公开(公告)号：US09897012B2

公开(公告)日：2018-02-20

申请号：US14399049

申请日：2013-05-06

Applicant: SNECMA

Inventor： Sylvain Chauvel

IPC: F02C9/18 ,  F02C6/08 ,  F15B15/14 ,  F04D27/02 ,  F04D29/64 ,  F01D17/10 ,  F04D27/00

CPC classification number: F02C9/18 ,  F01D17/105 ,  F02C6/08 ,  F04D27/009 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/644 ,  F05D2230/60 ,  F15B15/14 ,  Y02T50/671 ,  Y10T29/49229

Abstract: A method for assembling an actuating ram of air bleed valves, which ram is placed between low pressure and high pressure compressors of a turbomachine, the ram including a piston rod surrounded by a spacer extending from the piston cylinder and configured to be connected to an end of the transmission mechanism linked to the bleed valves, the method including: deploying the piston rod such that it projects from the spacer; connecting the projecting piston rod to the end of the transmission mechanism; retracting the piston rod to bring the cylinder closer to the case wall; and attaching the spacer to the case wall.

公开(公告)号：US20180038280A1

公开(公告)日：2018-02-08

申请号：US15667873

申请日：2017-08-03

Applicant: AIRBUS OPERATIONS (SAS)

Inventor： Jean-Michel ROGERO ,  Olivier VERSEUX

IPC: F02C7/14 ,  F02C3/04 ,  F02C7/22 ,  B64D15/02 ,  F02C6/04 ,  B64D27/10 ,  B64D33/02 ,  F01D25/24 ,  F02C7/047

CPC classification number: F02C7/14 ,  B64D15/02 ,  B64D27/10 ,  B64D33/02 ,  F01D25/02 ,  F01D25/24 ,  F02C3/04 ,  F02C6/04 ,  F02C7/047 ,  F02C7/222 ,  F02C7/224 ,  F02C9/18 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/675

Abstract: A dual-flow turbomachine including a nacelle, compressors, turbines, a fuel supply line, a transfer line, a de-icing circuit, and a heat management system having: a first heat exchanger providing an exchange of heat between fuel in the supply line and oil in the transfer line, a loop comprising a main line and a pump which circulates a heat transfer fluid in the main line, where the main line is connected to an outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger the main line meets an inlet of the de-icing circuit, where at the outlet of the de-icing circuit the main line meets the inlet of the pump, and where the third heat exchanger transfers heat between the heat transfer fluid of the main line and the oil of the transfer line.

公开(公告)号：US09879609B1

公开(公告)日：2018-01-30

申请号：US14080908

申请日：2013-11-15

Applicant: TUCSON EMBEDDED SYSTEMS, INC.

Inventor： David Crowe ,  Elden Crom

IPC: G06F19/00 ,  F02C9/00

CPC classification number: F02C9/00 ,  F02C6/00 ,  F02C6/02 ,  F02C9/18 ,  F02C9/22 ,  F02C9/26 ,  F02C9/42 ,  F04B17/00 ,  F04D13/02 ,  F04D15/0066 ,  F05D2270/021 ,  F05D2270/06 ,  H02P9/04

Abstract: A digital engine controller compatible with multiple variants of gas turbine engine is programmed to receive identification of a variant of gas turbine engine coupled to the digital controller and thereafter to automatically determine and adjust inputs to the engine, according to the received identification of engine variant, to meet user-specified output.

公开(公告)号：US20180023906A1

公开(公告)日：2018-01-25

申请号：US15213931

申请日：2016-07-19

Applicant: Unison Industries, LLC

Inventor： Gordon Tajiri ,  Michael Thomas Kenworthy ,  Yanzhe Yang ,  Dattu GV Jonnalagadda

IPC: F28F27/02 ,  F16K31/44 ,  F02C7/14 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F16K31/00 ,  F16K17/38

CPC classification number: F28F27/02 ,  F01D25/12 ,  F02C3/04 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02C9/18 ,  F02K3/115 ,  F05D2260/213 ,  F05D2300/505 ,  F16K17/38 ,  F16K31/002 ,  F16K31/44 ,  Y02T50/672 ,  Y02T50/675

Abstract: A valve and a heat exchanger apparatus for a gas turbine engine include a valve body having a valve seat and an actuation component including a plate formed from a set of metal layers and responsive to a change in at least one of a thermal condition and a pressure exerted thereon such that the plate moves and the valve moves between an opened and a closed position where a portion of the plate engages with the valve seat.

公开(公告)号：US20180023475A1

公开(公告)日：2018-01-25

申请号：US15217381

申请日：2016-07-22

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F02C7/18 ,  F02C9/18 ,  F01D9/06 ,  F02C3/04 ,  F01D25/24

CPC classification number: F02C7/18 ,  F01D9/065 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/12 ,  F02C9/18 ,  F02K3/115 ,  F05D2220/32 ,  F05D2260/208 ,  F05D2270/303 ,  Y02T50/676

Abstract: A gas turbine engine includes a core nacelle and a core engine disposed in the core nacelle. The core engine includes at least a compressor section, a combustor section, and a turbine section, which define a core flowpath. A bypass duct is radially outwards of the core nacelle. A component is disposed in the core engine. A cooling cavity is disposed outside of the bypass duct. A heat pipe contains a working medium sealed therein. The heat pipe includes a first section configured to accept thermal energy and a second section configured to dissipate the thermal energy in the cooling cavity. A tap from at least one of the compressor section or the bypass duct is configured to provide bleed air to the cooling cavity and dissipate the thermal energy from the second section.

公开(公告)号：US20180010520A1

公开(公告)日：2018-01-11

申请号：US15545072

申请日：2016-01-25

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Yoshifumi IWASAKI ,  Toshishige AI ,  Yuya FUKUNAGA ,  Tatsuya IWASAKI

IPC: F02C7/18 ,  F01D5/18 ,  F02C9/18 ,  F01D9/04 ,  F01D25/12 ,  F02C3/06

CPC classification number: F02C7/185 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F02C3/06 ,  F02C6/08 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/211 ,  F05D2260/606 ,  F05D2270/112 ,  F05D2270/303

Abstract: A cooling system includes: a high pressure bleed line configured to bleed high pressure compressed air from a first bleed position of a compressor and to send the air to a first hot part; a low pressure bleed line configured to bleed low pressure compressed air from a second bleed position of the compressor and to send the air to a second hot part; an orifice provided in the low pressure bleed line; a connecting line configured to connect the high pressure bleed line and the low pressure bleed line; a first valve provided in the connecting line; a bypass line configured to connect the connecting line and the low pressure bleed line; and a second valve provided in the bypass line.

公开(公告)号：US09863285B2

公开(公告)日：2018-01-09

申请号：US14662836

申请日：2015-03-19

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Thomas John Freeman ,  John David Memmer ,  Timothy Joseph Rehg ,  Alston Ilford Scipio

IPC: F01K23/10 ,  F02C6/02 ,  F02C6/00 ,  F02C6/18 ,  F02C9/18 ,  F02C3/10 ,  F02C6/08

CPC classification number: F01K23/10 ,  F02C3/10 ,  F02C6/00 ,  F02C6/02 ,  F02C6/08 ,  F02C6/18 ,  F02C9/18 ,  Y02E20/14 ,  Y02E20/16

Abstract: A power generation system may include a generator; a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A first control valve system controls flow of the excess air flow along an excess air flow path to a supplemental gas turbine system. The excess air flow may be combusted with a fuel and supplied to the supplemental gas turbine system. An eductor may be positioned in the excess air flow path for using the excess air flow as a motive force to augment the excess air flow with additional gas.

公开(公告)号：US09850818B2

公开(公告)日：2017-12-26

申请号：US14753074

申请日：2015-06-29

Applicant: General Electric Company

Inventor： Parag Prakash Kulkarni ,  Lewis Berkley Davis, Jr. ,  Robert Joseph Reed

IPC: F02C7/18 ,  F01D15/10 ,  F01N3/20 ,  F02C7/141 ,  F02C9/18 ,  F02C3/04 ,  F01D25/26 ,  F01D25/30 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D15/10 ,  F01D25/26 ,  F01D25/305 ,  F01N3/2066 ,  F01N2270/02 ,  F01N2590/10 ,  F01N2610/02 ,  F01N2610/08 ,  F02C3/04 ,  F02C6/08 ,  F02C7/141 ,  F02C9/18 ,  F05D2220/32 ,  F05D2250/80 ,  F05D2260/606 ,  F05D2270/082 ,  Y02T10/24

Abstract: An airflow control system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for extracting a supply of bypass air from an excess flow of air generated by the compressor component of the gas turbine system; an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

公开(公告)号：US20170363043A1

公开(公告)日：2017-12-21

申请号：US15419533

申请日：2017-01-30

Applicant: ROLLS-ROYCE plc

Inventor： Ahmad RAZAK

IPC: F02K3/10 ,  F02C9/18 ,  F02C3/04 ,  F02C7/36 ,  F02K3/11 ,  F02K3/075

CPC classification number: F02K3/10 ,  F02C3/04 ,  F02C3/14 ,  F02C6/003 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F02K3/11 ,  F05D2220/80

Abstract: An aircraft gas turbine engine comprises a high pressure compressor driven by a high pressure turbine via a high pressure shaft, a first combustor provided downstream of the high pressure compressor and upstream of the high pressure turbine, a low pressure compressor driven by a low pressure turbine via a low pressure shaft, the low pressure compressor being configured to provide air to the high pressure compressor and to a bypass flow. The low pressure turbine comprises at least first and second turbine stages. The engine further comprises a second combustor provided downstream of the first stage of the low pressure turbine and upstream of the second stage of the low pressure turbine. The engine comprises a shaft coupling arrangement configured to transfer power between the high and low pressure shafts.

公开(公告)号：US20170321605A1

公开(公告)日：2017-11-09

申请号：US15148051

申请日：2016-05-06

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Mosheshe Camara-Khary Blake

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/18

CPC classification number: F02C7/18 ,  F02C3/04 ,  F02C6/08 ,  F02C7/185 ,  F02C9/18 ,  F02K3/115 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28F9/0278 ,  F28F2270/00 ,  Y02T50/675

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.