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    Fuel nozzle and swirler
    2.
    发明授权
    Fuel nozzle and swirler 有权

    公开(公告)号：US12123592B2

    公开(公告)日：2024-10-22

    申请号：US17686904

    申请日：2022-03-04

    Applicant: General Electric Company

    Inventor： Michael T. Bucaro ,  Clayton S. Cooper

    IPC: F23D14/62 ,  F23D14/58 ,  F23D14/70 ,  F23R3/06 ,  F23R3/28

    CPC classification number: F23D14/62 ,  F23D14/58 ,  F23D14/70 ,  F23R3/06 ,  F23R3/286

    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 liner, a dome assembly coupled to the combustor liner, a fuel nozzle fluidly coupled to the dome assembly, a combustion chamber fluidly coupled to the fuel nozzle, and at least one set of dilution openings located in the dome assembly or combustor liner that fluidly couple to the combustion chamber. A swirler can define at least one passage extending between at least one annular entrance and at least one annular exit, wherein the at least one annular entrance is fluidly coupled to the compressor section. A variable area device is movable relative to the at least one set of dilution openings or at least a portion of the swirler.

    COMBUSTOR WITH BAFFLE
    5.
    发明公开
    COMBUSTOR WITH BAFFLE 审中-公开

    公开(公告)号：US20240210036A1

    公开(公告)日：2024-06-27

    申请号：US18597287

    申请日：2024-03-06

    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.

    PASSIVE FUEL COUPLED DYNAMIC MITIGATION DEVICE
    7.
    发明申请
    PASSIVE FUEL COUPLED DYNAMIC MITIGATION DEVICE 有权

    公开(公告)号：US20220372915A1

    公开(公告)日：2022-11-24

    申请号：US17323088

    申请日：2021-05-18

    Applicant: General Electric Company

    Inventor： Gurunath Gandikota ,  Steven Clayton Vise ,  Clayton S. Cooper ,  Michael A. Benjamin

    IPC: F02C7/22

    Abstract: A gas turbine engine that is configured to mitigate fuel coupled dynamics. The engine includes a combustor, a fuel delivery system, a fuel manifold line; and a device configured to mitigate fuel coupled dynamics. The device is attached to the fuel manifold line and includes a housing and a reflector. The housing includes a wall and the wall defines a housing surface that is configured to reflect waves conducted by fuel within the fuel delivery system. The reflector is positioned within the housing and the reflector includes an anterior surface that is configured to reflect waves conducted by fuel within the fuel delivery system such that wave the reflected waves can strike the surface.

    Rotating Detonation Combustor
    8.
    发明申请
    Rotating Detonation Combustor 审中-公开

    公开(公告)号：US20180231256A1

    公开(公告)日：2018-08-16

    申请号：US15429655

    申请日：2017-02-10

    Applicant: General Electric Company

    Inventor： Sibtosh Pal ,  Joseph Zelina ,  Arthur Johnson ,  Clayton S. Cooper ,  Steven Vise

    IPC: F23R7/00 ,  F02C5/02

    CPC classification number: F23R7/00 ,  F02C5/02 ,  F02C7/264 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/35

    Abstract: A rotating detonation combustion system includes an outer wall and an inner wall together defining at least in part a combustion chamber and a combustion chamber inlet. A nozzle of the rotating detonation combustion system is located at the combustion chamber inlet, the nozzle defining a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction. The nozzle further defines a throat between the nozzle inlet and nozzle outlet. A fuel injection port is also provided, the fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to a flow of oxidizer received through the nozzle inlet.

    COMBUSTOR INCLUDING A STEAM INJECTOR OPERABLY INJECTING STEAM INOT A TRAPPED VORTEX CAVITY
    9.
    发明申请
    COMBUSTOR INCLUDING A STEAM INJECTOR OPERABLY INJECTING STEAM INOT A TRAPPED VORTEX CAVITY 有权

    公开(公告)号：US20250067439A1

    公开(公告)日：2025-02-27

    申请号：US18453506

    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: F23R3/28

    Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

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