公开(公告)号：EP4283835A1

公开(公告)日：2023-11-29

申请号：EP23163763.8

申请日：2023-03-23

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH ,  General Electric Company Polska Sp. Z o.o

Inventor： ERTAS, Bugra Han ,  ZIERER JR., Joseph John ,  RALLABANDI, Vandana Prabhakar ,  TORREY, David Allan ,  CRALL, David William ,  OSAMA, Mohamed ,  PAZINSKI, Adam Tomasz ,  SIBBACH, Arthur William

IPC: H02K1/20 ,  H02K9/19 ,  H02K9/10

Abstract: An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142) , wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).

公开(公告)号：EP3650656A1

公开(公告)日：2020-05-13

申请号：EP19213297.5

申请日：2017-09-15

Applicant: General Electric Company Polska sp. z o.o.

Inventor： CZARNECKI, Michal ,  KOWALCZYK, Michal ,  PACHOTA, Piotr ,  KRYSZTOPA, Adam

IPC: F01D11/00

Abstract: An inner band assembly (120) for a turbine nozzle (104) of a rotary machine (10) that includes a centerline axis (36) comprises a platform portion (140), a first flange (142) coupled to said platform portion, and a second flange (144) coupled to said first flange. The first flange is obliquely oriented with respect to the centerline axis and t he second flange is obliquely oriented with respect to the first flange.

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

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o.

Inventor： SLAWINSKA, Estera ,  KORZEPSKI, Krzysztof ,  KOLODZIEJCZYK, Artur ,  MANTEIGA, John Alan

IPC: F01D25/02 ,  B64D15/04 ,  F02C7/047 ,  F02C7/055

公开(公告)号：EP3418195A1

公开(公告)日：2018-12-26

申请号：EP17461552.6

申请日：2017-06-21

Applicant: General Electric Company Polska sp. z o.o.

Inventor： IGLEWSKI, Tomasz

IPC: B64D27/12 ,  B64D33/04 ,  F01D25/30 ,  B64D33/02

CPC classification number: B64D33/04 ,  B64D27/12 ,  B64D2033/0293 ,  F01D25/30

Abstract: An aircraft engine assembly (15) can include an engine (16) having an exhaust turbine with drive shaft (21) and exhaust collector (25), a propeller (17) rotationally coupled to the drive shaft (21) and defining a rotational axis (20), and an exhaust stub (30) to direct exhaust gases away from the aircraft (1).

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

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o.

Inventor： SIBBACH, Arthur William ,  PAZINSKI, Adam Tomasz

IPC: F02C6/20 ,  F02C7/18

CPC classification number: F05D2220/7620130101 ,  F02C3/145 ,  F02C3/103 ,  F01D15/10 ,  F02C7/18 ,  F05D2260/21320130101 ,  F02C6/206

Abstract: 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.

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

Applicant: General Electric Company ,  General Electric Company Polska Sp. Z o.o ,  General Electric Deutschland Holding GmbH

Inventor： CZARNIK, Miroslaw ,  PAZINSKI, Adam Tomasz ,  DROZD, Bartlomiej ,  ZATORSKI, Darek ,  GRUNWALD, Maciej Krzysztof ,  OSAMA, Mohamed ,  YAGIELSKI, John R.

IPC: F01D25/16

CPC classification number: F01D15/10 ,  F02C7/32 ,  F01D25/162 ,  F05D2220/7620130101 ,  F05D2260/9820130101 ,  F01D9/065 ,  F02C7/06 ,  Y02T50/60

Abstract: 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.

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

Applicant: General Electric Company ,  General Electric Company Polska Sp. Z o.o ,  General Electric Deutschland Holding GmbH

Inventor： OSAMA, Mohamed ,  DROZD, Bartlomiej ,  YAGIELSKI, John Russell

IPC: F02C7/32

CPC classification number: B64D33/00 ,  B64D27/24 ,  F02C7/32 ,  F05D2220/76620130101 ,  F05D2260/3120130101 ,  F02K1/04 ,  Y02T50/60 ,  B64D27/026

Abstract: 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.

公开(公告)号：EP4332351A1

公开(公告)日：2024-03-06

申请号：EP22461603.7

申请日：2022-09-05

Applicant: General Electric Company Polska Sp. Z o.o

Inventor： PAZINSKI, Adam ,  KACZMAREK, Grzegorz ,  KOSTROWSKI, Lukasz ,  MARKIEWICZ, Piotr ,  POREDA, Marek

IPC: F01D11/14 ,  F01D25/24 ,  F01D11/08

Abstract: A turbine rotor outer casing assembly (1) comprising a hanger (100) adjusted for connection to the turbine housing (21) and connected to a shroud (200), wherein the said shroud (200) is situated in the radial direction (R) between the hanger (100) and turbine blades (22), wherein the said hanger (100) has a hanger inner side (101) facing the said shroud (200) and a hanger outer side (102) facing the turbine housing (21), the said hanger (100) on the hanger outer side (102) further comprises mounting hooks (105) and each of the said mounting hooks (105) comprises an end portion (105A), bent out and extending in the longitudinal direction (L), and an intermediate portion (105B) extending in the radial direction (R), and between them is a bend (105C) having an inner side situated on the side of the turbine housing (21) cooperating therewith, the said shroud (200) being connected to the hanger (100) by means of a c-clip (106), characterized in that the hanger (100) comprises hanger stress relief means (3) formed in at least one mounting hook (105) on the inner side of the bend (105C).

公开(公告)号：EP4083391A1

公开(公告)日：2022-11-02

申请号：EP21204255.0

申请日：2021-10-22

Applicant: General Electric Company ,  General Electric Company Polska Sp. Z o.o

Inventor： CZARNIK, Miroslaw ,  PAZINSKI, Adam ,  ZDROJEWSKI, Pawel ,  DELAMETTER, Christopher ,  JANCZAK, Lukasz ,  GRUNWALD, Maciej ,  SCHIMMELS, Scott

IPC: F01D15/10 ,  F01D11/02 ,  F01D25/12 ,  F01D25/16

Abstract: In one exemplary embodiment, a gas turbine engine is provided. The gas turbine engine defines a radial direction, an axial direction, and an axis extending along the axial direction of the gas. The gas turbine engine includes: a shaft configured to rotate about the axis; an electric machine comprising a rotor coupled to and rotatable with the shaft and a stator, the rotor defining an end along the axial direction; and a cooling manifold rotatable with the rotor and positioned at the end of the rotor, the cooling manifold configured to receive a flow of cooling fluid and provide the cooling fluid to the stator during operation of the gas turbine engine.

公开(公告)号：EP4043696A1

公开(公告)日：2022-08-17

申请号：EP22150713.0

申请日：2022-01-10

Applicant: General Electric Company ,  General Electric Company Polska Sp. Z o.o ,  General Electric Deutschland Holding GmbH

Inventor： CZARNIK, Miroslaw ,  PAZINSKI, Adam Tomasz ,  DROZD, Bartlomiej ,  ZATORSKI, Darek ,  GRUNWALD, Maciej Krzysztof ,  OSAMA, Mohamed ,  YAGIELSKI, John

IPC: F01D15/10 ,  F02C7/32 ,  F01D9/06 ,  F01D25/16

Abstract: 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.