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公开(公告)号：US12123324B2
公开(公告)日：2024-10-22
申请号：US18343013
申请日：2023-06-28
Inventor： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC: F01D9/02
CPC classification number: F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
Abstract: 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：US20240318577A1
公开(公告)日：2024-09-26
申请号：US18307450
申请日：2023-04-26
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Dariusz Olczak
CPC classification number: F01D25/02 , F02C7/04 , F02K3/00 , F05D2220/36
Abstract: A compressor comprises a rotor shaft including a forward end portion. The forward end portion defines an outer surface. A first row of compressor rotor blades is coupled to the rotor shaft downstream from the forward end portion. An outer casing at least partially surrounds the first row of compressor rotor blades and the outer surface of the forward end portion of the rotor shaft. The outer casing at least partially defines an inlet to the compressor. An inlet guide vane comprises a mounting portion, a tip portion, a leading-edge portion, and a trailing-edge portion. The mounting portion is coupled to the outer casing upstream from the first row of compressor rotor blades. The tip portion extends towards the outer surface of the forward end portion of the rotor shaft. A radial gap is defined between the tip portion and the outer surface.
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23.发明公开公开(公告)号：US20240167422A1
公开(公告)日：2024-05-23
申请号：US18378974
申请日：2023-10-11
Inventor： Adam Tomasz Pazinski , Miroslaw Sobaniec , Christopher N. Delametter
CPC classification number: F02C7/18 , F02C6/00 , F05D2220/76
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine. The first cooling airflow path is in communication with a second cooling airflow path located outside the enclosure that at least partially defines a second cooling airflow buffer cavity at least partially around the enclosure. A cooling duct provides pressurized air to the first cooling airflow path such that the air flows along both the first cooling airflow path and the second cooling airflow path providing the first cooling airflow buffer cavity and the second cooling airflow buffer cavity.
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公开(公告)号：US20240051656A1
公开(公告)日：2024-02-15
申请号：US18085112
申请日：2022-12-20
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
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25.发明授权公开(公告)号：US11891954B2
公开(公告)日：2024-02-06
申请号：US17400936
申请日：2021-08-12
Inventor： Adam Tomasz Paziński , Miroslaw Sobaniec , Christopher N. Delametter
CPC classification number: F02C7/18 , F02C6/00 , F05D2220/76
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine. The first cooling airflow path is in communication with a second cooling airflow path located outside the enclosure that at least partially defines a second cooling airflow buffer cavity at least partially around the enclosure. A cooling duct provides pressurized air to the first cooling airflow path such that the air flows along both the first cooling airflow path and the second cooling airflow path providing the first cooling airflow buffer cavity and the second cooling airflow buffer cavity.
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Patent Agency Ranking
公开(公告)号：US20230366908A1
公开(公告)日：2023-11-16
申请号：US17987566
申请日：2022-11-15
Applicant: GENERAL ELECTRIC COMPANY POLSKA SP. Z O.O
Inventor： Tomasz Iglewski , Aleksander Piotr Pasieczny
IPC: G01P5/14
Abstract: Methods, apparatus, and articles of manufacture to measure pressure of a fluid are disclosed. An example apparatus to measure a total pressure of a fluid includes a probe head including a plurality of ports, the plurality of ports fluidly coupled to a measurement chamber, and a pressure sensor operatively coupled to the measurement chamber to measure the total pressure inside the measurement chamber, the total pressure corresponding to fluid flow through one of the plurality of ports.
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公开(公告)号：US20230366324A1
公开(公告)日：2023-11-16
申请号：US18225933
申请日：2023-07-25
Inventor： Maciej Grunwald , Lukasz Maciej Janczak , Adam Tomasz Pazinski , Pawel Piotr Hanczewski , Mohamed Osama
Abstract: A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.
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公开(公告)号：US11788425B2
公开(公告)日：2023-10-17
申请号：US17561156
申请日：2021-12-23
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
CPC classification number: F01D11/18 , F01D9/04 , F01D11/24 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2260/201
Abstract: A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.
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29.发明授权公开(公告)号：US11719122B2
公开(公告)日：2023-08-08
申请号：US17170215
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Adam Tomasz Paziński , Tomasz Jan Bulsiewicz , Bartlomiej Drozd , Miroslaw Czarnik , Mohamed Osama , John R. Yagielski
CPC classification number: F01D25/12 , F01D15/10 , F02C7/24 , F05D2220/76 , F05D2260/213 , F05D2260/231 , H02K5/203 , H02K7/1823 , H02K9/19
Abstract: 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 comprising an outer electrical machine stator and an inner electrical machine rotor is provided. The method includes directing a liquid coolant radially inward past the outer electrical machine stator and toward an inner electrical machine rotor using a coolant passageway. The liquid coolant is directed onto and/or through one or both of the inner electrical machine rotor and a rotor support thereby removing heat from the inner electrical machine rotor.
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公开(公告)号：US20220255401A1
公开(公告)日：2022-08-11
申请号：US17170221
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Miroslaw Czarnik , Adam Tomasz Pazinski , Bartlomiej Drozd , Darek Zatorski , Maciej Krzysztof Grunwald , Mohamed Osama , John R. Yagielski
Abstract: 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 a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.
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