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公开(公告)号：US12025315B2
公开(公告)日：2024-07-02
申请号：US17811762
申请日：2022-07-11
Applicant: General Electric Company
CPC classification number: F23R3/42 , F02C3/14 , F02C7/00 , F23R3/002 , F23R2900/00017 , F23R2900/03041
Abstract: An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.
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公开(公告)号：US11994295B2
公开(公告)日：2024-05-28
申请号：US17651642
申请日：2022-02-18
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Kwanwoo Kim , Saket Singh , Perumallu Vukanti , Karthikeyan Sampath , Steven C. Vise , Nicholas R. Overman , Michael A. Benjamin
Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.
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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
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
CPC classification number: F23R3/06 , F23R3/16 , F23R3/28 , F23R2900/03044
Abstract: 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：US20230324047A1
公开(公告)日：2023-10-12
申请号：US17812897
申请日：2022-07-15
Applicant: General Electric Company
Inventor： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC classification number: F23R3/002 , F23R2900/03045 , F23R2900/00017 , F23R3/60
Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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公开(公告)号：US20230266007A1
公开(公告)日：2023-08-24
申请号：US17809381
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Karthikeyan Sampath , Perumallu Vukanti , Rimple Rangrej , Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/16 , F23R3/06 , F23R2900/00001 , F23R2900/03045 , F23R2900/03044
Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.
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Patent Agency Ranking
公开(公告)号：US20230266006A1
公开(公告)日：2023-08-24
申请号：US17651642
申请日：2022-02-18
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Kwanwoo Kim , Saket Singh , Perumallu Vukanti , Karthikeyan Sampath , Steven C. Vise , Nicholas R. Overman , Michael A. Benjamin
Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.
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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
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：US20230213191A1
公开(公告)日：2023-07-06
申请号：US17587169
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
CPC classification number: F23R3/06 , F23R3/28 , F23R3/16 , F23R2900/03044
Abstract: 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
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：US11572835B2
公开(公告)日：2023-02-07
申请号：US17317131
申请日：2021-05-11
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Varun Lakshmanan , Perumallu Vukanti , Allen M. Danis , Michael A. Benjamin
Abstract: A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.
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