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公开(公告)号：US20230204213A1
公开(公告)日：2023-06-29
申请号：US17691781
申请日：2022-03-10
Applicant: General Electric Company
Inventor： Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Ajoy Patra , Manampathy G. Giridharan , Steven C. Vise , Michael A. Benjamin , Sripathi Mohan , R Narasimha Chiranthan , Joseph Zelina
CPC classification number: F23R3/14 , F23R3/286 , F23D11/383
Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives 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 carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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公开(公告)号：US10598380B2
公开(公告)日：2020-03-24
申请号：US15711203
申请日：2017-09-21
Applicant: General Electric Company
Inventor： David Albin Lind , Rishikesh Karande , Pradeep Naik , Ajoy Patra , Gregory Allen Boardman
Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into 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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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：US12163660B2
公开(公告)日：2024-12-10
申请号：US18484987
申请日：2023-10-11
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
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Patent Agency Ranking
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：US20240044493A1
公开(公告)日：2024-02-08
申请号：US18484987
申请日：2023-10-11
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
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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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