公开(公告)号：EP3901445B1

公开(公告)日：2024-08-28

申请号：EP21151924.4

申请日：2021-01-15

IPC分类号： F02K3/06 ,  F02C1/10

CPC分类号： F02C6/08 ,  F02C9/18 ,  F02C7/185 ,  F05D2260/21320130101 ,  F05D2220/6220130101 ,  F02C1/10 ,  F02K3/06 ,  F01K25/103 ,  F01K23/02 ,  F22B3/08 ,  F01K23/10

公开(公告)号：EP3106646B2

公开(公告)日：2024-07-31

申请号：EP16174862.9

申请日：2016-06-16

IPC分类号： F02C7/14 ,  F02K3/115 ,  F02C7/18 ,  F01D25/12 ,  F02C6/08 ,  B64D33/10 ,  B64D29/02 ,  F02C9/18

CPC分类号： F01D25/12 ,  F02K3/115 ,  F02C6/08 ,  F02C7/14 ,  F02C9/18 ,  F05D2260/21320130101 ,  F05D2260/23120130101 ,  F05D2270/30320130101 ,  F02C7/185 ,  Y02T50/60

公开(公告)号：EP3901411B1

公开(公告)日：2024-07-03

申请号：EP21170439.0

申请日：2019-10-22

IPC分类号： F01D5/08 ,  F01D9/06 ,  F02C7/18 ,  F02C7/10

CPC分类号： F01D5/081 ,  F01D9/065 ,  F02C7/185 ,  F05D2260/21320130101

公开(公告)号：EP4365428A1

公开(公告)日：2024-05-08

申请号：EP23202077.6

申请日：2023-10-06

申请人： General Electric Company

发明人： NIERGARTH, Daniel Alan ,  CLEMENTS, Jeffrey Donald ,  SPRUILL, Jeffrey ,  OSGOOD, Daniel Endecott ,  KRAMMER, Erich Alois ,  MACDONALD, Matthew Kenneth ,  SCHIMMELS, Scott Alan

IPC分类号： F02C7/18 ,  F02K3/02 ,  F02K3/06

CPC分类号： F02C7/185 ,  F02K3/06 ,  F02K3/02 ,  F02K3/025

摘要： A gas turbine engine (100) is provided. The gas turbine engine includes a turbomachine (120) including a compressor section, a combustion section (130), and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor (128) defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine (100) defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal x EGT / (AHPCExit2 x 1000).

公开(公告)号：EP3398702A3

公开(公告)日：2018-12-26

申请号：EP18170078.2

申请日：2018-04-30

申请人： Unison Industries LLC

发明人： YANG, Yanzhe ,  DYER, Daniel ,  BRINGAS, Armando ,  BURDETTE, Jason Levi ,  TAJIRI, Gordon ,  JONNALAGADDA, Dattu GuruVenkata ,  KENWORTHY, Michael Thomas

IPC分类号： B22F3/00 ,  B22F5/10 ,  F01D9/06 ,  F16L9/00

CPC分类号： F16L9/006 ,  B22F3/00 ,  B22F5/009 ,  B22F5/106 ,  B22F2005/103 ,  B64D13/06 ,  F02C6/08 ,  F02C7/14 ,  F02C7/185 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/642 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/131 ,  F05D2250/25 ,  F05D2250/75 ,  F05D2260/60 ,  F16L9/00 ,  F16L9/02 ,  F16L27/111 ,  F16L51/025 ,  F28D7/106 ,  F28D7/1615 ,  F28F1/06 ,  F28F2210/06

摘要： A duct (100) for a turbine engine (10), such as a gas turbine engine, can be utilized to carry a fluid from one portion of the engine (10) to another. The duct (100) can include a metallic tubular element (101) having one of a varying wall thickness, a varying cross section, or a tight bend (132). Such a duct (100) can be formed utilizing additive manufacturing or metal deposition on an additively manufactured mandrel (486).

公开(公告)号：EP3406885A1

公开(公告)日：2018-11-28

申请号：EP18170080.8

申请日：2018-04-30

申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

发明人： Snyder, Douglas ,  Hall, Ronald

IPC分类号： F02C7/224 ,  F23R3/28

CPC分类号： F23R3/283 ,  F02C7/185 ,  F02C7/224 ,  F05D2260/204 ,  F05D2260/213 ,  F23R2900/00018

摘要： A cooling air system for use in a gas turbine fuel injector (32) includes a microchannel fuel-air heat exchanger (38). The fuel-air heat exchanger (38) allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine and includes a leak management system (40).

公开(公告)号：EP3379036A1

公开(公告)日：2018-09-26

申请号：EP17162453.9

申请日：2017-03-22

申请人： Ansaldo Energia Switzerland AG

发明人： HUBER, Tobias Christoph ,  BAUMANN, Andres Robert

IPC分类号： F01D11/24 ,  F02C6/08 ,  F02C7/18

CPC分类号： F01D11/24 ,  F01D11/003 ,  F02C6/08 ,  F02C7/185 ,  F05D2260/213

摘要： The gas turbine engine (1) comprises a compressor (2), a combustor plenum (3) housing at least one combustion chamber (4), at least one turbine (5) having at least a first stage (16). The turbine (5) comprises an outer housing (7) and a turbine vane carrier (12). A cooling plenum (13) for air is defined between the outer housing (7) and the turbine vane carrier (12). The gas turbine engine (1) comprises an annular element (15, 19) upstream of a vane (10A) of the first stage with respect to the hot gas direction (G), and a heat exchanger (6) is connected between the combustor plenum (3) and the cooling plenum (13). The method for cooling the gas turbine engine involves cooling the compressed air in said heat exchanger (6).

公开(公告)号：EP3194729B1

公开(公告)日：2018-09-26

申请号：EP15797889.1

申请日：2015-11-06

申请人： Siemens Aktiengesellschaft

发明人： LARSON, Marco

IPC分类号： F01D21/00 ,  F02C7/143 ,  F02C7/18 ,  F02C9/20

CPC分类号： F02C7/143 ,  F01D21/00 ,  F02C3/04 ,  F02C7/042 ,  F02C7/185 ,  F02C9/20 ,  F05D2220/32 ,  F05D2260/212 ,  F05D2270/303 ,  F05D2270/311

公开(公告)号：EP2944767B1

公开(公告)日：2018-09-12

申请号：EP15164984.5

申请日：2015-04-24

申请人： Rolls-Royce plc

发明人： Bagall, Adam MacGregor ,  Beecroft, Peter ,  Stretton, Richard Geoffrey ,  Woodrow, Philip Geoffrey ,  Baralon, Stephane Michel Marcel ,  Smith, Angus Roy

IPC分类号： F01D9/06 ,  F02C7/14 ,  F02C7/18

CPC分类号： F02C9/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/24 ,  F02C6/08 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02K3/06 ,  F02K3/115 ,  Y02T50/675

摘要： A gas turbine engine comprising an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing comprises a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop comprises a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine.

公开(公告)号：EP3330524A1

公开(公告)日：2018-06-06

申请号：EP17205089.0

申请日：2017-12-04

申请人： United Technologies Corporation

发明人： SCHWARZ, Frederick M. ,  SNAPE, Nathan

IPC分类号： F02K3/115 ,  F02C7/141 ,  F02C9/18

CPC分类号： F02C7/185 ,  F02C3/04 ,  F02C7/141 ,  F02C9/18 ,  F02K3/06 ,  F02K3/115 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2270/01 ,  Y02T50/675

摘要： A gas turbine engine (100) has a fan rotor (87) delivering air into a bypass duct defined between an outer fan case (94) and an outer interior housing. The fan rotor (87) also delivers air into a compressor section (77,79), a combustor (106), a turbine section (108H,108L). A chamber (97) is defined between the outer interior housing and an inner housing (113). The inner housing (113) contains the compressor section (77,79), the combustor (106) and the turbine section (108H,108L). A first conduit (110) taps hot compressed air to be cooled and passes the air to at least one heat exchanger (102). The air is cooled in the heat exchanger (102) and returned to a return conduit (112). The return conduit (112) passes the cooled air to at least one of the turbine section (108H,108L) and the compressor section (77,79). The heat exchanger (102) has a core exhaust plane (86). The turbine section (108H,108L) has at least a first and a downstream second rotor blade row (80,82), with the core exhaust plane (86) located downstream of a center plane (88) of the second blade row (82).