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公开(公告)号：US12297774B2
公开(公告)日：2025-05-13
申请号：US17244729
申请日：2021-04-29
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Pradeep Naik , Narendra D. Joshi , Harris D. Abramson
Abstract: A fuel mixer configured to provide a fuel-air mixture to a combustor of an engine. The fuel mixer may include a mixer body having a mixer outer wall, a center body, an annular passageway defined between the mixer outer wall and the center body, and a fuel tube assembly placed circumferentially about the mixer body. The fuel tube assembly may include at least one fuel channel for injecting a fuel flow into the annular passageway. The fuel tube assembly may be configured to cool a boundary layer flow present in the annular passageway. The fuel tube assembly may be configured to cool the mixer outer wall, the center body, or both the mixer outer wall and the center body. Heat from the mixer outer wall, the center body, or both the mixer outer wall and the center body, may pass to the fuel flow in the fuel tube assembly.
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2.发明授权公开(公告)号：US12215866B2
公开(公告)日：2025-02-04
申请号：US17734469
申请日：2022-05-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Manampathy G. Giridharan , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in axial flow arrangement. The combustion section can include a combustor having a fuel-air mixer. The fuel-air mixer can include a body with at least an air passage, as well as a set of mixing passages.
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公开(公告)号：US20240401809A1
公开(公告)日：2024-12-05
申请号：US18805691
申请日：2024-08-15
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Clayton S. Cooper , Michael A. Benjamin , Michael T. Bucaro , Manampathy G. Giridharan , Steven C. Vise , Ajoy Patra , Saket Singh , R Narasimha Chiranthan
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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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公开(公告)号：US12146662B2
公开(公告)日：2024-11-19
申请号：US18482949
申请日：2023-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Manampathy G. Giridharan , Ajoy Patra , Pradeep Naik , R Narasimha Chiranthan , Perumallu Vukanti , Michael T. Bucaro
IPC: F23R3/28
Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.
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公开(公告)号：US20240318597A1
公开(公告)日：2024-09-26
申请号：US18736667
申请日：2024-06-07
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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Patent Agency Ranking
公开(公告)号：US20240310048A1
公开(公告)日：2024-09-19
申请号：US18673532
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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公开(公告)号：US20240309804A1
公开(公告)日：2024-09-19
申请号：US18673559
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
CPC classification number: F02C3/22 , F02C7/22 , F23R3/28 , F05D2220/323 , F05D2240/35
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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公开(公告)号：US11846426B2
公开(公告)日：2023-12-19
申请号：US17397396
申请日：2021-08-09
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Pradeep Naik
CPC classification number: F23R3/346 , F02C3/20 , F02C3/30 , F23R3/36 , F23R3/002 , F23R3/286 , F23R3/34
Abstract: A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
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公开(公告)号：US20230220802A1
公开(公告)日：2023-07-13
申请号：US17717636
申请日：2022-04-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Michael T. Bucaro , Manampathy G. Giridharan , Pradeep Naik , Sripathi Mohan , Michael A. Benjamin , Steven C. Vise , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
Abstract: 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：US20230194091A1
公开(公告)日：2023-06-22
申请号：US17682373
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Clayton S. Cooper , Michael A. Benjamin , Michael T. Bucaro , Manampathy G. Giridharan , Steven C. Vise , Ajoy Patra , Saket Singh , R Narasimha Chiranthan
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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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