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公开(公告)号：US20240141805A1
公开(公告)日：2024-05-02
申请号：US17976302
申请日：2022-10-28
发明人： Lawrence A. Binek , Sean R. Jackson
摘要： A manufacturing method is provided during which a body is additively manufactured. The body includes an engine case for a gas turbine engine, a support structure and an aperture. The support structure projects out from the engine case. The support structure includes a lattice, a wall and an internal volume. The wall surrounds the lattice. The internal volume is within the support structure along the lattice. The internal volume is filled with powder. The aperture is at an intersection between the engine case and the support structure. The powder is extracted from the internal volume through the aperture.
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公开(公告)号：US20240077030A1
公开(公告)日：2024-03-07
申请号：US17902307
申请日：2022-09-02
发明人： Lawrence A. Binek , Sean R. Jackson
摘要： An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.
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公开(公告)号：US11739690B2
公开(公告)日：2023-08-29
申请号：US17746206
申请日：2022-05-17
发明人： Lawrence A. Binek , Jesse R. Boyer , Evan J. Butcher , Michael Winter , Jesus A. Garcia , Sean R. Jackson
CPC分类号： F02C7/055 , B22F10/28 , F05D2230/31 , F05D2260/607 , B22F2999/00 , B22F10/28 , B22F3/1115
摘要： A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.
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公开(公告)号：US20230055939A1
公开(公告)日：2023-02-23
申请号：US17408049
申请日：2021-08-20
发明人： Lawrence A. Binek , Sean R. Jackson
摘要： A monolithic combustion liner for use in a gas turbine engine includes fuel channels integrated into the wall of the combustion liner. The integrated fuel channels can have an aerodynamic shape to reduce flow losses of cooling air flowing around the exterior of the combustion liner. The monolithic combustion liner allows more cooling air to flow around the combustion liner, increasing the cooling of the combustor region of the gas-turbine engine.
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公开(公告)号：US20220099001A1
公开(公告)日：2022-03-31
申请号：US17034854
申请日：2020-09-28
发明人： Lawrence A. Binek , Sean R. Jackson
IPC分类号： F01D25/24
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case, a first transceiver and a second transceiver. The turbine engine case includes a case wall and a waveguide. The waveguide is formed integral with the case wall. The waveguide includes a waveguide channel. The second transceiver is configured to be in signal communication with the first transceiver through the waveguide channel.
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公开(公告)号：US12072101B2
公开(公告)日：2024-08-27
申请号：US17675584
申请日：2022-02-18
CPC分类号： F23R3/28 , F02C7/222 , F23R3/283 , F05D2220/32 , F05D2240/36
摘要： An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector receptacle. The injector receptacle extends longitudinally through the engine structure along a centerline. The fuel injector is received by the injector receptacle. The fuel injector includes a fuel nozzle and a splash plate. The fuel nozzle is configured to direct fuel out of the fuel injector to impinge against the splash plate.
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公开(公告)号：US12066188B2
公开(公告)日：2024-08-20
申请号：US17214730
申请日：2021-03-26
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23R2900/00012
摘要： An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.
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公开(公告)号：US20230265761A1
公开(公告)日：2023-08-24
申请号：US17675564
申请日：2022-02-18
CPC分类号： F01D5/18 , F01D25/12 , F02C7/12 , F05D2220/32 , F05D2260/20
摘要： An assembly is provided for a gas turbine engine. This assembly includes a compressor rotor, a turbine rotor and a cooling circuit. The compressor rotor includes a gas path surface. The turbine rotor is rotatable with the compressor rotor about a rotational axis. The cooling circuit includes an inlet in the gas path surface. The cooling circuit extends from the inlet, through the compressor rotor and into the turbine rotor.
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公开(公告)号：US11441451B2
公开(公告)日：2022-09-13
申请号：US17034854
申请日：2020-09-28
发明人： Lawrence A. Binek , Sean R. Jackson
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case, a first transceiver and a second transceiver. The turbine engine case includes a case wall and a waveguide. The waveguide is formed integral with the case wall. The waveguide includes a waveguide channel. The second transceiver is configured to be in signal communication with the first transceiver through the waveguide channel.
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公开(公告)号：US20240076033A1
公开(公告)日：2024-03-07
申请号：US17902245
申请日：2022-09-02
CPC分类号： B64C21/08 , F02C6/08 , B64C2230/06 , F05D2220/323 , F05D2260/605 , F05D2260/606
摘要： An assembly is provided for an aerial vehicle. This assembly includes an airframe and a fluid circuit. The airframe includes a body and an airfoil projecting out from the body. The airfoil includes a first surface and a first aperture in the first surface. The fluid circuit is configured to bleed gas from a gas turbine engine mounted to the airframe to provide control gas. The fluid circuit is configured to selectively direct the control gas to the first aperture.
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