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公开(公告)号：US20240344460A1
公开(公告)日：2024-10-17
申请号：US18644422
申请日：2024-04-24
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：US20240178721A1
公开(公告)日：2024-05-30
申请号：US18398671
申请日：2023-12-28
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
CPC分类号： H02K7/1815 , H02K1/12 , H02K7/003 , H02K7/08 , H02K7/14
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 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：US20240052755A1
公开(公告)日：2024-02-15
申请号：US18081813
申请日：2022-12-15
发明人： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
CPC分类号： F01D17/162 , F01D7/00 , F05D2240/12 , F05D2220/323 , F05D2240/20
摘要： A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
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公开(公告)号：US11885240B2
公开(公告)日：2024-01-30
申请号：US17380139
申请日：2021-07-20
发明人： Tomasz Edward Berdowski , Mirosław Sobaniec , Maciej Czerwiński , Ashish Sharma , Piotr Jerzy Kuliński
CPC分类号： F01D9/041 , F01D9/065 , F01D25/26 , F05D2240/128 , F05D2250/185 , F05D2250/323 , F05D2250/324 , F05D2260/232 , F05D2260/601
摘要： A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit.
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公开(公告)号：US11859500B2
公开(公告)日：2024-01-02
申请号：US17561203
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： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
摘要： A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.
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公开(公告)号：US20230407758A1
公开(公告)日：2023-12-21
申请号：US18452764
申请日：2023-08-21
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
摘要： A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.
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公开(公告)号：US20230358144A1
公开(公告)日：2023-11-09
申请号：US18081266
申请日：2022-12-14
发明人： Tomasz Iglewski
IPC分类号： F01D7/00
CPC分类号： F01D7/00 , F05D2220/36 , F05D2220/32
摘要： A fan assembly is provided for a gas turbine engine including: a plurality of fan blades, the plurality of fan blades including a first fan blade; and an actuation assembly including: a first linkage connected to the first fan blade; a first pivot point rotatable with the first fan blade, the first linkage further connected to the first pivot point; a control point moveable relative to the first pivot point and connected to the first linkage for changing a relative position of the first fan blade within the plurality of fan blades.
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公开(公告)号：US20230146084A1
公开(公告)日：2023-05-11
申请号：US17561156
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： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
CPC分类号： F01D11/18 , F01D9/04 , F01D25/24 , F05D2220/32
摘要： 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：US20220341346A1
公开(公告)日：2022-10-27
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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公开(公告)号：US20180215478A1
公开(公告)日：2018-08-02
申请号：US15869823
申请日：2018-01-12
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/022 , B64D2033/0293 , F02C7/055 , F05D2250/10 , F05D2260/607 , Y02T50/675
摘要： An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.
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