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公开(公告)号：US11774100B2
公开(公告)日：2023-10-03
申请号：US17725895
申请日：2022-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinod Patel , Michael A. Benjamin
CPC classification number: F23R3/34 , F23R3/06 , F23R3/14 , F23R3/36 , F02C7/22 , F23R3/28 , F23R3/346
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
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公开(公告)号：US20230304665A1
公开(公告)日：2023-09-28
申请号：US18302346
申请日：2023-04-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ajoy Patra , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , R Narasimha Chiranthan , Manampathy G. Giridharan , Michael A. Benjamin , Clayton S. Cooper
CPC classification number: F23R3/286 , F02C7/264 , F23D14/64 , F23R3/045 , F23R3/50 , F05D2240/35 , F05D2260/99 , F23D2207/00
Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.
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公开(公告)号：US20230296250A1
公开(公告)日：2023-09-21
申请号：US17740443
申请日：2022-05-10
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Michael T. Bucaro , Pradeep Naik , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/03044
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.
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公开(公告)号：US11754288B2
公开(公告)日：2023-09-12
申请号：US17115877
申请日：2020-12-09
Applicant: General Electric Company
Inventor： Hari Ravi Chandra , Arvind Kumar Rao , Shai Birmaher , Jayanth Sekar , Gurunath Gandikota , Michael A. Benjamin
CPC classification number: F23R3/343 , F02C7/222 , F23D14/64 , F23D14/70 , F23R3/286 , F05D2240/35 , F23D2206/10
Abstract: A mixing assembly for a combustor, including: a pilot mixer and a pilot fuel nozzle; a main mixer including: a main housing surrounding the pilot mixer; a fuel manifold positioned between the pilot housing and the main housing; a mixer foot extending outward from a forward end of the main housing; a main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and coupled to the mixer foot; and a main fuel ring in the mixing channel downstream of the mixer foot connected to the main housing by main fuel vanes, at least one of the main fuel ring and the main fuel vanes including fuel injection ports positioned to discharge fuel into a central portion of the mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring.
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公开(公告)号：US20230243311A1
公开(公告)日：2023-08-03
申请号：US17590472
申请日：2022-02-01
Applicant: GENERAL ELECTRIC COMPANY , GE Avio S.r.l.
Inventor： David Justin Brady , Mirko Gernone , Michael A. Benjamin , Steven C. Vise
CPC classification number: F02C9/40 , F02C7/22 , F23R3/36 , F23R3/30 , F05D2220/32 , F05D2240/36
Abstract: A fuel supply system for a combustion section of a turbine engine. The turbine engine including a heat source. The fuel supply system comprising a first fuel supply having a liquid fuel, a second fuel supply having a first gaseous fuel, and a heat exchanger fluidly coupled to the first fuel supply and the heat source. The heat exchanger producing a heat sufficient to change the liquid fuel to a second gaseous fuel that is the same type of fuel as the first gaseous fuel.
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Patent Agency Ranking
公开(公告)号：US20230228424A1
公开(公告)日：2023-07-20
申请号：US17725895
申请日：2022-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinod Patel , Michael A. Benjamin
CPC classification number: F02C7/22 , F02C3/04 , F23R3/14 , F23R3/28 , F23R3/36 , F05D2220/30 , F05D2240/35
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
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公开(公告)号：US20230194095A1
公开(公告)日：2023-06-22
申请号：US17700852
申请日：2022-03-22
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Michael T. Bucaro , Ajoy Patra , Manampathy G. Giridharan , Steven C. Vise , R Narasimha Chiranthan , Michael A. Benjamin , 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. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and 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：US20230175435A1
公开(公告)日：2023-06-08
申请号：US17457559
申请日：2021-12-03
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：US11668241B2
公开(公告)日：2023-06-06
申请号：US17350932
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F02C7/224 , F02C9/28 , F05D2220/32 , F05D2240/35 , F05D2260/20
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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公开(公告)号：US20220403784A1
公开(公告)日：2022-12-22
申请号：US17351023
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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