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公开(公告)号：US20240328355A1
公开(公告)日：2024-10-03
申请号：US18735712
申请日：2024-06-06
发明人： Scott SMITH
IPC分类号： F02C7/143 , F02C3/04 , F02C3/20 , F02C7/16 , F02C7/22 , F02C7/224 , F02C7/32 , F02C7/36 , F02C9/26
CPC分类号： F02C7/143 , F02C3/20 , F02C7/16 , F02C7/22 , F02C7/224 , F02C7/36 , F02C9/263 , F02C3/04 , F02C7/32
摘要： In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.
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公开(公告)号：US12044175B2
公开(公告)日：2024-07-23
申请号：US17944405
申请日：2022-09-14
摘要： A gas turbine facility includes: a fuel pipe connected to a fuel supply facility; a fuel supply pipe connected to a combustor of a gas turbine; a fuel treating pipe connected to a fuel treating apparatus that treats a fuel; and a three-way valve having an inlet port connected to the fuel pipe, a first outlet port connected to the fuel supply pipe, and a second outlet port connected to the fuel treating pipe.
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公开(公告)号：US20240209798A1
公开(公告)日：2024-06-27
申请号：US18085680
申请日：2022-12-21
发明人： Milos Ilak , Edmund Emmett Rochford , Martin Amari , Abhijit Chakraborty , Jerry Ding , Daniel T. Pollock , Konda Reddy Chevva , Jeffrey Ernst , William S. Heglund
摘要： A system including a supervisory controller configured to receive one or more mission objectives for an aircraft mission, and condition data; a memory for storing program instructions; at least one local supervisory controller, operatively coupled to the memory, and in communication with the supervisory controller and operative to execute program instructions to: simulate execution of the aircraft mission to address at least one of the one or more mission objectives; receive data output from at least one subsystem, the data output including a measurement of an aircraft physical system; generate a mission plan executable to address at least one of the one or more mission objectives via manipulation of the at least one subsystem; receive the generated mission plan at a subsystem controller directly from the at least one local supervisory controller; and automatically execute the generated mission plan to operate an aircraft.
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公开(公告)号：US11970977B2
公开(公告)日：2024-04-30
申请号：US17896786
申请日：2022-08-26
摘要： A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal. The auxiliary fuel circuit joins with the secondary fuel circuit for delivery to a fuel nozzle.
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公开(公告)号：US11959423B2
公开(公告)日：2024-04-16
申请号：US17869428
申请日：2022-07-20
发明人： David Justin Brady
CPC分类号： F02C9/263 , F02C7/232 , F02C7/236 , F02C9/28 , F02C9/30 , F02C9/32 , F02C9/36 , F02C9/46 , F05D2270/09 , F05D2270/3015 , F05D2270/304
摘要： A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA) is disclosed. An example fuel supply system includes a fuel supply line to supply fuel to a combustion engine, a fuel metering valve coupled to the fuel supply line, the fuel metering valve to control a flow of fuel through the fuel supply line to the combustion engine, a throttle valve coupled to the fuel supply line downstream of the fuel metering valve, the throttle valve to bleed off fuel supplied to the combustion engine based on a pressure difference across the fuel metering valve, and a controllable servo coupled to the throttle valve, the controllable servo to control the throttle valve based on a sensor output indicative of the pressure difference.
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公开(公告)号：US11959420B2
公开(公告)日：2024-04-16
申请号：US16736970
申请日：2020-01-08
申请人： RTX Corporation
发明人： Timothy S. Snyder
CPC分类号： F02C7/228 , F02C7/232 , F02C9/263 , F05D2220/323 , F05D2270/303 , F23D2900/00015 , F23K2300/206 , F23N2235/24
摘要： A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.
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公开(公告)号：US11952940B2
公开(公告)日：2024-04-09
申请号：US17609101
申请日：2020-03-17
发明人： Tyler Berger , Jaskirat Singh
摘要： A water delivery system (18) for delivering water for injection into gas turbine engine combustor (4) includes a centrifugal pump (19) and a metering valve (23). The centrifugal pump (19) has an inlet (20) connected to a water source and a discharge (21) connected to a water supply line (22). The metering valve (23) is connected to the water supply line (22) downstream of the discharge (21) of the centrifugal pump (19). The water supply line (22) is connected to an injector nozzle (14) downstream of the metering valve (23). The metering valve (23) is operable to regulate a flow rate of water in the water supply line (22), to thereby meter an amount of water supplied to the injector nozzle (14).
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公开(公告)号：US11946549B2
公开(公告)日：2024-04-02
申请号：US18155334
申请日：2023-01-17
申请人： Woodward, Inc.
发明人： Jimroy A. McCormack
IPC分类号： F16K15/06 , B67D7/36 , F02C9/26 , F16K15/04 , F16K17/04 , F16K17/30 , F16K17/34 , F16K47/00 , F16K47/02 , F23R3/28
CPC分类号： F16K15/063 , B67D7/36 , F02C9/263 , F16K15/044 , F16K15/065 , F16K17/04 , F16K17/0433 , F16K17/30 , F16K17/34 , F16K47/011 , F16K47/0111 , F16K47/023 , F23R3/28 , F05D2220/32 , Y10T137/7727 , Y10T137/7931
摘要： A fuel nozzle metering valve that includes a spool having an inlet port and an outlet flow port, and a retainer assembled to one end of the spool. A valve liner houses a portion of the spool. The spool is configured to move back and forth within the valve liner. The metering valve is biased in a closed position in which the outlet flow port is disposed entirely within the valve liner. The valve is opened when the spool slides within the valve liner such that some portion of the outlet flow port extends beyond an end of the valve liner. The retainer has a stepped portion configured to abut an end of the retainer at a fuel flow pressure below the expected maximum fuel flow pressure to be used in the fuel nozzle metering valve.
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公开(公告)号：US20240068405A1
公开(公告)日：2024-02-29
申请号：US17896762
申请日：2022-08-26
发明人： Brandon P. Williams , Jason A. Ryon , Todd Haugsjaahabink , Murtuza Lokhandwalla , Charles E. Reuter
CPC分类号： F02C7/232 , F02C9/263 , F23R3/28 , F05D2220/323 , F05D2240/35
摘要： A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet in response to fuel pressure received at the fuel inlet. Primary and secondary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the primary circuit, adapted and configured to actively control fuel through the primary circuit in response to a control signal.
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公开(公告)号：US11898449B2
公开(公告)日：2024-02-13
申请号：US17092525
申请日：2020-11-09
申请人： ABB Schweiz AG
发明人： Camilo Lopez , Mark Foltz , Steve Miller
IPC分类号： F01C20/28 , G01P21/02 , G01R31/28 , F01D17/06 , F02C9/28 , F01D21/02 , H02J3/38 , H02J3/40 , F01K13/00 , F01K13/02 , F16K37/00 , F02C7/232 , F02C9/26 , F02C9/52 , F02C9/54 , F01D17/14 , F01D17/26
CPC分类号： F01C20/28 , F01D17/06 , F01D17/145 , F01D17/26 , F01D21/02 , F01K13/003 , F01K13/02 , F02C7/232 , F02C9/263 , F02C9/28 , F02C9/52 , F02C9/54 , F16K37/0041 , F16K37/0083 , G01P21/02 , G01R31/2829 , H02J3/381 , H02J3/40 , F05D2220/31 , F05D2260/80 , F05D2270/02 , F05D2270/021 , F05D2270/80
摘要： A turbine control system is provided for decreasing the response time between readings of the speed of the turbine and changing a valve position in response thereto. The speed control system includes a speed probe that detects the speed of the turbine and a turbine valve that controls the flow of fluid or gas from or to the turbine. A controller receives a speed signal from the speed probe and sends valve position commands to the turbine valve. The controller also sends support functions to the turbine valve. The controller sends the valve position commands at a faster rate than the support functions.
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