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公开(公告)号：US12129800B2
公开(公告)日：2024-10-29
申请号：US17657182
申请日：2022-03-30
CPC分类号： F02C7/232 , F16K1/46 , F16K15/14 , F23K5/147 , F23N2235/24
摘要： A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.
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2.发明公开公开(公告)号：US20240318601A1
公开(公告)日：2024-09-26
申请号：US18261185
申请日：2022-01-07
摘要： A system for supplying the combustion chamber in an aircraft turboshaft engine with fuel, comprising injectors comprising a first pilot stage, a second pilot stage, and a main stage. The pilot stages being configured to deliver a permanent flow rate of fuel and the main stage being configured to deliver an intermittent flow rate of fuel. A device for distributing (2) fuel into the injectors comprising a primary circuit, a secondary circuit, and a valve configured to distribute the fuel between the primary circuit and the secondary circuit. The primary circuit being connected to the first pilot stage and the main stage, the secondary circuit being connected to the second pilot stage, and a member for controlling the valve.
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公开(公告)号：US12098678B2
公开(公告)日：2024-09-24
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：US20240310049A1
公开(公告)日：2024-09-19
申请号：US18583305
申请日：2024-02-21
摘要： A leakage gas emission system includes an enclosure surrounding at least part of a fuel supply system of a combustion device. The enclosure is provided with an outside emission unit for emitting internal gas to the outside. Fuel gas leaking from a leakage spot of the fuel supply system surrounded by the enclosure is taken in from an inlet port at one end of a first pipe and emitted from an emission port at another end toward the outside emission unit.
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公开(公告)号：US12092041B2
公开(公告)日：2024-09-17
申请号：US17423349
申请日：2020-03-19
CPC分类号： F02C9/263 , F02C7/232 , F05D2260/80
摘要： A method for monitoring the operating state of a turbomachine hydro-mechanical unit of an aircraft comprising:
a metering valve, comprising a movable metering part,
a control valve, configured to control the flow rate (Q) through the metering valve,
a flow rate meter able to measure the mass flow rate (Q) of passing fuel, characterized in that a monitoring module is configured for implementing the following steps:
determining a reconstructed flow rate based on the position of the movable part and on a measurement of the density of the fuel,
calculating a residue, and comparing said residue to a determined threshold value,
determining an abnormal operating state of the hydro-mechanical unit depending on the result of the comparison.-
公开(公告)号：US12078108B2
公开(公告)日：2024-09-03
申请号：US17830105
申请日：2022-06-01
发明人： Constantinos Minas
CPC分类号： F02C7/224 , B64D37/02 , B64D37/30 , F02C3/22 , F02C7/232 , F02C9/28 , F02C9/40 , F05D2220/323 , F05D2260/213 , F05D2260/231 , F05D2260/60 , F05D2270/301 , F05D2300/121 , F05D2300/603 , F17C2221/033 , F17C2223/0161 , F17C2270/0189
摘要： Methods and apparatus are disclosed for a hydrogen aircraft with cryo-compressed storage. An example fuel distribution system includes a vacuum vessel, a cryogenic vessel positioned within the vacuum vessel, the cryogenic vessel part of a cryo-compressed hydrogen delivery assembly, and at least one of a heater or a thermosiphoning loop to maintain a pressure of the cryogenic vessel.
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公开(公告)号：US12071898B2
公开(公告)日：2024-08-27
申请号：US17390638
申请日：2021-07-30
发明人： Adrian L. Stoicescu
IPC分类号： F02C7/236 , F02C7/232 , F02C9/30 , F04D1/06 , F04D1/10 , F04D9/04 , F04D13/12 , F04D15/00 , F04D15/02
CPC分类号： F02C7/236 , F02C7/232 , F02C9/30 , F04D1/06 , F04D1/10 , F04D13/12 , F04D15/0072 , F04D9/04 , F04D15/0218
摘要： A multi-stage fluid pump system can include a first stage configured to provide a first pressure and a second stage configured to provide a second pressure. The pump system can be configured to prevent output of the second stage in a first stage mode such that only the first pressure is output from the first stage and second stage and to allow output of the second stage in a multi-stage mode such that there is a combined pressure output from the first stage and the second stage.
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公开(公告)号：US12044176B2
公开(公告)日：2024-07-23
申请号：US17860756
申请日：2022-07-08
申请人： RTX Corporation
摘要： Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
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公开(公告)号：US20240209788A1
公开(公告)日：2024-06-27
申请号：US18337699
申请日：2023-06-20
申请人： ROLLS-ROYCE PLC
发明人： Christopher P. MADDEN , Craig W. BEMMENT , Paul W. FERRA , Benjamin J. KEELER , Andrea MINELLI , Peter SWANN , Martin K. YATES
CPC分类号： F02C7/224 , F02C7/222 , F02C7/232 , F05D2270/07
摘要： A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine for an aircraft.
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公开(公告)号：US12018614B2
公开(公告)日：2024-06-25
申请号：US18356662
申请日：2023-07-21
摘要： A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.
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