IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    12.
    发明公开
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的涡轮螺栓固定器的冷却

    公开(公告)号:EP2877705A4

    公开(公告)日:2015-11-11

    申请号:EP13813721

    申请日:2013-03-28

    Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.

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