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    Combustor
    21.
    发明授权
    Combustor 有权

    公开(公告)号：US12152779B1

    公开(公告)日：2024-11-26

    申请号：US18453500

    申请日：2023-08-22

    Applicant: General Electric Company

    Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

    IPC: F23R3/16 ,  F23L7/00

    Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.

    Turbine engine including a combustor
    22.
    发明授权
    Turbine engine including a combustor 有权

    公开(公告)号：US12130016B1

    公开(公告)日：2024-10-29

    申请号：US18326647

    申请日：2023-05-31

    Applicant: General Electric Company

    Inventor： Hiranya Nath ,  Clayton S. Cooper ,  Steven C. Vise ,  Michael A. Benjamin ,  Pradeep Naik ,  Ranganatha Narasimha Chiranthan ,  Perumallu Vukanti ,  Sibtosh Pal

    IPC: F23R3/12 ,  F23R3/46

    CPC classification number: F23R3/12 ,  F23R3/46

    Abstract: A combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.

    COMBUSTOR WITH BAFFLE
    23.
    发明公开
    COMBUSTOR WITH BAFFLE 审中-公开

    公开(公告)号：US20230220998A1

    公开(公告)日：2023-07-13

    申请号：US17694978

    申请日：2022-03-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Michael T. Bucaro ,  Clayton S. Cooper

    IPC: F23D14/70 ,  F23R3/06 ,  F23R3/28 ,  F23R3/50

    CPC classification number: F23D14/70 ,  F23R3/06 ,  F23R3/50 ,  F23R3/286 ,  F23D2210/00

    Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.

    ACTIVE BOUNDARY LAYER CONTROL IN DIFFUSER
    25.
    发明申请
    ACTIVE BOUNDARY LAYER CONTROL IN DIFFUSER 有权

    公开(公告)号：US20220373181A1

    公开(公告)日：2022-11-24

    申请号：US17325938

    申请日：2021-05-20

    Applicant: General Electric Company

    Inventor： Joseph Zelina ,  Clayton S. Cooper ,  Michael T. Bucaro ,  Steven C. Vise ,  John Thomas Herbon

    IPC: F23R3/10 ,  F02C3/14

    Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.

    SWIRLER-FERRULE ASSEMBLY
    27.
    发明申请
    SWIRLER-FERRULE ASSEMBLY 有权

    公开(公告)号：US20250035304A1

    公开(公告)日：2025-01-30

    申请号：US18913347

    申请日：2024-10-11

    Applicant: General Electric Company

    Inventor： Steven C. Vise ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Pradeep Naik ,  Kwanwoo Kim ,  Shai Birmaher ,  Perumallu Vukanti ,  Saket Singh ,  Karthikeyan Sampath

    IPC: F23D11/38 ,  B05B7/10

    Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

    Combustor with baffle
    29.
    发明授权
    Combustor with baffle 有权

    公开(公告)号：US11940151B2

    公开(公告)日：2024-03-26

    申请号：US17694978

    申请日：2022-03-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Michael T. Bucaro ,  Clayton S. Cooper

    IPC: F23R3/28 ,  F23R3/00 ,  F23R3/06 ,  F23R3/50

    CPC classification number: F23R3/286 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50

    Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.

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