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公开(公告)号：WO2022066471A1
公开(公告)日：2022-03-31
申请号：PCT/US2021/050278
申请日：2021-09-14
Inventor： EDRMENGER, Rodrigo Rodriguez , SELMEIER, Rudolph , BALADI, Mehdi Milani , ELSZKOWSKI, Jacek Marian
Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.
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公开(公告)号：US20250129745A1
公开(公告)日：2025-04-24
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：US20250101918A1
公开(公告)日：2025-03-27
申请号：US18973680
申请日：2024-12-09
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 thereby 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：US20250019304A1
公开(公告)日：2025-01-16
申请号：US18350165
申请日：2023-07-11
Inventor： Michal Jasiczek , Shatil Sinha , Hrishikesh Keshavan , Gregory Carl Gemeinhardt , John Harvey Graves , Wendy Wenling Lin
Abstract: A geopolymer composite material includes a geopolymer resin, a fibrous reinforcement material embedded in the geopolymer resin for reinforcing the geopolymer resin, and a protective coating material covering the fibrous reinforcement material embedded in the geopolymer resin to provide a coated fibrous reinforcement material. Further, the geopolymer resin and the coated fibrous reinforcement material are combined together to form a prepreg containing the geopolymer resin being pre-impregnated into the coated fibrous reinforcement material and being curable into a solid matrix.
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公开(公告)号：US20240418096A1
公开(公告)日：2024-12-19
申请号：US18357410
申请日：2023-07-24
Inventor： Rajesh Kumar , Sesha Subramanian , Vaishnav Raghuvaran , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine includes a compressor section comprising a compressor, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, the compressor comprising an aft-most compressor stage; a spool drivingly coupled to the compressor; a stage of stator vanes located downstream of the aft-most compressor stage; and a stator case, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the stage of stator vanes including a first stator vane defining a fluid passage, and the stator case defining a plenum and a supplemental airflow passage, the plenum in fluid communication with the fluid passage in the first stator vane, the supplemental airflow passage in fluid communication with the plenum and the rotor cavity for proving an airflow to the rotor cavity
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Patent Agency Ranking
公开(公告)号：US20240344460A1
公开(公告)日：2024-10-17
申请号：US18644422
申请日：2024-04-24
Inventor： Michal Tomasz Kuropatwa , Adam Wojciech Deskiewicz , Robert Kaminski , Adam Kunicki , Nicholas Joseph Kray
CPC classification number: F01D5/027 , F01D5/30 , F05D2220/32 , F05D2240/24 , F05D2260/96
Abstract: 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
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
CPC classification number: H02K7/1815 , H02K1/12 , H02K7/003 , H02K7/08 , H02K7/14
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：US20240052755A1
公开(公告)日：2024-02-15
申请号：US18081813
申请日：2022-12-15
Inventor： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
CPC classification number: F01D17/162 , F01D7/00 , F05D2240/12 , F05D2220/323 , F05D2240/20
Abstract: 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
Inventor： Tomasz Edward Berdowski , Mirosław Sobaniec , Maciej Czerwiński , Ashish Sharma , Piotr Jerzy Kuliński
CPC classification number: F01D9/041 , F01D9/065 , F01D25/26 , F05D2240/128 , F05D2250/185 , F05D2250/323 , F05D2250/324 , F05D2260/232 , F05D2260/601
Abstract: 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
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
IPC: F01D11/24
CPC classification number: F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
Abstract: 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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