Cooled component for a gas turbine engine

    公开(公告)号:US11326518B2

    公开(公告)日:2022-05-10

    申请号:US16751494

    申请日:2020-01-24

    Abstract: A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.

    FUEL DISPENSING APPARATUS AND METHOD OF OPERATION
    2.
    发明申请
    FUEL DISPENSING APPARATUS AND METHOD OF OPERATION 审中-公开
    燃料分配装置和操作方法

    公开(公告)号:US20160003158A1

    公开(公告)日:2016-01-07

    申请号:US14790951

    申请日:2015-07-02

    Abstract: A fluid dispensing apparatus that may be additive manufactured as one unitary piece and may be a fuel injector for a gas turbine engine includes a radial displacement bellows having an outer surface that faces and may be exposed to a surrounding environment and an interior surface that faces and may define at least in-part a flowpath extending along a centerline. The radial displacement bellows is constructed and arranged to move between an expanded state when a pressure differential between the environment and the flowpath is low to a restricted state when the pressure differential is high.

    Abstract translation: 可以作为一个整体件制成的并且可以是用于燃气涡轮发动机的燃料喷射器的流体分配装置包括径向位移波纹管,其具有面向并可能暴露于周围环境的外表面和面向和 可以至少部分地限定沿着中心线延伸的流路。 当压差高时,径向位移波纹管被构造和布置成当环境和流路之间的压差低到受限状态时在膨胀状态之间移动。

    COOLED COMPONENT FOR A GAS TURBINE ENGINE
    6.
    发明申请

    公开(公告)号:US20200256250A1

    公开(公告)日:2020-08-13

    申请号:US16751494

    申请日:2020-01-24

    Abstract: A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.

    TUBE ASSEMBLY
    7.
    发明申请
    TUBE ASSEMBLY 审中-公开

    公开(公告)号:US20180187982A1

    公开(公告)日:2018-07-05

    申请号:US15905120

    申请日:2018-02-26

    Abstract: A tube assembly that may be for a fuel nozzle of a fuel system of a gas turbine engine may have a first tube defining a first flowpath along a centerline, a second tube generally spaced radially outward from the first tube with a first void located between and defined by the first and second tubes, and a support structure located in the first void and extending between the first and second tubes. The support structure is constructed and arranged to minimize or eliminate thermal conduction between the tubes. The entire assembly may be additive manufactured as one unitary piece. One example of a method of operation may include designed-for breakage of the structural support due to thermal stresses thereby further minimizing thermal conduction between tubes.

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