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公开(公告)号：US20240003298A1
公开(公告)日：2024-01-04
申请号：US17810624
申请日：2022-07-04
CPC分类号： B64D37/06 , F02C7/232 , F02C7/222 , F05D2260/60 , F05D2220/323
摘要： A fuel system of an aircraft engine, has: a fuel manifold having a first manifold inlet and a second manifold inlet; a transfer tube assembly having a first tube slidably engaged to the fuel manifold and fluidly connected to the first manifold inlet, and a second tube slidably engaged to the fuel manifold and fluidly connected to the second manifold inlet; and an adaptor having: a body slidably engaged by the first tube and by the second tube, a first member defining a first fuel conduit fluidly connected to the first manifold inlet via the first tube, and a second member defining a second fuel conduit fluidly connected to the second manifold inlet via the second tube.
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公开(公告)号：US11859553B2
公开(公告)日：2024-01-02
申请号：US17486237
申请日：2021-09-27
发明人： Ryan Susca , Steve Doerner , Charles E. Reuter
CPC分类号： F02C7/232 , F02C7/222 , F02C7/228 , F23K5/06 , F23K5/147 , F23K5/18 , F02C9/30 , F05D2260/602 , F05D2260/607 , F05D2260/608 , F23K2300/206
摘要： A fluid injection system can include a main flow line, a primary flow line connected to the main flow line, and a primary flow valve disposed between the primary flow line and the main flow line and configured to allow injectant flow to the primary flow line from the main flow line in an open primary flow valve state, and to prevent injectant flow to the primary flow line from the main flow line in a closed primary flow valve state. The system can include a secondary flow line connected to the main flow line and a secondary flow valve disposed between the secondary flow line and the main flow line and configured to selectively allow injectant flow to the secondary flow line from the main flow line in an open secondary flow valve state, and to prevent injectant flow to the secondary flow line from the main flow line in a closed secondary flow valve state. The system can include a primary purge branch configured and a secondary purge branch configured to be in fluid communication with a purge gas line to receive a purge gas flow from the purge gas line.
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公开(公告)号：US11851204B2
公开(公告)日：2023-12-26
申请号：US16178970
申请日：2018-11-02
发明人： Ethan Patrick O'Connor , Daniel Alan Niergarth , Brandon Wayne Miller , Richard Alan Wesling , David Justin Brady
CPC分类号： B64D37/34 , F02C7/222 , F02C7/232 , F02C7/236 , F02M37/22 , B01D19/0063 , B01D2257/104 , F02C7/224 , F05D2210/13 , F05D2260/213
摘要： A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.
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公开(公告)号：US20230392551A1
公开(公告)日：2023-12-07
申请号：US17830105
申请日：2022-06-01
发明人： Constantinos Minas
CPC分类号： F02C7/224 , F02C7/232 , F02C3/22 , F02C9/40 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/301 , F05D2300/121 , F05D2260/231 , F05D2300/603 , F05D2260/60
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：US11821368B2
公开(公告)日：2023-11-21
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：US20230313742A1
公开(公告)日：2023-10-05
申请号：US17657182
申请日：2022-03-30
IPC分类号： F02C7/232
CPC分类号： F02C7/232
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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公开(公告)号：US20230296053A1
公开(公告)日：2023-09-21
申请号：US18184485
申请日：2023-03-15
发明人： Bouzid SEBA , Michaael-Alexandre BAERT , Alix NOCA
CPC分类号： F02C7/222 , F02C7/232 , F23R3/34 , F05D2220/32 , F05D2240/35
摘要： The invention relates to an engine having at least two combustion chambers, a shared high-pressure fuel storage tank for holding fuel gas available as pressurized gas, and means for direct injection of the fuel gas from the high-pressure fuel storage tank into the combustion chambers, wherein it is possible to provide the fuel gas in the high-pressure fuel storage tank from a primary tank, wherein it is possible to withdraw the fuel gas from the primary tank and/or to generate it from a fuel withdrawn from the primary tank along a conversion path, and a gas buffer storage tank connected to the high-pressure fuel storage tank discharges fuel gas from the high-pressure fuel storage tank into the gas buffer storage tank, and the gas buffer storage tank is further connected via a separate fuel gas path to the air intake section of the gas combustion engine.
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公开(公告)号：US11760501B2
公开(公告)日：2023-09-19
申请号：US17345868
申请日：2021-06-11
发明人： Scott Smith
CPC分类号： B64D37/32 , B64D37/34 , F01D21/003 , F02C7/224 , F02C7/232 , F02C7/25 , F02C7/32 , F05D2220/323 , F05D2240/14 , F05D2260/213 , F05D2260/605 , F05D2260/80
摘要： In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.
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公开(公告)号：US11753996B1
公开(公告)日：2023-09-12
申请号：US17895969
申请日：2022-08-25
CPC分类号： F02C7/232 , F02C7/222 , F23R3/34 , F05D2220/32 , F05D2230/31 , F05D2240/36
摘要： A fuel injector assembly can include a manifold defining a manifold channel and a nozzle extending from the manifold. The nozzle can be configured to direct flow from the manifold channel into a combustor. The nozzle can define a fuel inlet open to the manifold channel, a fuel outlet configured to be open to a combustor, and a throat fluidly connecting the fuel inlet to the fuel outlet. The assembly can include a trim device inserted into the manifold. The trim device can be configured to adjust flow between the manifold channel and the fuel inlet to adjust flow through the throat and out of the fuel outlet.
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公开(公告)号：US20230265798A1
公开(公告)日：2023-08-24
申请号：US18170404
申请日：2023-02-16
申请人： Woodward, Inc.
发明人： Bidhan Dam , Michael Hackenberg
CPC分类号： F02C7/264 , F02C7/232 , F23R3/28 , F05D2220/32 , F05D2240/36 , F05D2260/99
摘要： The subject matter of this specification can be embodied in, among other things, an assembly that includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet, and an igniter carried by the primary combustion chamber an includes an igniter stage having an auxiliary combustion chamber housing comprising a mixing chamber and a tubular throat converging downstream of the mixing chamber, an auxiliary air conduit having an auxiliary air outlet in fluidic communication with the auxiliary combustion chamber, an auxiliary fuel conduit having an auxiliary fuel outlet fluidic communication with the auxiliary combustion chamber, and an ignition source proximal the auxiliary fuel outlet.
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