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公开(公告)号：EP4417796A1
公开(公告)日：2024-08-21
申请号：EP24151475.1
申请日：2024-01-11
CPC分类号： F05D2220/7620130101 , F02C3/145 , F02C3/103 , F01D15/10 , F02C7/18 , F05D2260/21320130101 , F02C6/206
摘要： An aircraft engine (10) assembly comprising: a gas turbine engine (10) having a high pressure compressor (22), a high pressure turbine (28), a high pressure shaft (34) coupling the high pressure compressor (22) with the high pressure turbine (28), a low pressure turbine, and a low pressure shaft (36) coupled to the low pressure turbine, the high pressure turbine (28) located forward of the high pressure compressor (22), and the low pressure turbine located on a forward end of the gas turbine engine (10); an intake channel (54) of the gas turbine engine (10) configured to receive an incoming flow of air and form an intake flow of air, the intake channel (54) configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine (10), the incoming flow direction reverse of the first axial direction; and an electric machine (74, 74a, 74b) coupled with the low pressure shaft (36) and located on a side of the high pressure compressor (22) opposite of the high pressure turbine (28) and proximate the intake channel (54), the electric machine (74, 74a, 74b) in heat exchange communication with the intake flow of air such that the electric machine (74, 74a, 74b) transfers heat to the incoming flow of air within the intake channel (54) when the electric machine (74, 74a, 74b) is operated.
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公开(公告)号：EP4386182A2
公开(公告)日：2024-06-19
申请号：EP24173191.8
申请日：2022-01-10
申请人： General Electric Company , General Electric Company Polska Sp. Z o.o , General Electric Deutschland Holding GmbH
发明人： CZARNIK, Miroslaw , PAZINSKI, Adam Tomasz , DROZD, Bartlomiej , ZATORSKI, Darek , GRUNWALD, Maciej Krzysztof , OSAMA, Mohamed , YAGIELSKI, John R.
IPC分类号： F01D25/16
CPC分类号： F01D15/10 , F02C7/32 , F01D25/162 , F05D2220/7620130101 , F05D2260/9820130101 , F01D9/065 , F02C7/06 , Y02T50/60
摘要： An electrical machine includes a stator assembly (302) coupled to an engine stator component of a propulsion engine (100). The stator assembly includes a stator support assembly (308) fixedly attached to the engine stator component and a stator (314) disposed on the stator support structure. An electrical machine shaft (502) is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame (514) extends from the propulsion engine, the bearing support frame defining a bearing cavity (520) in conjunction with the electrical machine shaft. Electrical machine bearings (522, 524) radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor (346) is attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.
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公开(公告)号：EP4361425A2
公开(公告)日：2024-05-01
申请号：EP24163075.5
申请日：2022-02-17
申请人： General Electric Company , General Electric Company Polska Sp. Z o.o , General Electric Deutschland Holding GmbH
IPC分类号： F02C7/32
CPC分类号： B64D33/00 , B64D27/24 , F02C7/32 , F05D2220/76620130101 , F05D2260/3120130101 , F02K1/04 , Y02T50/60 , B64D27/026
摘要： A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.
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公开(公告)号：EP3699403A1
公开(公告)日：2020-08-26
申请号：EP20169012.0
申请日：2017-10-12
摘要： A method for manufacturing an inlet frame (54) of a gas turbine engine (10), the method comprising:
depositing a layer of additive material on a bed of an additive manufacturing machine; and
selectively directing energy from an energy source onto the layer of additive material to fuse a portion of the additive material and form the inlet frame comprising:
a forward annular body (102);
a rear annular body (104) spaced apart from the forward annular body (102) to define an inlet passageway (106);
an annular heating plenum (84) defined by the forward annular body (102); and
a fluid supply conduit (138) defining a hot fluid passageway, the hot fluid passageway providing fluid communication between the annular heating plenum (84) and a hot air source (150) for providing a flow of heated fluid to the annular heating plenum (84).-
公开(公告)号：EP3450722A1
公开(公告)日：2019-03-06
申请号：EP17461597.1
申请日：2017-08-31
发明人： GOULD, Kenneth Arthur , SHAMIM, Abdus , DEKOWSKI, Jaroslaw Henryk , HANCE, Piotr Sebastian , TKACZYK, Przemyslaw Slawomir , FABER, Marcin Pawel , KRYSZTOPA, Adam , BAR, Piotr Lech , CHELSTOWSKI, Krzysztof , GONYOU, Craig Alan , PARKS, Robert John
摘要： A gas turbine engine (100) having an improved air delivery system (400) that includes features for pressurizing and/or cooling various components of the engine (100) while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.
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公开(公告)号：EP3444447A1
公开(公告)日：2019-02-20
申请号：EP17461587.2
申请日：2017-08-14
IPC分类号： F01D25/02
摘要： An inlet frame (54) and a method (300) of additively manufacturing the same are provided. The inlet frame (54) includes a forward annular body (102) spaced apart from a rear annular body (104) to define an inlet passageway (106) in fluid communication with a compressor inlet (108). Inlet frame (54) defines one or more integral annular heating plenums (84, 186) in fluid communication with a hot air source (150) for heating regions of the inlet frame that are prone to icing conditions.
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公开(公告)号：EP3444446B1
公开(公告)日：2020-04-15
申请号：EP17196072.7
申请日：2017-10-12
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8.发明授权Circuit Breaker Zone Selective Interlock For Differentiated Faults And Method Of Operation 有权隔离范围内选择用于各种错误和操作程序锁
公开(公告)号：EP2110919B1
公开(公告)日：2015-01-07
申请号：EP09157489.7
申请日：2009-04-07
发明人： Vicente, Nataniel Barbosa , Culler, Mark Fredrick , Lenhart, Brian Patrick , Valdes, Marcelo Esteban
IPC分类号： H02H7/30
CPC分类号： H02H7/30
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9.发明公开Circuit Breaker Zone Selective Interlock For Differentiated Faults And Method Of Operation 有权隔离范围内选择用于各种错误和操作程序锁
公开(公告)号：EP2110919A3
公开(公告)日：2012-11-21
申请号：EP09157489.7
申请日：2009-04-07
发明人： Vicente, Nataniel Barbosa , Culler, Mark Fredrick , Lenhart, Brian Patrick , Valdes, Marcelo Esteban
IPC分类号： H02H7/30
CPC分类号： H02H7/30
摘要： A circuit breaker system and method having zone selective interlock features is provided. The system and method include the transmission of a selective interlock signal from a downstream circuit breaker to an upstream circuit breaker in the event a first or second fault condition is detected. The upstream circuit breaker upon receipt of this signal changes the response of the second circuit breaker depending on whether the first or second fault condition has been detected.
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公开(公告)号：EP4361425A3
公开(公告)日：2024-06-26
申请号：EP24163075.5
申请日：2022-02-17
申请人： General Electric Company , General Electric Company Polska Sp. Z o.o , General Electric Deutschland Holding GmbH
IPC分类号： B64D27/33 , B64D27/351 , B64D35/024 , B64D33/00 , F02C7/32 , F02K1/04 , B64D27/359 , B64D27/357 , B64D27/31
CPC分类号： B64D33/00 , F02C7/32 , F05D2220/76620130101 , F05D2260/3120130101 , F02K1/04 , Y02T50/60 , B64D27/31 , B64D27/351 , B64D27/357 , B64D27/359 , B64D35/024 , B64D27/33
摘要： A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.
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