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公开(公告)号：US12018839B2
公开(公告)日：2024-06-25
申请号：US17969913
申请日：2022-10-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Sibtosh Pal , Michael A. Benjamin , Bhavya Naidu Panduri , Aritra Chakraborty , Pabitra Badhuk
CPC classification number: F23R3/28 , F02C7/22 , F23R3/002 , F05D2220/32 , F05D2240/35
Abstract: A combustor including an annular liner, a dome wall, a combustion chamber, at least one fuel cup and at least one dilution passage. The fuel cup being provided on the dome wall and being fluidly coupled to the combustion chamber. The fuel cup defining a fuel cup centerline. The at least on dilution passage terminating in at least on slot opening onto the dome wall, with the at least one slot having a longitudinal body axis.
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公开(公告)号：US20240200778A1
公开(公告)日：2024-06-20
申请号：US18104408
申请日：2023-02-01
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , R Narasimha Chiranthan , Ajoy Patra , Arijit Sinha Roy , Pabitra Badhuk , Aritra Chakraborty , Bhavya Naidu Panduri , Michael T. Bucaro , Sibtosh Pal
Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.
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公开(公告)号：US20240200777A1
公开(公告)日：2024-06-20
申请号：US18104433
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pabitra Badhuk , Michael T. Bucaro , Pradeep Naik , Perumallu Vukanti , Arijit Sinha Roy , Sibtosh Pal , Bhavya Naidu Panduri , Aritra Chakraborty , Ajoy Patra , R Narasimha Chiranthan , Michael A. Benjamin
Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.
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公开(公告)号：US12007114B1
公开(公告)日：2024-06-11
申请号：US18187359
申请日：2023-03-21
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Sibtosh Pal , Pradeep Naik , R Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Aritra Chakraborty , Arijit Sinha Roy , Pabitra Badhuk , Bhavya Naidu Panduri
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A first fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.
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公开(公告)号：US20230366551A1
公开(公告)日：2023-11-16
申请号：US18350205
申请日：2023-07-11
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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Patent Agency Ranking
56.发明授权公开(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：US20230235884A1
公开(公告)日：2023-07-27
申请号：US17685883
申请日：2022-03-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Manampathy G. Giridharan , Michael T. Bucaro , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan , Gregory A. Boardman
CPC classification number: F23R3/002 , F02C3/04 , F05D2240/35
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.
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公开(公告)号：US20230212984A1
公开(公告)日：2023-07-06
申请号：US17692411
申请日：2022-03-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Steven C. Vise , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Ajoy Patra , R Narasimha Chiranthan , Michael A. Benjamin , Manampathy G. Giridharan , Hiranya Kumar Nath
CPC classification number: F02C7/232 , F23R3/28 , F05D2220/32 , F05D2240/35
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. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.
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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：US20230194088A1
公开(公告)日：2023-06-22
申请号：US17686800
申请日：2022-03-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Manampathy G. Giridharan , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan
CPC classification number: F23R3/06 , F23R3/286 , F23R2900/03044
Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.
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