GAS TURBINE ENGINE AIRFOIL TRAILING EDGE PASSAGE AND CORE FOR MAKING SAME
    2.
    发明申请
    GAS TURBINE ENGINE AIRFOIL TRAILING EDGE PASSAGE AND CORE FOR MAKING SAME 有权
    气体涡轮发动机飞行器通道和核心用于制造

    公开(公告)号:US20150118064A1

    公开(公告)日:2015-04-30

    申请号:US14390496

    申请日:2013-03-12

    Abstract: An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.

    Abstract translation: 机翼具有主体,其包括邻接压力侧和吸力侧的前缘和后缘,以提供外部翼型表面。 冷却通道在径向方向上从根部延伸到尖端。 后缘冷却通道将冷却通道与后缘相互连接。 后缘冷却通道包括不同尺寸的第一和第二基座,其相对于具有相同尺寸的基座并且相对于不同尺寸的基座以重复图案布置。

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