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公开(公告)号：US12071899B2
公开(公告)日：2024-08-27
申请号：US18197499
申请日：2023-05-15
发明人： Todd Haugsjaahabink , Ryan Shook
CPC分类号： F02C7/236 , F02C7/232 , F02C9/28 , F05D2270/301
摘要： A pump system for a gas turbine engine including a first pump connected to a fluid flow demand line for delivering fluid to a fluid flow demand and a second pump connected, in parallel to the first pump, to the fluid flow demand line and supplementing fluid to the actuation or burner system based on the fluid flow demand. A pressure regulating valve (PRV) is fluidly connected to the flow demand line for bypassing flow to a pump inlet pressure of the first pump and second pump, and controlling a modulated pressure flow signal to a bypass valve, wherein the bypass valve is in fluid communication with the second pump and the PRV for receiving modulated pressure from the PRV and regulating delivery of fluid from the second pump to a bypass flow line.
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公开(公告)号：US12031492B2
公开(公告)日：2024-07-09
申请号：US17498855
申请日：2021-10-12
发明人： James Harder , Andrew W. Solomon
CPC分类号： F02C9/30 , F02C7/236 , F02C9/28 , F04D13/06 , F05D2220/323 , F05D2270/301 , F05D2270/303
摘要： A fuel control system for an aircraft includes first and second electric motor controlled fuel pumps connect in parallel with one another to a fuel line. A plurality of fuel nozzles are connected to the fuel line to issue pressurized fuel from the fuel line with the ability to throttle flow based on system needs along with the electric pumping. At least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system. A fuel controller is operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle.
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公开(公告)号：US12031487B1
公开(公告)日：2024-07-09
申请号：US18214250
申请日：2023-06-26
发明人： Ryan Prescott Susca , Ryan Shook
CPC分类号： F02C7/232 , F02C7/236 , F02C9/30 , F05D2260/84
摘要： A fuel system can include a main fuel pump (MFP) configured to output main flow to a main line, an augmentor fuel pump (AFP) configured to output an augmenter flow to an augmenter line, and a variable displacement pump assembly (VDPP) in fluid communication with the AFP via the augmentor line to receive the augmentor flow. The VDPP can include a variable displacement pump (VDP) configured to output a VDP flow to a VDP output line. The system can include a main fuel throttle valve assembly (MFTV) in fluid communication with the main fuel pump via the main line to receive the main flow and in fluid communication with the VDPP via a backup line. The MFTV can be in fluid communication with an engine line, an actuation assembly in fluid communication with the VDPP via an actuation line to receive an actuation flow.
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公开(公告)号：US12006873B2
公开(公告)日：2024-06-11
申请号：US17759208
申请日：2021-01-15
CPC分类号： F02C7/236 , F02C7/26 , F02C9/30 , F05D2220/76
摘要： A fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.
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公开(公告)号：US11988158B2
公开(公告)日：2024-05-21
申请号：US17379532
申请日：2021-07-19
发明人： Ezzat Meshkin Fam , Xuening Lu
摘要： A method is provided for operating an aircraft system. During this method, an engine is operated using first fuel provided by a first fuel source. A fuel supply for the engine is switched between the first fuel source and a second fuel source, where the switching of the fuel supply includes shutting down the engine during aircraft flight. The engine is operated using second fuel provided by the second fuel source.
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公开(公告)号：US11982235B2
公开(公告)日：2024-05-14
申请号：US18181626
申请日：2023-03-10
申请人： ROLLS-ROYCE plc
发明人： Jonathan E. Holt
CPC分类号： F02C7/236 , F02C7/224 , F02C3/22 , F05D2220/62 , F05D2260/213
摘要： Disclosed is a fuel system for a gas turbine engine having a core exhaust and a combustion section. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and an air feed to drive the driving turbine, the air feed being fluidly connectable to the core exhaust of the gas turbine engine. Also disclosed is a fuel system comprising: a fuel pump for fluid communication with a fuel reservoir; a fuel line from the fuel pump for fluid communication with the combustion section of the gas turbine engine; and an air feed to a heat exchanger, the air feed being fluidly connectable to the core exhaust of the gas turbine engine, wherein the fuel line is in thermal communication with the air feed within a heat exchanger.
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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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8.发明公开公开(公告)号：US20240077032A1
公开(公告)日：2024-03-07
申请号：US18504453
申请日：2023-11-08
发明人： Cédric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , David WADDLETON , Marc-André TREMBLAY , Ignazio BROCCOLINI , Stephen TARLING
CPC分类号： F02C7/30 , F02C6/00 , F02C6/16 , F02C7/222 , F02C7/232 , F02C7/236 , F02C9/42 , F23D2209/30 , F23K2300/203
摘要： Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.
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公开(公告)号：US20230417190A1
公开(公告)日：2023-12-28
申请号：US17846583
申请日：2022-06-22
CPC分类号： F02C7/236 , F02C7/222 , F05D2220/323 , F02C9/44 , F02C7/232
摘要： According to an aspect, a dual fuel pump system includes a primary run-dry fuel pump having multiple stages, each of the stages configured to produce fuel pressure between a pump stage inlet and a pump stage outlet, and at least one of the stages operable in a run-dry mode. A secondary run-dry fuel pump is operable in run-dry mode, where the secondary run-dry fuel pump is mechanically driven by an accessory gearbox of an engine of the aircraft. An electric motor is operably coupled to the primary run-dry fuel pump and configured to drive rotation of the stages of the primary run-dry fuel pump. A controller is configured to pressurize fuel using a single stage of the primary run-dry fuel pump, pressurize fuel using at least two stages of the primary run-dry fuel pump, and pressurize fuel using the secondary run-dry fuel pump under various operating conditions.
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10.发明授权公开(公告)号：US11846236B2
公开(公告)日：2023-12-19
申请号：US17836510
申请日：2022-06-09
发明人： Cédric Saintignan , Joseph Daniel Maxim Cirtwill , Kian McCaldon , David Waddleton , Marc-André Tremblay , Ignazio Broccolini , Stephen Tarling
CPC分类号： F02C7/30 , F02C6/00 , F02C6/16 , F02C7/222 , F02C7/232 , F02C7/236 , F02C9/42 , F23D2209/30 , F23K2300/203
摘要： Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.
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