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1.发明公开公开(公告)号：US20230193829A1
公开(公告)日：2023-06-22
申请号：US17589145
申请日：2022-01-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael A. Benjamin , Michael T. Bucaro
Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.
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公开(公告)号：US11795879B2
公开(公告)日：2023-10-24
申请号：US17589145
申请日：2022-01-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael A. Benjamin , Michael T. Bucaro
CPC classification number: F02C7/266 , F23R3/286 , F02C7/232 , F23R3/28 , F23R2900/00006 , F23R2900/00009
Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.
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公开(公告)号：US20230323809A1
公开(公告)日：2023-10-12
申请号：US17658903
申请日：2022-04-12
Applicant: General Electric Company
Inventor： Arin Elspeth Lastufka Cross , Krishnakumar Venkatesan
CPC classification number: F02C6/00 , B64D27/10 , B64D33/02 , B64D33/04 , F02C7/057 , B64D2033/026 , F05D2220/323 , F05D2240/35
Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.
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公开(公告)号：US20230194094A1
公开(公告)日：2023-06-22
申请号：US17677165
申请日：2022-02-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Fei Han , Ramal Janith Samarasinghe , Pradeep Naik , Krishnakumar Venkatesan , Michael T. Bucaro , Ajoy Patra , Manampathy G. Giridharan
Abstract: A turbine engine having a compressor section, a combustion section and a turbine section in serial flow arrangement. The turbine engine further having a combustor, provided within the combustion section, defining a combustion chamber and having at least one fuel injector. The fuel injector having a fuel channel, a first set of fuel orifices, and a flow restrictor located within the fuel channel and having a second set of fuel orifices.
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公开(公告)号：US12253050B2
公开(公告)日：2025-03-18
申请号：US17658903
申请日：2022-04-12
Applicant: General Electric Company
Inventor： Arin Elspeth Lastufka Cross , Krishnakumar Venkatesan
IPC: F02K7/16 , F02C6/00 , F02C6/08 , F02C7/042 , F02C7/057 , F02C7/18 , F02K1/06 , F02K7/14 , F02K7/20 , F23R7/00
Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.
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Patent Agency Ranking
公开(公告)号：US12228282B2
公开(公告)日：2025-02-18
申请号：US18409690
申请日：2024-01-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan , Clayton Stuart Cooper , Michael A. Benjamin , Steven C. Vise , Manampathy G. Giridharan , Krishnakumar Venkatesan
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 can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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7.发明公开公开(公告)号：US20230194093A1
公开(公告)日：2023-06-22
申请号：US17717739
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Manampathy G. Giridharan , Krishnakumar Venkatesan
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 can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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公开(公告)号：US10352570B2
公开(公告)日：2019-07-16
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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公开(公告)号：US20170284678A1
公开(公告)日：2017-10-05
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
CPC classification number: F23R3/38 , F02C7/22 , F23D2900/11101 , F23R3/14 , F23R3/28
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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10.发明授权公开(公告)号：US11906165B2
公开(公告)日：2024-02-20
申请号：US17717739
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Manampathy G. Giridharan , Krishnakumar Venkatesan
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 can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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