Method of operating a combustor with a variable combustion chamber

    公开(公告)号:US11668462B1

    公开(公告)日:2023-06-06

    申请号:US17664976

    申请日:2022-05-25

    Abstract: A method of operating a combustor of a gas turbine, the combustor including a combustor liner that defines a total combustion chamber volume, and has a primary combustion zone defining a primary volume. The combustor liner includes a movable portion that is arranged to be actuated to adjust a percentage of the primary volume with respect to the total combustion chamber volume. The method includes, at a first operating state of the gas turbine, adjusting a size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume, and at a second operating state of the gas turbine different from the first operating state, adjusting the size of the primary volume to a second percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

    COMBUSTOR FOR A GAS TURBINE ENGINE
    106.
    发明申请

    公开(公告)号:US20220390110A1

    公开(公告)日:2022-12-08

    申请号:US17340585

    申请日:2021-06-07

    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; 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; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

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