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公开(公告)号：US12091984B2
公开(公告)日：2024-09-17
申请号：US18081844
申请日：2022-12-15
发明人： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC分类号： F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
摘要： A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US20240239504A1
公开(公告)日：2024-07-18
申请号：US18307172
申请日：2023-04-26
摘要： An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction, a leading edge, a trailing edge, and a chord extending from the leading edge to the trailing edge, the pylon fairing including a maximum thickness portion along the lengthwise direction of the pylon fairing located between 10% and 60% of the chord.
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公开(公告)号：US20240117741A1
公开(公告)日：2024-04-11
申请号：US18081844
申请日：2022-12-15
发明人： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC分类号： F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
摘要： A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
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公开(公告)号：US20230340885A1
公开(公告)日：2023-10-26
申请号：US18343013
申请日：2023-06-28
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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公开(公告)号：US20230147089A1
公开(公告)日：2023-05-11
申请号：US17561182
申请日：2021-12-23
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Tomasz Edward Berdowski , Ashish Sharma , Raymond Floyd Martell , Piotr Jerzy Kulinski , Lukasz Maciej Janczak
CPC分类号： F01D11/18 , F01D25/26 , F05D2240/11 , F05D2260/38
摘要： A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.
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公开(公告)号：US20230139068A1
公开(公告)日：2023-05-04
申请号：US18146763
申请日：2022-12-27
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
发明人： Miroslaw Czarnik , Adam Tomasz Pazinski , Bartlomiej Drozd , Darek Zatorski , Maciej Krzysztof Grunwald , Mohamed Osama , John R. Yagielski
摘要： An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft 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 extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor 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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7.发明授权公开(公告)号：US11641144B2
公开(公告)日：2023-05-02
申请号：US17170216
申请日：2021-02-08
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
摘要： A method of removing heat from an electrical machine located in a gas turbine engine at least partially inward of a core airflow path in a radial direction, the electrical machine including an outer generator stator and an inner generator rotor is provided. The method includes directing cooling airflow radially through an airflow passageway to an enclosure at least partially defined by a thermal shield at least partially around the electrical machine. The cooling airflow is directed radially inward past the outer generator stator and toward the inner generator rotor using a cooling manifold thereby removing heat from the generator rotor.
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公开(公告)号：US11492924B1
公开(公告)日：2022-11-08
申请号：US17381677
申请日：2021-07-21
发明人： Miroslaw Czarnik , Adam Tomasz Pazinski , Pawel Zdrojewski , Christopher N. Delametter , Lukasz Maciej Janczak , Maciej Krzysztof Grunwald , Scott Alan Schimmels
摘要： 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.
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9.发明申请公开(公告)号：US20220255396A1
公开(公告)日：2022-08-11
申请号：US17170216
申请日：2021-02-08
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
摘要： A method of removing heat from an electrical machine located in a gas turbine engine at least partially inward of a core airflow path in a radial direction, the electrical machine including an outer generator stator and an inner generator rotor is provided. The method includes directing cooling airflow radially through an airflow passageway to an enclosure at least partially defined by a thermal shield at least partially around the electrical machine. The cooling airflow is directed radially inward past the outer generator stator and toward the inner generator rotor using a cooling manifold thereby removing heat from the generator rotor.
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公开(公告)号：US20220251965A1
公开(公告)日：2022-08-11
申请号：US17170229
申请日：2021-02-08
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
发明人： Miroslaw Czarnik , Adam Tomasz Pazinski , Bartlomiej Drozd , Darek Zatorski , Maciej Krzysztof Grunwald , Mohamed Osama , John R. Yagielski
摘要： An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft 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 extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor 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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