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公开(公告)号：US12129812B2
公开(公告)日：2024-10-29
申请号：US17603151
申请日：2020-05-20
发明人： Kevin Michael VandeVoorde , Joshua Tyler Mook , Aigbedion Akwara , Jason Joseph Bellardi , Mohammed El Hacin Sennoun , Mary Kathryn Thompson , Scott Douglas Waun , Michael Thomas Gansler , Michael Robert Notarnicola
IPC分类号： F02G1/044 , B33Y80/00 , F02G1/04 , F02G1/043 , F02G1/047 , F02G1/05 , F02G1/053 , F02G1/055 , F02G1/057 , F02G3/00 , F23R3/00 , F28D9/04 , F28D21/00 , F28F7/02 , F28F13/00 , F28F13/14
CPC分类号： F02G1/044 , B33Y80/00 , F02G1/04 , F02G1/043 , F02G1/047 , F02G1/05 , F02G1/053 , F02G1/055 , F02G1/057 , F02G3/00 , F23R3/005 , F28D9/04 , F28F7/02 , F28F13/003 , F28F13/14 , F02G1/0435 , F02G2243/00 , F02G2244/00 , F02G2244/08 , F02G2244/50 , F02G2244/52 , F02G2244/54 , F02G2250/00 , F02G2254/10 , F02G2254/18 , F02G2257/00 , F02G2258/10 , F02G2270/40 , F02G2270/45 , F02G2270/80 , F02G2280/10 , F28D2021/0026 , F28F2210/10 , F28F2250/04
摘要： A system for energy conversion, the system including a closed cycle engine containing a volume of working fluid, the engine comprising a first chamber defining an expansion chamber and a second chamber defining a compression chamber each separated by a piston attached to a connection member of a piston assembly, and wherein the engine comprises a heater body in thermal communication with the first chamber, and further wherein the engine comprises a cold side heat exchanger in thermal communication with the second chamber, and wherein a third chamber is defined within the piston, wherein the third chamber is in selective flow communication with the first chamber, the second chamber, or both.
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2.发明公开公开(公告)号：US20240353105A1
公开(公告)日：2024-10-24
申请号：US18639359
申请日：2024-04-18
申请人： RTX Corporation
CPC分类号： F23R3/60 , F23R3/002 , F23R3/50 , F23R2900/00017
摘要： A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.
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公开(公告)号：US12123362B2
公开(公告)日：2024-10-22
申请号：US18225427
申请日：2023-07-24
申请人： ROLLS-ROYCE plc
CPC分类号： F02C9/40 , F02C9/28 , F23R3/343 , F05D2220/323 , F05D2270/08 , F05D2270/306 , F05D2270/31 , F05D2270/71
摘要： An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.
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4.发明授权公开(公告)号：US12123361B2
公开(公告)日：2024-10-22
申请号：US17568313
申请日：2022-01-04
CPC分类号： F02C9/40 , F02C7/22 , F23R3/36 , F05D2220/32 , F05D2240/35
摘要： Systems and methods include a fuel cell stack extended around a combustion chamber that is configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution. The fuel cell stack is positioned at a downstream section of the combustion chamber along an axial direction.
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公开(公告)号：US20240344702A1
公开(公告)日：2024-10-17
申请号：US18135594
申请日：2023-04-17
发明人： Gregory Boardman
IPC分类号： F23R3/28
CPC分类号： F23R3/286
摘要： An assembly is provided for a turbine engine. This assembly includes a combustor, a fuel-air mixer and a mixer guide. The combustor includes a bulkhead. The fuel-air mixer includes an inner passage, a sidewall and a fuel circuit. The inner passage extends axially along an axis within the fuel-air mixer. The sidewall extends circumferentially around and axially along the inner passage. The fuel circuit includes a first fuel passage and a first fuel nozzle outlet fluidly coupled with the first fuel passage. The first fuel passage is embedded within the sidewall and extends along the inner passage. The fuel circuit is configured to direct fuel into the inner passage through the first fuel nozzle outlet. The mixer guide couples the fuel-air mixer to the bulkhead. The mixer guide is configured to slide axially along the fuel-air mixer.
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公开(公告)号：US20240328360A1
公开(公告)日：2024-10-03
申请号：US18742260
申请日：2024-06-13
发明人： Michael T. Bucaro , Manampathy G. Giridharan , Pradeep Naik , Sripathi Mohan , Michael A. Benjamin , Steven C. Vise , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
摘要： A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.
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公开(公告)号：US20240328349A1
公开(公告)日：2024-10-03
申请号：US18127155
申请日：2023-03-28
发明人： Dave MENHEERE
CPC分类号： F02C5/08 , F23R7/00 , F05D2240/35
摘要： A combustor assembly for a turbine engine includes a combustor assembly where a first combustion space is defined between a first closed end of a combustion chamber and a first piston, a second combustion space is defined between a second closed end of the combustion chamber and a second piston and a center combustion space is defined between the first piston and the second piston. An air inlet assembly provides for communication of inlet air to the first combustion space, the second combustion space and the center combustion space. First, second and center injectors are provided to inject fuel into a corresponding one of the first combustion space, the second combustion space, and the center combustion space. An exhaust outlet communicates an exhaust gas flow generated in each of the first combustion space, the second combustion space and the center combustion space to a turbine section.
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公开(公告)号：US12104795B2
公开(公告)日：2024-10-01
申请号：US17664975
申请日：2022-05-25
摘要： A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.
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公开(公告)号：US12104793B2
公开(公告)日：2024-10-01
申请号：US18555930
申请日：2022-04-15
摘要： A flame-holder device for a turbojet afterburner comprises an annular row of flame-holder arms, each having an inner branch having a free end and another end, and two outer branches which extend from the other end (52) and diverge from one another in a direction extending from the free end to the other end, such that the inner branch transitions radially outward into the two outer branches which diverge radially outward from one another in two opposing circumferential directions, thereby forming mutually approaching areas between consecutive flame-holder arms for enabling the flame to spread from arm to arm.
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公开(公告)号：US20240318822A1
公开(公告)日：2024-09-26
申请号：US18663324
申请日：2024-05-14
发明人： Perumallu Vukanti , Sibtosh Pal , Pradeep Naik , R Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Aritra Chakraborty , Arijit Sinha Roy , Pabitra Badhuk , Bhavya Naidu Panduri
IPC分类号： F23R3/06
CPC分类号： F23R3/06
摘要： A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.
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