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公开(公告)号：US20230366550A1
公开(公告)日：2023-11-16
申请号：US18355449
申请日：2023-07-20
发明人： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
CPC分类号： F23R3/06 , F23R3/16 , F23R3/28 , F23R2900/03044
摘要： A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
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公开(公告)号：US20230220998A1
公开(公告)日：2023-07-13
申请号：US17694978
申请日：2022-03-15
CPC分类号： F23D14/70 , F23R3/06 , F23R3/50 , F23R3/286 , F23D2210/00
摘要： A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.
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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
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：US20230213191A1
公开(公告)日：2023-07-06
申请号：US17587169
申请日：2022-01-28
发明人： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
CPC分类号： F23R3/06 , F23R3/28 , F23R3/16 , F23R2900/03044
摘要： A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
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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
发明人： 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
摘要： 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：US20220373181A1
公开(公告)日：2022-11-24
申请号：US17325938
申请日：2021-05-20
摘要： A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.
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公开(公告)号：US12092332B2
公开(公告)日：2024-09-17
申请号：US17675270
申请日：2022-02-18
发明人： Pradeep Naik , Ajoy Patra , Michael T. Bucaro , Perumallu Vukanti , Steven C. Vise , Michael A. Benjamin , Manampathy G. Giridharan , Saket Singh , Clayton S. Cooper
摘要： 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：US20240280264A1
公开(公告)日：2024-08-22
申请号：US18296220
申请日：2023-04-05
发明人： Bhavya Naidu Panduri , Perumallu Vukanti , Pradeep Naik , Michael T. Bucaro , Sibtosh Pal , Aritra Chakraborty , Pabitra Badhuk , Arijit Sinha Roy , Ajoy Patra , R Narasimha Chiranthan
IPC分类号： F23R3/00
摘要： A combustor for a gas turbine engine. The combustor having a dome wall, a set of fuel cups, an inner liner, an outer liner, and a set of dilution passages. The dome wall, the inner liner, and the outer liner, together, at least partially defining a combustion chamber. The set of dilution passages terminating in a plurality of dilution holes arranged in a dilution hole arrangement provided in at least one of the inner liner or the outer liner. The dilution hole arrangement having at least a first subset of dilution holes arranged along a first leg and a second subset of dilution holes arranged along a second leg.
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公开(公告)号：US12060995B1
公开(公告)日：2024-08-13
申请号：US18187773
申请日：2023-03-22
发明人： Aritra Chakraborty , Perumallu Vukanti , Pradeep Naik , Arijit Sinha Roy , Bhavya Naidu Panduri , R Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Sibtosh Pal , Pabitra Badhuk
IPC分类号： F23R3/06
CPC分类号： F23R3/06
摘要： A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.
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公开(公告)号：US20240151396A1
公开(公告)日：2024-05-09
申请号：US18482949
申请日：2023-10-09
发明人： Manampathy G. Giridharan , Ajoy Patra , Pradeep Naik , R Narasimha Chiranthan , Perumallu Vukanti , Michael T. Bucaro
IPC分类号： F23R3/28
CPC分类号： F23R3/286
摘要： 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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