust from cylinders having exhaust gas recirculation (EGR) and a second side receiving exhaust from non-EGR cylinders, said first side having a first EGR-driving passage and a second EGR-driving passage and said second side having a first non-EGR-driving passage and a second non-EGR-driving passage;a first control valve associated with the second EGR-driving passage;a second control valve associated with the second non-EGR-driving passage; and,a controller adapted to control the first and second control valves.2. The variable geometry turbine for turbochargers in exhaust gas recirculation engines as defined in wherein the first EGR-driving passage is sized to provide a back pressure driving a predetermined maximum EGR rate.3. The variable geometry turbine for turbochargers in exhaust gas recirculation engines as defined in wherein with the first control valve in a hilly opened position the second EGR-driving passage is sized in combination with the first EGR-driving passage to provide a second back pressure driving a predetermined minimum EGR rate.4. The variable geometry turbine for turbochargers in exhaust gas ...

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Номер записи: 74
04-01-2018 дата публикации

Steam turbine plant, combined cycle plant provided with same, and method of operating steam turbine plant

Номер: US20180003085A1
Автор: Hideaki Sugishita, Hideyuki Uechi, Yuichi Oka
Принадлежит: Mitsubishi Heavy Industries Ltd

A boiler includes one or more evaporators configured to heat water which has flowed therein to a specific heat maximum temperature at constant pressure or more in which a specific heat at constant pressure is maximized using a heated fluid and one or more reheaters configured to heat the steam which has come from the boiler using the heated fluid. All the reheaters configured to supply steam to a low-pressure steam turbine are disposed only at a downstream side of the high-pressure evaporator. All the reheaters heat reheating steam (FRHS) containing steam which has passed through a high-pressure steam turbine configured to receive steam supplied from the high-pressure evaporator and having a temperature lower than a specific heat maximum temperature at constant pressure in the high-pressure evaporator to less than the specific heat maximum temperature at constant pressure.

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Номер записи: 75
02-01-2020 дата публикации

Relative Position Measurement

Номер: US20200003071A1
Автор: Prentice Ian Francis
Принадлежит:

A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter. 111.-. (canceled)12. A method for determining a position of a first ring relative to a second ring in a gas turbine engine , the first ring including a surface having one or more first ring features and the second ring including a surface having one or more second ring features , the method comprising:directing a sensor towards the surface of the first ring, wherein the first ring substantially completely obstructs the surface of the second ring from a direct line of sight view of the sensor throughout the entire operation;sensing with the sensor a parameter influenced by the one or more first ring features and the one or more second ring features; anddetermining a position of the first ring relative to the second ring based on the parameter sensed with the sensor.13. The method of claim 12 , wherein determining a position of the first ring relative to the second ring based on the parameter sensed with the sensor comprises:sensing an overlap of the first ring features and the second ring features as a phase of parameter values;sensing a marker included on the surface of the first ring, wherein the marker has a geometry different than the one or more first ring features; anddetermining a position of the first ring relative to the second ring based on a position of the marker in the sensed phase of parameter values.14. The method of claim 13 , wherein the ...

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Номер записи: 76
02-01-2020 дата публикации

AIR TURBINE STARTER WITH TURBINE AIR EXHAUST OUTLET VALVE

Номер: US20200003072A1
Автор: FUKUDA Takao, Simpson Scott W., Zawilinski David J.
Принадлежит:

A system includes an air turbine starter having an inlet, a turbine air exhaust outlet, an output shaft, and a turbine in fluid communication with the inlet and the turbine air exhaust outlet. The turbine is operably coupled to the output shaft. The system also includes an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet. 1. A system comprising: an inlet;', 'a turbine air exhaust outlet;', 'an output shaft; and', 'a turbine in fluid communication with the inlet and the turbine air exhaust outlet, the turbine operably coupled to the output shaft; and', 'an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet., 'an air turbine starter comprising2. The system as in claim 1 , further comprising an actuator in fluid communication with the outlet valve assembly claim 1 , the actuator operable to adjust the exhaust area of the turbine air exhaust outlet.3. The system as in claim 2 , wherein the outlet valve assembly further comprises:a valve housing; anda valve body arranged between the valve housing and the turbine air exhaust outlet.4. The system as in claim 3 , wherein the valve housing comprises at least one pressure port claim 3 , and a pressurized cavity is formed between the at least one pressure port and the valve body responsive a pressurized flow from the actuator.5. The system as in claim 4 , further comprising at least one spring positioned between a housing of the air turbine starter and the valve body claim 4 , the at least one spring configured to provide an opening force to slide the valve body towards an open position and increase the exhaust area of the turbine air exhaust outlet.6. The system as in claim 5 , wherein the actuator is operable to increase the pressurized flow to the pressurized cavity and provide a closing force greater than the opening force to slide the valve body towards a closed position and decrease the exhaust area of the turbine air exhaust outlet.7. ...

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Номер записи: 77
02-01-2020 дата публикации

VARIABLE STATOR VANE ARRANGEMENT

Номер: US20200003073A1
Автор: KARAPURATH Neelambaran, KYLE Robert J.
Принадлежит: ROLLS-ROYCE PLC

A variable stator vane arrangement is provided in which the variable stator vanes extend from a first end at a radially inner flow boundary to a second end at a radially outer flow boundary. At least one of the radially inner flow boundary and the radially outer flow boundary is faceted, such that the surface of the faceted flow boundary comprises flat portions at the interfaces with the respective first or second end of each stator vane. The flat portions mean that the tips of the variable stator vanes can be made substantially flush with the flat casing portions. This may improve aerodynamic efficiency and/or increase the design flexibility on where to position the pivot axis of the variable stator vanes. 1. A compressor for a gas turbine engine comprising:a radially inner flow boundary;a radially outer flow boundary;an annular array of variable stator vanes, each stator vane extending from a first end at the radially inner flow boundary to a second end at the radially outer flow boundary, wherein:at least one of the radially inner flow boundary and the radially outer flow so boundary is faceted, such that the surface of the faceted flow boundary comprises flat portions at the interfaces with the respective first or second end of each stator vane.2. The compressor according to claim 1 , wherein:each stator vane is pivotable about a pivot axis; andthe flat portions of the faceted flow boundary are perpendicular to the pivot axis of the respective stator vane at each interface.3. The compressor according to claim 1 , wherein each stator vane comprises:an aerofoil portion; anda boundary interface portion, whereinthe boundary interface portion is a flat surface lying in the same plane as the adjacent flat portion of the faceted flow boundary.4. The compressor according to claim 3 , wherein the boundary interface portion is circular.5. The compressor according to claim 3 , wherein there is substantially no gap between the boundary interface portion and the surrounding ...

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Номер записи: 78
02-01-2020 дата публикации

Harmonic Drive for Shaft Driving Multiple Stages of Vanes via Gears

Номер: US20200003228A1
Автор: Gabriel L. Suciu, Jesse M. Chandler
Принадлежит: United Technologies Corp

A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

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Номер записи: 79
07-01-2021 дата публикации

VANE ANGLE SYSTEM ACCURACY IMPROVEMENT

Номер: US20210003029A1
Автор: Ward Thomas W.
Принадлежит:

A stator vane angle system includes an engine case, a plurality of stator vanes located at an interior of the engine case. Each stator vane is rotatable about a stator vane axis. A synchronization ring is located at an exterior of the engine case. The synchronization ring is operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes. A plurality of impingement openings extend through the engine case from the interior of the engine case to the exterior of the engine case. The plurality of impingement openings are configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring, thereby reducing a thermal mismatch between the engine case and the synchronization ring. 1. A stator vane angle system , comprising:an engine case;a plurality of stator vanes disposed at an interior of the engine case, each stator vane rotatable about a stator vane axis;a synchronization ring disposed at an exterior of the engine case, the synchronization ring operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes; anda plurality of impingement openings extending through the engine case from the interior of the engine case to the exterior of the engine case, the plurality of impingement openings configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring.2. The stator vane angle system of claim 1 , wherein the plurality of impingement openings each have an impingement opening outlet disposed at a same axial location as the synchronization ring.3. The stator vane angle system of claim 1 , wherein the plurality of impingement openings each extend perpendicular to ...

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Номер записи: 80
07-01-2021 дата публикации

GAS TURBINE ENGINE WITH MORPHING VARIABLE COMPRESSOR VANES

Номер: US20210003030A1
Автор: Chaudhry Zaffir A., Evans Simon W., Joly Michael M., Medic Gorazd, Prasad Dilip
Принадлежит:

A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed. 1. A stator vane for a gas turbine engine section comprising:a stator vane having an airfoil extending between a leading edge and a trailing edge, said airfoil having a suction side and a pressure side, and there being at least one piezoelectric actuator for changing a shape of at least one of said leading edge and said trailing edge.2. The stator vane as set forth in claim 1 , wherein at least one piezoelectric actuator is mounted on each of said suction and pressure sides claim 1 , with one of said piezoelectric actuators being controlled to contract and the other being controlled to expand to change the position of said leading edge relative to said trailing edge.3. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are mounted within pockets in said suction and pressure sides.4. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said leading edge about a virtual hinge axis while changing the position of the trailing edge to a lesser extent.5. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said trailing edge about a virtual hinge axis while changing the position of the leading edge to a lesser extent.6. The stator vane as set forth in claim 2 , wherein said airfoil is connected to inner and outer platforms.7. The stator vane as set forth in claim 6 , wherein there is an elastomeric material between said airfoil and said radially inner and outer platforms to accommodate movement of at least one of said leading and trailing edges.8. The stator vane as ...

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Номер записи: 81
03-01-2019 дата публикации

THERMALLY DRIVEN SPRING VALVE FOR TURBINE GAS PATH PARTS

Номер: US20190003333A1
Автор: Propheter-Hinckley Tracy A., Thornton Lane M.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A thermally driven spring valve for turbine gas path parts is disclosed herein. A thermally driven spring valve includes a bimetallic sheet comprising a base, a first finger portion extending from the base and a second finger portion extending from the base, the first finger portion having a first curvature vector and the second finger portion have a second curvature vector, wherein an exterior surface extends from the base through the first finger portion and the second finger portion and an interior surface extends from the base through the first finger portion and the second finger portion, wherein the exterior surface of the first finger portion is disposed proximate the interior surface of the base wherein the exterior surface of the second finger portion is disposed proximate the interior surface of the base. A thermally driven spring valve may include perforations through a finger portion. 1. A thermally driven spring valve comprising:a metallic sheet comprising a base mount portion and a floating portion having a curvature vector, wherein the base mount portion is coupled to a wall of a chamber, wherein the floating portion is disposed proximate an aperture in the wall.2. The thermally driven spring valve of , wherein the metallic sheet is coupled to the wall of the chamber by at least one of brazing or welding. The thermally driven spring valve of , wherein the metallic sheet is a bimetallic sheet.4. The thermally driven spring valve of claim 1 , wherein the metallic sheet comprises at least one of steel claim 1 , titanium claim 1 , titanium alloy claim 1 , cobalt claim 1 , cobalt alloy claim 1 , platinum claim 1 , or platinum alloy.5. The thermally driven spring valve of claim 1 , wherein the metallic sheet has a coefficient of thermal expansion of between about 0.6×10/K to about 25×10/K.6. The thermally driven spring valve of claim 1 , wherein the chamber is coupled to a baffle. This application is a divisional of, and claims priority to, and the benefit ...

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Номер записи: 82
03-01-2019 дата публикации

GAS TURBINE COOLING SYSTEM, GAS TURBINE FACILITY INCLUDING THE SAME, AND CONTROL METHOD OF GAS TURBINE COOLING SYSTEM

Номер: US20190003394A1
Автор: Fujii Satoko, Higashi Kazuya, YABE Tetsuya
Принадлежит:

A gas turbine cooling system includes: a cooling air line that guides compressed air compressed by an air compressor to a hot part; a cooler that cools the compressed air in the cooling air line; a return line that returns cooling air in the cooling air line to an upstream side in the cooling air line; a return valve that adjusts the flow rate of the cooling air flowing through the return line; and a control device that controls the degree of opening of the return valve. The control device has a second valve command generation section that, when a reception unit receives a load rejection command, generates as a second valve command a valve command ordering the degree of opening of the return valve to be forcedly increased to a predetermined load rejection-adapted degree of opening. 1. A gas turbine cooling system comprising:a cooling air line that guides compressed air compressed by an air compressor of a gas turbine to a hot part coming in contact with combustion gas in the gas turbine;a cooler that cools the compressed air in the cooling air line to produce cooling air;a booster that pressurizes the cooling air in the cooling air line;a return line that returns the cooling air in a discharge line that is a line of the cooling air line located on a side of the hot part from the booster, to an intake air line that is a line of the cooling air line located on a side of the air compressor from the booster;a return valve that is provided in the return line and adjusts a flow rate of the cooling air flowing through the return line;a detector that detects a state amount of the cooling air flowing through the intake air line and a state amount of the cooling air flowing through the discharge line; and a reception unit that receives a load rejection command indicating a load rejection of the gas turbine;', 'a first valve command generation section that generates a first valve command indicating a degree of opening of the return valve according to the state amount detected ...

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Номер записи: 83
13-01-2022 дата публикации

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

Номер: US20220010689A1
Автор: Becky E. Rose, Jonathan Gilson, Robert E. Malecki, Wesley K. Lord, Yuan J. Qiu
Принадлежит: Raytheon Technologies Corp

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

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Номер записи: 84
13-01-2022 дата публикации

VARIABLE-CAPACITY TURBOCHARGER

Номер: US20220010722A1
Автор: HANDA Kouichi, SAKISAKA Ryota, SEGAWA Kenichi
Принадлежит:

A variable-capacity turbocharger includes a nozzle flow passage in which a gas is capable of flowing therethrough from a scroll flow passage toward a turbine impeller, a connecting pin connecting flow passage wall surfaces forming the nozzle flow passage, and nozzle vanes arranged in a rotation direction of the turbine impeller. At least one of the flow passage wall surfaces includes an inner peripheral side wall surface extending radially inward of a first reference line extending in the rotation direction, an outer peripheral side wall surface which is a plane extending radially outward from a second reference line extending in the rotation direction and parallel to a plane orthogonal to rotation axes of the nozzle vanes, and an intermediate wall surface which is a plane extending from the first reference line to the second reference line and parallel to the plane extending orthogonal to the rotation axes of the nozzle vanes. 1. A variable-capacity turbocharger comprising:a nozzle flow passage in which a gas is capable of flowing therethrough from a scroll flow passage toward a turbine impeller;a connecting pin connecting flow passage wall surfaces forming the nozzle flow passage; andnozzle vanes arranged in a rotation direction of the turbine impeller, an inner peripheral side wall surface extending radially inward of a first reference line extending in the rotation direction, the inner peripheral side wall surface being inclined to extend away from the nozzle vanes in a rotation axis direction of the turbine impeller;', 'an outer peripheral side wall surface extending radially outward from a second reference line extending in the rotation direction and parallel to a plane orthogonal to rotation axes of the nozzle vanes, the outer peripheral side wall surface being located farther from the nozzle vanes than an edge portion of the inner peripheral side wall surface, the second reference line being located radially outward from the first reference line, and the ...

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Номер записи: 85
20-01-2022 дата публикации

WASTE HEAT RECOVERY SYSTEM WITH NOZZLE BLOCK INCLUDING GEOMETRICALLY DIFFERENT NOZZLES AND TURBINE EXPANDER FOR THE SAME

Номер: US20220018281A1
Автор: Huscher Frederick Michael
Принадлежит:

A waste heat recovery system for recovering waste heat of in internal combustion engine includes a turbine expander. The turbine expander includes a turbine blade, a shaft coupled to and rotatable by the turbine blade, and a nozzle assembly. The nozzle assembly includes a nozzle block disposed about the shaft and adjacent the turbine blade, a first nozzle component coupled to the nozzle block, and a second nozzle component coupled to the nozzle block. The first nozzle component defines a first nozzle having a first geometrical configuration. The second nozzle component defines a second nozzle having a second geometrical configuration that is different from the first geometrical configuration. The waste heat recovery system also includes a flow control device in fluid communication with the turbine expander. The waste heat recovery system further includes a controller in communication with the flow control device. 1. A waste heat recovery system for recovering waste heat of an internal combustion engine , said waste heat recovery system comprising: a turbine blade rotatable by the working fluid,', 'a shaft coupled to and rotatable by said turbine blade, with said shaft extending along a longitudinal axis, and', a nozzle block disposed about said shaft and adjacent said turbine blade,', 'a first nozzle component coupled to said nozzle block for accelerating the working fluid, with said nozzle component defining a first nozzle having a first geometrical configuration,', 'a second nozzle component coupled to said nozzle block for accelerating the working fluid, with said second nozzle component defining a second nozzle having a second geometrical configuration that is different from said first geometrical configuration', 'a third nozzle component coupled to said nozzle block for accelerating the working fluid, with said third nozzle component defining a third nozzle having a third geometrical configuration that is different from at least one of said first and second ...

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Номер записи: 86
08-01-2015 дата публикации

TURBINE FLOW MODULATION FOR PART LOAD PERFORMANCE

Номер: US20150010382A1
Автор: John Joshy, Subramaniyan Moorthi
Принадлежит:

Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation. 1. A method of modulating turbine airflow during part load operation in a turbomachine using exhaust gas recirculation , the turbomachine including a compressor , a turbine with a plurality of stages , and a diffuser , the method comprising:(a) extracting airflow from an upstream component of the turbomachine; and(b) admitting the extracted airflow into a turbine rear stage of the plurality of stages, wherein step (b) is practiced to increase rear stage loading and alter an energy distribution in the rear stage during the part load operation.2. A method according to claim 1 , further comprising claim 1 , prior to step (a) claim 1 , increasing compressor inlet flow claim 1 , wherein step (a) is practiced by extracting airflow from a front stage of the compressor claim 1 , the method further comprising claim 1 , before step (b) claim 1 , increasing a temperature of the airflow extracted from the compressor.3. A method according to claim 2 , wherein the step of increasing the temperature of the airflow comprises drawing exhaust gas from the diffuser and mixing the extracted airflow with the exhaust gas to form mixed flow claim 2 , wherein step (b) is practiced by admitting the mixed flow into the turbine rear stage.4. A method according to claim 2 , wherein the mixing step is practiced using an ejector.5. A method according to claim 2 , wherein step (a) is practiced by extracting the airflow from the front stage of the compressor at a preset temperature ...

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Номер записи: 87
08-01-2015 дата публикации

TURBOCHARGER

Номер: US20150010390A1
Автор: Kobayashi Takahiro, ONITSUKA Kazuhiro
Принадлежит: IHI CORPORATION

A turbocharger includes: an inflow passage to guide a fluid to a housing space for a turbine wheel; an exhaust passage to discharge the fluid having rotated the turbine wheel from a turbocharger body; a bypass passage connecting the inflow passage and the exhaust passage; a valve unit having one valve for a communicating portion between the exhaust passage and the housing space, and another valve for the bypass passage; an actuator to turn the valve unit and a stem connected to the valve unit about an axis of the stem; and a controller to operate the actuator. The controller adjusts the opening of the bypass passage by turning the valve unit within a specific range about the axis of the stem when a specific condition is met, and closes the exhaust passage by turning the valve unit beyond the specific range when the specific condition is not met. 1. A turbocharger comprising:a turbocharger body;a shaft located inside the turbocharger body, and provided with a turbine wheel on one end and a compressor wheel on another end;a housing space provided inside the turbocharger body, and configured to house the turbine wheel;an inflow passage communicating with the housing space, and configured to guide a fluid flowing from outside of the turbocharger body to the housing space;an exhaust passage communicating with a downstream side of the housing space in a flowing direction of the fluid, and configured to discharge the fluid having rotated the turbine wheel from the turbocharger body;a bypass passage connecting the inflow passage and the exhaust passage;a valve unit formed by integrating a first valve and a second valve, the first valve configured to open and close a communicating portion between the exhaust passage and the housing space, the second valve configured to open and close the bypass passage;an actuator configured to turn the valve unit and a stem connected to the valve unit about an axis of the stem; anda controller configured to operate the actuator, wherein the ...

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Номер записи: 88
11-01-2018 дата публикации

Bleed flow extraction system for a gas turbine engine

Номер: US20180009536A1
Автор: Brandon Wayne Miller, Charles Kammer Christopherson
Принадлежит: General Electric Co

An air cycle machine for extracting bleed air from a gas turbine engine of an aircraft is provided. The air cycle machine extracts a stream of low pressure bleed air and a stream of high pressure bleed air from a compressor section of the gas turbine engine. The air cycle machine includes a compressor that receives the stream of low pressure bleed air and a turbine that receives the stream of high pressure bleed air. The stream of high pressure bleed air is expanded as it drives the turbine, and the stream of low pressure bleed air is compressed by the compressor. The resulting streams of bleed air are substantially the same pressure, such that they may be merged using a junction into a combined bleed air stream having a temperature and pressure suitable for use by a variety of aircraft accessory systems, such as an environmental control system. The air cycle machine may further power or be powered from an electrical storage device or generator on the fan.

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Номер записи: 89
14-01-2016 дата публикации

Gas turbine engine airfoil leading edge cooling

Номер: US20160010465A1
Автор: Dominic J. Mongillo, Jr., Matthew A. Devore, Thomas N. Slavens
Принадлежит: United Technologies Corp

An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.

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Номер записи: 90
14-01-2016 дата публикации

AERO-ACTUATED VANES

Номер: US20160010486A1
Автор: Christians Joseph T.
Принадлежит:

A turbomachinery vane includes a vane body defining a longitudinal axis, a trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis, and a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions. A gas turbine engine includes a turbomachinery component including a row of actuated stators, wherein the actuated stator row includes a plurality of the turbomachinery vanes. A method of actuating a vane by aerodynamic loads includes moving the vane about a pivot point from a first position to a second position by a first set of by aerodynamic loads. 1. A turbomachinery vane comprising:a vane body defining a longitudinal axis; anda trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis.2. A vane as recited in claim 1 , further comprising a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions.3. A vane as recited in claim 2 , wherein the vane body includes a leading edge claim 2 , an opposed trailing edge claim 2 , a high pressure side claim 2 , and an opposed low pressure side claim 2 , and the trunnion is located at a position relative to the leading edge claim 2 , the trailing edge claim 2 , the high pressure side claim 2 , and the low pressure side for aerodynamic loads to pivot the vane body.4. A vane as recited in claim 3 , wherein the trunnion is located at a position relative to the leading edge claim 3 , the trailing edge claim 3 , the high pressure side claim 3 , and the low pressure side for a first set of aerodynamic loads pivot the vane body from a first locked position to the second locked position and a second set of aerodynamic loads pivot the vane body from the second locked position to a first locked position.5. A vane as recited in claim 1 , wherein the lock system is configured to release the ...

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Номер записи: 91
14-01-2016 дата публикации

VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM

Номер: US20160010487A1
Автор: BREEZE-STRINGFELLOW Andrew, CEDAR Richard David, Zatorski Darek Tomasz
Принадлежит: GENERAL ELECTRIC COMPANY

A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle. 1. A unshrouded vane assembly for an unducted propulsion system , comprising a vane assembly having a plurality of vanes which have non-uniform characteristics with respect to one another configured to generate a desired vane exit swirl angle.2. The vane assembly of claim 1 , wherein said vanes have a non-uniform characteristic selected from the group consisting of: camber claim 1 , stagger claim 1 , circumferential spacing claim 1 , axial position claim 1 , span claim 1 , tip radius claim 1 , and combinations thereof.3. The vane assembly of claim 2 , wherein said vanes have a root claim 2 , a tip claim 2 , and a span therebetween claim 2 , and wherein said non-uniform characteristic is attributed to a portion of the span of said vanes.4. The vane assembly of claim 3 , wherein said non-uniform characteristic is attributed to substantially all of the span of said vanes.5. The vane assembly of claim 1 , wherein said vanes are variable in pitch.6. The vane assembly of claim 5 , wherein said vanes are individually variable in pitch.7. The vane assembly of claim 5 , wherein a plurality of said vanes are variable in pitch in conjunction with one another.8. An unducted propulsion system claim 5 , said propulsion system comprising a rotating element having an axis of rotation and a stationary element claim 5 , said rotating element having a plurality of blades each having a blade root proximal to said axis claim 5 , a blade tip remote from said axis claim 5 , and a blade span measured between said blade root and said blade tip claim 5 , wherein said stationary element has a plurality of vanes each having a vane root proximal to said axis claim 5 , a vane tip remote from said axis claim 5 , and a vane span measured between said vane root and said vane tip configured to impart a change in ...

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Номер записи: 92
14-01-2016 дата публикации

WEAR PROTECTION ARRANGEMENT FOR A TURBOMACHINE, PROCESS AND COMPRESSOR

Номер: US20160010488A1
Автор: ALBERS Lothar, BOCK Stephan, Schneiderbanger Stefan
Принадлежит:

The present invention relates to a wear protection arrangement for a turbomachine, comprising at least one adjustable guide vane, a casing in which the guide vane is arranged in an adjustable manner, an inner ring, made from a metallic material, in or on which the guide vane is arranged in an adjustable manner, a first gap between an inner guide vane tab and the inner ring and a second gap between an outer guide vane tab and the casing, at least one wear protection coating, wherein the wear protection coating(s) is/are connected to the inner ring and/or to the inner guide vane tab and the wear protection coating(s) forms or form the first gap, at least in certain regions, and/or the wear protection coating(s) is/are connected to the casing and/or to the outer guide vane tab and the wear protection coating(s) forms/form the second gap, at least in certain regions. The invention further relates to a method for applying an abradable wear protection coating and for applying an abrasive wear protection coating and to a compressor for a turbomachine having a wear protection arrangement. 114.-. (canceled)15. A wear protection arrangement for a turbomachine , wherein the arrangement comprisesat least one adjustable guide vane,a casing in which the at least one guide vane is arranged in an adjustable manner,an inner ring made from a metallic material, in or on which ring the at least one guide vane is arranged in an adjustable manner,a first gap between an inner guide vane tab and the inner ring and a second gap between an outer guide vane tab and the casing,one or more wear protection coatings connected to the inner ring and/or to the inner guide vane tab and forming the first gap, at least in certain regions,and/or one or more wear protection coatings connected to the casing and/or to the outer guide vane tab and forming the second gap, at least in certain regions.16. The wear protection arrangement of claim 15 , wherein the one or more wear protection coatings are ...

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Номер записи: 93
14-01-2016 дата публикации

Variable nozzle for aeronautic gas turbine engine

Номер: US20160010489A1
Автор: Takehiko Kimura, Yoshinori Ooba, Yuta Matsumoto
Принадлежит: IHI Corp

A variable nozzle is comprised of: an exhaust duct vectoring a flow of the exhaust gas to the aft end; a plurality of primary flaps arranged to define a primary flow path converging toward the aft end, each of the primary flaps being swingably pivoted on the exhaust duct to regulate a degree of opening the primary flow path and including a first section and a second section forming an angle axially outward relative to the first section; and a plurality of secondary flaps arranged to define a secondary flow path in communication with the primary flow path, the secondary flow path being capable of divergent toward the aft end, the secondary flaps being respectively swingably pivoted on the second sections of the primary flaps to regulate a degree of opening the secondary flow path.

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Номер записи: 94
14-01-2016 дата публикации

EXHAUST-GAS TURBOCHARGER

Номер: US20160010542A1
Автор: Metz Dietmar
Принадлежит: BORGWARNER INC.

An exhaust-gas turbocharger () having a turbine () which has a turbine wheel () surrounded by an inflow duct (), and having a VTG cartridge (), which VTG cartridge has a disk () and a vane bearing ring (), which delimit the inflow duct (), and which VTG cartridge has a multiplicity of vanes () which are arranged in the inflow duct () and which are mounted in the vane bearing ring () by way of rotatable vane shafts (), which vane shafts are connected to vane levers (), the lever heads () of which engage into associated grooves () in an adjusting ring () which surrounds the vane bearing ring () on the outside. At least one min-flow stop () has, on an outer surface (), a laser-cut portion (). 11. An exhaust-gas turbocharger () having{'b': '2', 'claim-text': {'b': 3', '4, 'which has a turbine wheel () surrounded by an inflow duct (), and'}, 'a turbine ()'}{'b': '5', 'claim-text': {'b': 8', '4', '7', '9', '10', '11', '12', '13', '7, 'which VTG cartridge has a multiplicity of vanes () which are arranged in the inflow duct () and which are mounted in the vane bearing ring () by way of rotatable vane shafts (), which vane shafts are connected to vane levers (), the lever heads () of which engage into associated grooves () in an adjusting ring () which surrounds the vane bearing ring () on the outside;'}, 'a VTG cartridge (),'}{'b': 25', '26', '31', '32, 'wherein at least one min-flow stop (, ) has, on an outer surface (), a laser-cut portion ().'}225263231. The exhaust-gas turbocharger as claimed in claim 1 , wherein the min-flow stop ( claim 1 , ) is a round stop bolt claim 1 , and wherein the laser-cut portion () is a planar surface region on the round outer surface ().329302526132728. The exhaust-gas turbocharger as claimed in claim 1 , wherein cutouts ( claim 1 , ) claim 1 , which come into contact with the min-flow stop ( claim 1 , ) claim 1 , of the adjusting ring () have parallel stop edges ( claim 1 , ).4137. The exhaust-gas turbocharger as claimed in claim 1 , ...

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Номер записи: 95
14-01-2016 дата публикации

GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO

Номер: US20160010565A9
Автор: Kohlenberg Gregory A., Schwarz Frederick M., Zamora Sean P.
Принадлежит:

A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. 1. A gas turbine engine comprising:a core nacelle defined about an engine centerline axis;a core engine at least partially disposed within the core nacelle;a fan section with twenty (20) or less fan blades;a gear system driven by the core engine to drive said fan section;a fan nacelle mounted at least partially around said fan section and said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan bypass airflow having a fan pressure ratio of the fan bypass airflow during engine operation, said fan pressure ratio less than about 1.45;a variable fan nozzle axially movable relative to the fan nacelle, the variable fan nozzle including at least two sectors; anda controller for independently adjusting each of the at least two sectors.2. (canceled)3. The engine as recited in claim 1 , wherein the controller is operable to reduce said fan nozzle exit area at a cruise flight condition.4. The engine as recited in claim 1 , wherein said controller is operable to control said fan nozzle exit area to reduce a fan instability.5. The engine as recited in claim 1 , wherein said fan variable area nozzle defines a trailing edge of said fan nacelle.6. The engine as recited in claim 1 , wherein said fan variable area nozzle is axially movable relative to said fan nacelle.7. (canceled)8. The engine as recited in claim 1 , wherein said fan section defines a corrected fan tip speed less than about 1150 ft/second.9. The engine as recited in claim 1 , wherein said core engine includes a low pressure turbine which defines a low pressure turbine pressure ratio that is greater than about five (5).10. The engine as recited in claim 7 , wherein said core engine includes a low pressure turbine which defines a low pressure turbine pressure ratio that is greater than five (5).11. The engine as recited in claim 1 , further comprising a gear system ...

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Номер записи: 96
11-01-2018 дата публикации

TURBINE IMPELLER AND VARIABLE GEOMETRY TURBINE

Номер: US20180010464A1
Автор: Ibaraki Seiichi, Yokoyama Takao, YOSHIDA Toyotaka
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade. 112-. (canceled)13. A turbine impeller , comprising:a hub portion coupled to an end of a rotational shaft;a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; anda short blade disposed between two adjacent main blades among the plurality of main blades,wherein an inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction,wherein a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade, in a meridional plane, andwherein, in the meridional plane, a hub-side end of a trailing edge of the short blade is positioned on a same position, in an axial direction, as a hub-side end of a trailing edge of the main blade.14. The turbine impeller according to claim 13 ,{'b': 2', '1', '1', '2, 'wherein the hub-side end of the leading edge of the short blade is positioned in a region which satisfies 0.30 Подробнее

Номер записи: 97
11-01-2018 дата публикации

SYSTEM FOR CONTROLLING VARIABLE PITCH BLADES FOR A TURBINE ENGINE

Номер: US20180010478A1
Автор: BENDERRADJI Kamel, BROMANN Alain Marc, COUSTILLAS Suzanne Madeleine, DUMAS Lilian Yann, Lucien
Принадлежит:

The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot () that defines a substantially radial axis of rotation of the blade and which is connected by a lever () to control means (, ) extending about said axis. The invention is characterized in that said control means include first links () supported by said pivots and second links () extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means (). 1. A control system for variable-pitch vanes for a turbine engine , comprising at least one annular row of variable-pitch vanes extending around an axis and each comprising a blade which is connected at the radially outer end thereof to a pivot which defines a substantially radial axis of rotation of the vane and which is connected by a lever to control means extending around said axis , wherein said control means comprise first links carried by said pivots and second links extending between said first links , said first and second links extending substantially over the same circumference around said axis and being connected to one another and to actuation means.2. The control system according to claim 1 , wherein the number of the first links is equal to the number of the second links claim 1 , which is equal to the number of levers.3. The control system according to claim 1 , wherein said first links are formed in one piece with said levers.4. The control system according to claim 1 , wherein each of the first and/or second links has an elongate shape and is connected by the longitudinal ends thereof to other links.5. The control system according to claim 1 , wherein the first links are connected by pivot and/or swivel connections to the second links. ...

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Номер записи: 98
11-01-2018 дата публикации

Plant control apparatus, plant control method and power plant

Номер: US20180010526A1
Автор: Kazuna SAWATA, Masayuki Tobo, Takahiro Mori
Принадлежит: Toshiba Corp

In one embodiment, a plant includes a combustor to burn fuel with oxygen from an inlet guide vane (IGV) to generate a gas for a gas turbine (GT), and a heat recovery steam generator to use an exhaust gas from GT to generate steam for a steam turbine (ST). An apparatus controls an IGV opening degree to a first degree and a GT output value to a value larger than a first value between GT start and ST start. The first value is an output value at which exhaust gas temperature can be kept at a first temperature that depends on ST metal temperature, when the IGV opening degree is the first degree. The apparatus increases the IGV opening degree from the first degree based on steam temperature or the GT output value, while the GT output value is controlled to the value larger than the first value.

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Номер записи: 99
14-01-2021 дата публикации

TURBOCHARGER

Номер: US20210010387A1
Автор: HAYASHI Katsunori, ITOU Koutarou, IWASA Yoshitaka, KOJIMA Hidenori, SEGAWA Kenichi, UEDA Takafumi
Принадлежит:

A turbocharger includes a turbine housing configured to accommodate a turbine wheel provided at one end of a rotation shaft, a bearing housing joined to the turbine housing and in which a bearing for supporting the rotation shaft is provided; and a variable nozzle unit that is disposed between the turbine housing and the bearing housing. The variable nozzle unit includes a nozzle ring disposed around a rotation axis of the rotation shaft and a support ring provided adjacent to the nozzle ring that includes an outer peripheral portion partially in contact with the turbine housing. One or more non-contact portions are formed in the outer peripheral portion of the support ring and do not contact the turbine housing. 1. A turbocharger comprising:a turbine housing configured to accommodate a turbine wheel provided at one end of a rotation shaft;a bearing housing joined to the turbine housing and in which a bearing for supporting the rotation shaft is provided; and a nozzle ring disposed around a rotation axis of the rotation shaft; and', 'a support ring provided adjacent to the nozzle ring that comprises an outer peripheral portion partially in contact with the turbine housing,, 'a variable nozzle unit that is disposed between the turbine housing and the bearing housing and compriseswherein one or more non-contact portions are formed in the outer peripheral portion of the support ring and do not contact the turbine housing.2. The turbocharger according to claim 1 ,wherein the variable nozzle unit comprises one or more connecting pins configured to connect the nozzle ring to the support ring, andwherein the non-contact portions are provided at locations in the outer peripheral portion of the support ring corresponding to the connecting pins in the circumferential direction.3. The turbocharger according to claim 2 , further comprising:one or more nozzle ring pin holes provided at the nozzle ring; andone or more support ring pin holes provided at the support ring,wherein at ...

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Номер записи: 100