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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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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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公开(公告)号：US10801365B2
公开(公告)日：2020-10-13
申请号：US15906466
申请日：2018-02-27
Applicant: General Electric Company Polska sp. z.o.o
Inventor： Leszek Marek Rzeszutek , Dariusz Olczak , Grzegorz Maciej Kaczmarek , Tomasz Bulsiewicz , Maciej Michal Stanczyk , Adam Tralewski
Abstract: A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.
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公开(公告)号：US12283870B2
公开(公告)日：2025-04-22
申请号：US18398671
申请日：2023-12-28
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Mirosław Czarnik , Adam Tomasz Paziński , Bartłomiej 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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Patent Agency Ranking
公开(公告)号：US20250122831A1
公开(公告)日：2025-04-17
申请号：US18990439
申请日：2024-12-20
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
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公开(公告)号：US12276227B1
公开(公告)日：2025-04-15
申请号：US18592663
申请日：2024-03-01
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A screen for an aeronautical gas turbine engine includes a plurality of first filaments and a plurality of second filaments. The plurality of second filaments define a plurality of openings with the plurality of first filaments. The plurality of first filaments and the plurality of second filaments define a first arrangement in which the plurality of first filaments are perpendicular to the plurality of second filaments. Upon application of a force to the screen, at least some of the plurality of first filaments and at least some of the plurality of second filaments are configured to translate from the first arrangement to a second arrangement in which a size of at least one of the openings is configured to change from a first size to a second size.
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公开(公告)号：US12227284B2
公开(公告)日：2025-02-18
申请号：US18415155
申请日：2024-01-17
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Krzysztof Jedliński , Mirosław Sobaniec , Mateusz Gołdyn , Tomasz Biwański , Tomasz Kosieradzki , Dariusz Łodkowski
Abstract: A pitch change mechanism for an aircraft engine includes a unison ring, a plurality of crankshafts coupled to the unison ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the unison ring, and an actuator cylinder and an actuator piston. The actuator cylinder is coupled to the inner shaft and is configured to move relative to the actuator piston along a longitudinal axis of the pitch change mechanism. Movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around a longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.
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公开(公告)号：US20250052193A1
公开(公告)日：2025-02-13
申请号：US18925916
申请日：2024-10-24
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
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公开(公告)号：US20250019065A1
公开(公告)日：2025-01-16
申请号：US18415155
申请日：2024-01-17
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Krzysztof Jedlinski , Miroslaw Sobaniec , Mateusz Goldyn , Tomasz Biwanski , Tomasz Kosieradzki , Dariusz Lodkowski
Abstract: A pitch change mechanism for an aircraft engine includes a unison ring, a plurality of crankshafts coupled to the unison ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the unison ring, and an actuator cylinder and an actuator piston. The actuator cylinder is coupled to the inner shaft and is configured to move relative to the actuator piston along a longitudinal axis of the pitch change mechanism. Movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around a longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.
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