Multi pressure drop swirler ferrule plate

    公开(公告)号:US11994295B2

    公开(公告)日:2024-05-28

    申请号:US17651642

    申请日:2022-02-18

    CPC classification number: F23R3/16 F02C7/22

    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.

    Thermo-acoustic damper in a combustor liner

    公开(公告)号:US11898752B2

    公开(公告)日:2024-02-13

    申请号:US17932332

    申请日:2022-09-15

    Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.

    FUEL TEMPERATURE CONTROL SYSTEM
    95.
    发明公开

    公开(公告)号:US20230332549A1

    公开(公告)日:2023-10-19

    申请号:US17719659

    申请日:2022-04-13

    Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.

    MULTI PRESSURE DROP SWIRLER FERRULE PLATE
    98.
    发明公开

    公开(公告)号:US20230266006A1

    公开(公告)日:2023-08-24

    申请号:US17651642

    申请日:2022-02-18

    CPC classification number: F23R3/16 F02C7/22

    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.

    COMBUSTOR WITH A VARIABLE PRIMARY ZONE COMBUSTION CHAMBER

    公开(公告)号:US20230250961A1

    公开(公告)日:2023-08-10

    申请号:US17664975

    申请日:2022-05-25

    CPC classification number: F23R3/42 F23R3/002 F23R3/60

    Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.

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