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公开(公告)号：US20230213194A1
公开(公告)日：2023-07-06
申请号：US17699735
申请日：2022-03-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Manampathy G. Giridharan , Ajoy Patra , R Narasimha Chiranthan
CPC classification number: F23R3/286 , F23R3/14 , F23R2900/03042
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.
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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：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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公开(公告)号：US11649966B1
公开(公告)日：2023-05-16
申请号：US17689070
申请日：2022-03-08
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 turbine engine having a combustion section. The combustion section can have a combustor, at least one fuel cup, and at least one ignition tube. The combustor can include a combustor liner and a dome wall, which together at least partially define a combustion chamber. The at least one fuel cup can include a swirler and a fuel injector. The at least one ignition tube can include an outlet directly fluidly coupled to the combustion chamber.
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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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Patent Agency Ranking
公开(公告)号：US12222104B2
公开(公告)日：2025-02-11
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
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：US20240328360A1
公开(公告)日：2024-10-03
申请号：US18742260
申请日：2024-06-13
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：US20240318822A1
公开(公告)日：2024-09-26
申请号：US18663324
申请日：2024-05-14
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 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：US11828465B2
公开(公告)日：2023-11-28
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 , F23R3/286 , 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：US20230266009A1
公开(公告)日：2023-08-24
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
CPC classification number: F23R3/286 , F23R3/002 , F02C7/22 , F05D2240/35
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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