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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：JP2005324028A
公开(公告)日：2005-11-24
申请号：JP2005139267
申请日：2005-05-12
Applicant: General Electric Co
, Johns Hopkins Univ , ザ・ジョン・ホプキンス・ユニバーシティGeneral Electric Company , ゼネラル・エレクトリック・カンパニイGeneral Electric Company Inventor： GIAQUINTO RANDY OTTO J , CLINE HARVEY E , HARDY CHRISTOPHER JUDSON , DUMOULIN CHARLES L , BOTTOMLEY PAUL A
IPC: A61B5/055 , G01R33/34 , G01R33/3415 , G01R33/36 , G01V3/00
CPC classification number: G01R33/3415 , G01R33/34007
Abstract: PROBLEM TO BE SOLVED: To provide an RF coil assembly (200) for use in a multiple receive-channel MRI system.
SOLUTION: The RF coil assembly is configured as a multi-turn-element RF coil assembly (210) to operate as a surface-coil array in cooperation with the MRI system (100) which is configured to operate in a multiple-channel receive mode. In the first embodiment, the RF coil assembly (210) includes a plurality of multi-turn coil elements to receive RF signals during imaging. The multi-turn coil elements are connected to a plurality of corresponding receive-channel pre-amplifier inputs in the MRI system. In the second embodiment, the RF coil assembly includes at least one RF coil array which includes a plurality of multi-turn coil elements which receives the RF signal during imaging, the multi-turn coil elements are connected to a plurality of corresponding receive-channels corresponding of the MRI system (100).
COPYRIGHT: (C)2006,JPO&NCIPIAbstract translation: 要解决的问题：提供用于多个接收信道MRI系统中的RF线圈组件（200）。 解决方案：RF线圈组件被配置为多匝元件RF线圈组件（210），以与MRI系统（100）协作操作作为表面线圈阵列，该MRI系统（100）被配置为以多重功能 频道接收模式。 在第一实施例中，RF线圈组件（210）包括多个多匝线圈元件，用于在成像期间接收RF信号。 多匝线圈元件连接到MRI系统中的多个对应的接收通道前置放大器输入端。 在第二实施例中，RF线圈组件包括至少一个RF线圈阵列，其包括在成像期间接收RF信号的多个多匝线圈元件，多匝线圈元件连接到多个对应的接收通道 对应的MRI系统（100）。 版权所有（C）2006，JPO＆NCIPI
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公开(公告)号：JP2017506813A
公开(公告)日：2017-03-09
申请号：JP2016567167
申请日：2015-01-30
Applicant: ザ・ジェネラル・エレクトリック・カンパニーThe General Electric Company , ザ・ジェネラル・エレクトリック・カンパニーThe General Electric Company
Inventor： レスリー．トーマス．フォーキンガム
IPC: H01H33/666 , H01H33/662
CPC classification number: H01H33/666 , H01H9/20 , H01H33/38 , H01H33/6662
Abstract: 負荷および無負荷条件、ならびに任意選択で短絡条件下で電気回路をスイッチングするための真空スイッチング・デバイス(100)が開示される。具体的には、スイッチング・デバイス(100)は、真空排気されたハウジング(110)と、ハウジング内の第1の電極(122)および第2の電極(120)と、第1の電極(122)を第2の電極(120)に対して移動し、電極同士を機械的に係合および係合解除し、スイッチング機能を実施するためのアクチュエータ(144)とを備え、第1の電極(122)が真空排気されたハウジング(110)内に全体として配置され、その結果、スイッチング機能の動きがハウジング(110)内だけで行われる。スイッチング機能の動きをハウジング内だけにすることによって、真空スイッチング・デバイスの信頼性が改善される。【選択図】図5
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公开(公告)号：US20250122830A1
公开(公告)日：2025-04-17
申请号：US18990397
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：US12221893B2
公开(公告)日：2025-02-11
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
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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Patent Agency Ranking
公开(公告)号：US12091984B2
公开(公告)日：2024-09-17
申请号：US18081844
申请日：2022-12-15
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：US20240239504A1
公开(公告)日：2024-07-18
申请号：US18307172
申请日：2023-04-26
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: 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
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：US20230340885A1
公开(公告)日：2023-10-26
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：US20230147089A1
公开(公告)日：2023-05-11
申请号：US17561182
申请日：2021-12-23
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Tomasz Edward Berdowski , Ashish Sharma , Raymond Floyd Martell , Piotr Jerzy Kulinski , Lukasz Maciej Janczak
CPC classification number: F01D11/18 , F01D25/26 , F05D2240/11 , F05D2260/38
Abstract: 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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