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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
发明人： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
摘要： 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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2.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
CPC分类号： F02C7/18 , F02C6/00 , F05D2220/76
摘要： 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
发明人： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
摘要： 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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4.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
CPC分类号： F02C7/18 , F02C6/00 , F05D2220/76
摘要： 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：US11788425B2
公开(公告)日：2023-10-17
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 , F01D11/24 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2260/201
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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6.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
申请人： General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
发明人： Adam Tomasz Paziński , Tomasz Jan Bulsiewicz , Bartlomiej Drozd , Miroslaw Czarnik , Mohamed Osama , John R. Yagielski
CPC分类号： F01D25/12 , F01D15/10 , F02C7/24 , F05D2220/76 , F05D2260/213 , F05D2260/231 , H02K5/203 , H02K7/1823 , H02K9/19
摘要： 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
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
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：US4548466A
公开(公告)日：1985-10-22
申请号：US536997
申请日：1983-09-29
CPC分类号： G02B6/4202 , G02B6/4236 , G02B6/4248 , G02B6/4238
摘要： A coupling between an optical fibre (1) and an opto-electronic device e.g. a semiconductor laser (2) is located within a hermetically sealed housing (3,6). The device is supported on a header (14) mounted on the front wall (3) of the housing, the lead (16) to the device passes through the housing wall via a glass-to-metal seal (17,19,20), and the fibre is soldered into a ferrule (10) which is inserted through a boss (4) on the front housing wall. After alignment of the fibre with the device, the ferrule is clamped in position by two parallel sets of screws (11(a), 11(b)) inserted through the boss, and is then soldered to the boss. The housing, header, ferrule and metal component(s) of the glass-to-metal seal are all formed of the same metal, preferably gold-plated copper, to avoid differential expansion.
摘要翻译： 光纤（1）和光电子器件之间的耦合，例如， 半导体激光器（2）位于密封的壳体（3,6）内。 装置支撑在安装在壳体的前壁（3）上的集管（14）上，装置的引线（16）经由玻璃 - 金属密封件（17,19,20）穿过壳体壁， 并且将纤维焊接到通过前壳体壁上的凸台（4）插入的套圈（10）中。 在纤维与装置对准之后，通过插入凸台的两组平行的螺钉（11（a），11（b））将套圈夹紧就位，然后将其焊接到凸台。 玻璃对金属密封件的壳体，头部，套圈和金属部件都由相同的金属形成，优选镀金铜，以避免不同的膨胀。
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公开(公告)号：US20240280053A1
公开(公告)日：2024-08-22
申请号：US18307938
申请日：2023-04-27
CPC分类号： F02C7/18 , F01D17/12 , F02C7/04 , F05D2260/201 , F05D2260/232
摘要： 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：US20240239506A1
公开(公告)日：2024-07-18
申请号：US18316577
申请日：2023-05-12
摘要： 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 and comprising a leading edge section, the leading edge section defining a leading edge camber that varies along the lengthwise direction of the pylon fairing.
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