-
公开(公告)号：EP3418507A1
公开(公告)日：2018-12-26
申请号：EP17461548.4
申请日：2017-06-19
Applicant: General Electric Company Polska Sp. Z o.o
Inventor： IGLEWSKI, Tomasz
CPC classification number: F02K1/82 , B64D15/04 , B64D33/04 , F01D25/02 , F01D25/30 , F02C6/18 , F02C7/047 , F02K1/04 , F02K1/78 , F05D2210/33 , F05D2220/323 , F05D2220/324 , F05D2240/127 , F05D2240/128 , F05D2250/52 , F05D2260/2212
Abstract: An apparatus and method for an exhaust assembly for a turbine engine including a reverse flow portion. The exhaust assembly can include an exhaust stub extending between an exhaust collector and an exhaust outlet to define an exhaust conduit having the reverse flow portion. A flow of combustion gases can exit the engine and travel through the exhaust assembly. The exhaust assembly can be applied to a turboprop engine.
-
公开(公告)号：EP4491597A1
公开(公告)日：2025-01-15
申请号：EP24186553.4
申请日：2024-07-04
Inventor： JASICZEK, Michal , SINHA, Shatil , KESHAVAN, Hrishikesh , GEMEINHARDT, Gregory Carl , GRAVES, John Harvey , LIN, Wendy Wenling
Abstract: A geopolymer composite material (200) includes a geopolymer resin (202), a fibrous reinforcement material (204) embedded in the geopolymer resin (202) for reinforcing the geopolymer resin (202), and a protective coating material (206) covering the fibrous reinforcement material (204) embedded in the geopolymer resin (202) to provide a coated fibrous reinforcement material (208). Further, the geopolymer resin (202) and the coated fibrous reinforcement material (208) are combined together to form a prepreg (210) containing the geopolymer resin (202) being pre-impregnated into the coated fibrous reinforcement material (208) and being curable into a solid matrix.
-
公开(公告)号：EP4386182A3
公开(公告)日：2024-10-16
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.
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：EP4435235A1
公开(公告)日：2024-09-25
申请号：EP24151687.1
申请日：2024-01-12
Applicant: General Electric Company Polska Sp. Z o.o
Inventor： OLCZAK, Dariusz
CPC classification number: F01D17/162 , F01D11/001 , F01D11/04 , F01D11/02 , F01D9/065 , F05D2240/12520130101 , F02C3/145 , F05D2220/32420130101 , F05D2220/32520130101 , F01D25/02 , F01D9/041
Abstract: A compressor (20) comprises a rotor shaft (30) including a forward end portion (70). The forward end portion (70) defines an outer surface (72). A first row of compressor rotor blades (74) is coupled to the rotor shaft (30) downstream from the forward end portion (70). An outer casing (76) at least partially surrounds the first row of compressor rotor blades (74) and the outer surface (72) of the forward end portion (70) of the rotor shaft (30). The outer casing (76) at least partially defines an inlet (78) to the compressor (20). An inlet guide vane (100) comprises a mounting portion (102), a tip portion (106), a leading-edge portion (108), and a trailing-edge portion (110). The mounting portion (102) is coupled to the outer casing (76) upstream from the first row of compressor rotor blades (74). The tip portion (106) extends towards the outer surface (72) of the forward end portion (70) of the rotor shaft (30). A radial gap (112) is defined between the tip portion (106) and the outer surface (72).
-
公开(公告)号：EP4054061A3
公开(公告)日：2022-09-28
申请号：EP22150709.8
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 Krzyztof , OSAMA, Mohamed , YAGIELSKI, John
Abstract: An electrical machine includes a stator assembly (302) coupled to an engine stator component of a propulsion engine (100). The stator assembly (302) includes a stator support assembly (308) fixedly attached to the engine stator component and a stator (314) disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly (304) including a rotor support structure (338) connected to a shaft of the propulsion engine (100) and a rotor (346) attached to the rotor support structure (338) such that the rotor (346) is disposed radially inward of the stator (314). The rotor (346) exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.
-
Patent Agency Ranking
公开(公告)号：EP3862537A1
公开(公告)日：2021-08-11
申请号：EP20461510.8
申请日：2020-02-10
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Bulsiewicz, Tomasz , Rzeszutek, Leszek , Stanczyk, Maciej , Olczak, Dariusz , Stec, Jaroslaw
Abstract: A turbine nozzle segment (1) for a gas turbine engine comprising an outer band (2) comprising a cooling air inlet (9), an inner band (3) comprising a first cooling air outlet (24), at least one nozzle airfoil (10) comprising a pressure sidewall (7), a suction sidewall (8), a leading edge (4) and a trailing edge (6), wherein the nozzle airfoil (10) comprises cooling bores (26) arranged within the trailing edge (6), a cooling flow passage (12) in fluid communication with the cooling air inlet (9) that delivers the cooling air into the cooling flow passage (12) as cooling air stream, a first integral rib (15) protruding from the inner band (3) for defining a first channel (18) and a second channel (19) within the cooling flow passage (12), a deflector (14) arranged at the end the first integral rib (15) and configured for dividing flow of the cooling air stream into a first cooling air stream and a second cooling air stream, wherein the first and second cooling air streams are first and second cooling air jet streams, wherein the deflector (14) is configured to deflect the first cooling air jet stream obliquely to the suction sidewall (8) in the first channel (18) of the cooling flow passage (12), and the first channel (18) is configured to transport the first cooling air jet stream along said first channel (18) in a swirly flow.
-
公开(公告)号：EP3444441B1
公开(公告)日：2020-04-08
申请号：EP17196075.0
申请日：2017-10-12
Inventor： SLAWINSKA, Estera , KORZEPSKI, Krzysztof , KOLODZIEJCZYK, Artur , MANTEIGA, John Alan
IPC: F01D9/04 , F01D25/00 , F02C7/04 , B29C64/153
-
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
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: B64D27/33 , B64D27/351 , B64D35/024 , B64D33/00 , F02C7/32 , F02K1/04 , B64D27/359 , B64D27/357 , B64D27/31
CPC classification number: B64D33/00 , F02C7/32 , F05D2220/76620130101 , F05D2260/3120130101 , F02K1/04 , Y02T50/60 , B64D27/31 , B64D27/351 , B64D27/357 , B64D27/359 , B64D35/024 , B64D27/33
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：EP3444446A1
公开(公告)日：2019-02-20
申请号：EP17196072.7
申请日：2017-10-12
Inventor： SLAWINSKA, Estera , KORZEPSKI, Krzysztof , KOLODZIEJCZYK, Artur , MANTEIGA, John Alan
Abstract: An inlet frame (54) and a method (300) of heating an inlet screan of an inlet frame 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 (54) that are prone to icing conditions.
-
公开(公告)号：EP3444441A1
公开(公告)日：2019-02-20
申请号：EP17196075.0
申请日：2017-10-12
Inventor： SLAWINSKA, Estera , KORZEPSKI, Krzysztof , KOLODZIEJCZYK, Artur , MANTEIGA, John Alan
IPC: F01D9/04 , F01D25/00 , F02C7/04 , B29C64/153
Abstract: An inlet frame (54) and a method (200) 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). The inlet frame (54) defines integral wash manifolds (130) and discharge ports (140) for directing a flow of wash fluid directly through the compressor inlet (108).
-
-
-
-
-
-
-
-
-
Search Results
125
records
(took 0.033 seconds)
