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公开(公告)号：US12085283B2
公开(公告)日：2024-09-10
申请号：US17340764
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Veeraraju Vanapalli , Karthikeyan Sampath , Deepak Ghiya , Perumallu Vukanti , Rajendra Mahadeorao Wankhade , Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh
CPC classification number: F23R3/42 , F02C3/02 , F02C3/14 , F05D2220/32 , F05D2240/35
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.
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公开(公告)号：US12085281B2
公开(公告)日：2024-09-10
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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公开(公告)号：US12072099B2
公开(公告)日：2024-08-27
申请号：US17682510
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Steven C. Vise , Ajoy Patra , R Narasimha Chiranthan , Manampathy G. Giridharan , Michael A. Benjamin , Clayton S. Cooper , Dharmaraj Pachaiappan
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. Increasing efficiency and meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher 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：US12055293B2
公开(公告)日：2024-08-06
申请号：US17932806
申请日：2022-09-16
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Karthikeyan Sampath , Pradeep Naik , Ranganatha Narasimha Chiranthan , Rimple Rangrej , Hiranya Nath , Ravindra Shankar Ganiger
CPC classification number: F23R3/06 , F23R3/002 , F23R2900/00017 , F23R2900/03042
Abstract: A combustor for a gas turbine has a combustor liner including an upstream liner portion, and a downstream liner portion. The upstream liner portion includes an outer shell and a heat shield panel, with a baffle cavity therebetween. The outer shell includes an outer shell cooling opening for providing a flow of compressed air to the baffle cavity, and the heat shield panel includes a heat shield panel cooling opening at a downstream end of the heat shield panel. A fence is arranged at a downstream side of the heat shield panel cooling opening and extends beyond a hot side surface of the heat shield panel into a combustion chamber. The heat shield panel cooling opening provides a flow of the compressed air therethrough from the baffle cavity for cooling of the heat shield panel and for providing at least partial dilution of combustion gases within the combustion chamber.
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公开(公告)号：US20240230091A9
公开(公告)日：2024-07-11
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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Patent Agency Ranking
公开(公告)号：US12031486B2
公开(公告)日：2024-07-09
申请号：US17717636
申请日：2022-04-11
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：US20240183536A1
公开(公告)日：2024-06-06
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 , Krushnakumar Venkatesan, V
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：US20240133553A1
公开(公告)日：2024-04-25
申请号：US17969913
申请日：2022-10-19
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：US20230383949A1
公开(公告)日：2023-11-30
申请号：US17932806
申请日：2022-09-16
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Karthikeyan Sampath , Pradeep Naik , Ranganatha Narasimha Chiranthan , Rimple Rangrej , Hiranya Nath , Ravindra Shankar Ganiger
IPC: F23R3/06
CPC classification number: F23R3/06 , F23R2900/00017 , F23R2900/03042
Abstract: A combustor for a gas turbine has a combustor liner including an upstream liner portion, and a downstream liner portion. The upstream liner portion includes an outer shell and a heat shield panel, with a baffle cavity therebetween. The outer shell includes an outer shell cooling opening for providing a flow of compressed air to the baffle cavity, and the heat shield panel includes a heat shield panel cooling opening at a downstream end of the heat shield panel. A fence is arranged at a downstream side of the heat shield panel cooling opening and extends beyond a hot side surface of the heat shield panel into a combustion chamber. The heat shield panel cooling opening provides a flow of the compressed air therethrough from the baffle cavity for cooling of the heat shield panel and for providing at least partial dilution of combustion gases within the combustion chamber.
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公开(公告)号：US20230366548A1
公开(公告)日：2023-11-16
申请号：US17823198
申请日：2022-08-30
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Perumallu Vukanti , Ajoy Patra , Pradeep Naik , Hiranya Nath
IPC: F23R3/00
CPC classification number: F23R3/005
Abstract: A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.
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