GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING
    2.
    发明申请
    GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING 审中-公开
    气体涡轮发动机气动翼片,带有边缘倾斜和冲击冷却

    公开(公告)号:WO2015112225A3

    公开(公告)日:2015-09-24

    申请号:PCT/US2014064018

    申请日:2014-11-05

    Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.

    Abstract translation: 燃气涡轮发动机翼型件包括翼型结构,其包括由具有前缘的外壁提供的外表面。 翼型结构内的径向延伸的内壁分隔第一和第二径向冷却通道。 第一个冷却通道设置在前缘附近。 径向延伸的沟槽位于前缘。 冲击孔设置在内壁中并且构造成将冷却流体从第二冷却通道引导到第一冷却通道并且在前缘处引导到外壁上。

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