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公开(公告)号：US20250035311A1
公开(公告)日：2025-01-30
申请号：US18804465
申请日：2024-08-14
Applicant: General Electric Company
Inventor： Pradeep Naik , Ajoy Patra , Michael T. Bucaro , Perumallu Vukanti , Steven C. Vise , Michael A. Benjamin , Manampathy G. Giridharan , Sakat Singh , Clayton S. Cooper
Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.
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公开(公告)号：US20240392968A1
公开(公告)日：2024-11-28
申请号：US18652193
申请日：2024-05-01
Applicant: ROLLS-ROYCE PLC
Inventor： Stephen C. HARDING
Abstract: An integral guide vane combustor assembly for a gas turbine engine comprises an annular array of radially extending guide vane combustors. The gas turbine engine comprises, in axial flow sequence, a compressor assembly, the integral guide vane combustor assembly, a turbine assembly, and an exhaust assembly. Each of the guide vane combustors comprises, in axial flow sequence, a guide vane portion, and a combustor body portion. The guide vane portion is formed integrally with the combustor body portion, and the guide vane portion is configured to direct a gas flow exiting the compressor assembly into the combustor body portion.
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公开(公告)号：US20240392967A1
公开(公告)日：2024-11-28
申请号：US18652159
申请日：2024-05-01
Applicant: ROLLS-ROYCE plc
Inventor： Karpaga Vipran KANNAN , Joseph R. HARDY , Ryan L. ROGERS , Andrés E. LEIVA GONZALEZ , Shahrokh SHAHPAR
Abstract: A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. An inlet to the fuel stem portion is fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion is fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion has a cross-sectional profile that is generally dolioform shaped along an axis parallel to the engine's longitudinal axis, and has a first end and a second end. The first end of the fuel/air swirler portion has an air inlet face, and the second end of the fuel/air swirler portion has a fuel/air mixture outlet face. The first end comprises a rim portion enclosing the air inlet face in which the rim portion has a rim portion radius (rrim) normal to an outer circumference of the inlet face.
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公开(公告)号：US20240369225A1
公开(公告)日：2024-11-07
申请号：US18776600
申请日：2024-07-18
Applicant: IHI Corporation
Inventor： Shintaro ITO , Masahiro UCHIDA
Abstract: An injection nozzle includes: an inner wall having a cylindrical shape; a first outer wall having a cylindrical shape and being formed integrally with the inner wall through intermediation of a connection portion; a fuel passage having an annular shape and being formed between the inner wall and the first outer wall; and an inner air passage formed on an inner side of the inner wall.
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公开(公告)号：US12123596B2
公开(公告)日：2024-10-22
申请号：US17389022
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Mishra
IPC: F23R3/14
CPC classification number: F23R3/14 , F05D2240/127 , F05D2240/35 , F05D2250/183
Abstract: A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.
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公开(公告)号：US20240344482A1
公开(公告)日：2024-10-17
申请号：US18755155
申请日：2024-06-26
Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA
Inventor： Hiromitsu ARAI , Ryozo TANk , Tomoki TANIGUCHI , Yoshihiko MUTOU
CPC classification number: F02C7/18 , F23R3/14 , F05D2260/232
Abstract: A gas turbine engine includes a cooling air supply passage that feeds air from a compressor, as a cooling medium, to a turbine by swirling the air in a circumferential direction. The cooling air supply passage includes an entry zone to which the air enters, and a swirl zone in which the air flowing past the entry zone is circumferentially redirected. The gas turbine engine also includes a chamber branching from the swirl zone to capture foreign particles in the air. The chamber is formed to meet the relation: α≥β where, when viewed in a radial direction, α is an angle defined by the swirl zone relative to a horizontal direction and β is an angle defined between the chamber and the swirl zone.
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7.发明公开
公开(公告)号：US20240328626A1
公开(公告)日：2024-10-03
申请号：US18541041
申请日：2023-12-15
Applicant: AERO ENGINE ACADEMY OF CHINA
Inventor： Shiqi WANG , Quan WEN , Xiao HAN , Qian YANG
Abstract: The present disclosure provides a central staged combustion chamber with self-excited sweeping oscillating fuel injection nozzles, including an outer housing with a cavity inside, a main stage coaxially disposed with the outer housing, and a pilot stage coaxially disposed with the outer housing. An annular fuel passage is used for connecting a plurality of self-excited sweeping oscillating fuel injection nozzles, and the self-excited sweeping oscillating fuel injection nozzles are suitable for injecting oscillating liquid fuel into a primary swirling passage. The fuel is output in a fan shape through each of the self-excited sweeping oscillating fuel injection nozzles and is dispersed by an incoming flow through the swirling passage, so that the atomization performance and spatial distribution uniformity of the fuel can be greatly improved.
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公开(公告)号：US20240328624A1
公开(公告)日：2024-10-03
申请号：US18738916
申请日：2024-06-10
Applicant: RTX Corporation
Inventor： Baris A. Sen , Zhongtao Dai , Wookyung Kim , Stephen K. Kramer
IPC: F23R3/14
CPC classification number: F23R3/14
Abstract: A fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.
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公开(公告)号：US12092329B2
公开(公告)日：2024-09-17
申请号：US17680751
申请日：2022-02-25
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver , Daniel Patrick Kerns
Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
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公开(公告)号：US20240302044A1
公开(公告)日：2024-09-12
申请号：US18117920
申请日：2023-03-06
Applicant: Raytheon Technologies Corporation
Inventor： Ian Walters , Stephen K. Kramer , Gary J. Dillard
Abstract: An assembly is provided for a gas turbine engine. This turbine engine assembly includes a combustor and a fuel injector assembly. The combustor includes a combustion chamber that extends axially along and circumferentially about an axial centerline. The fuel injector assembly is configured to direct fuel and air into the combustion chamber. The fuel injector assembly includes a fuel injector nozzle and an air swirler structure. The fuel injector nozzle projects into and is coupled with the air swirler structure. The centerline axis of at least one of the fuel injector nozzle or the air swirler structure is angularly offset from the axial centerline by an offset angle in a circumferential direction about the axial centerline.
