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    TURBINE AIRFOIL WITH LATERALLY EXTENDING SNUBBER HAVING INTERNAL COOLING SYSTEM
    3.
    发明申请
    TURBINE AIRFOIL WITH LATERALLY EXTENDING SNUBBER HAVING INTERNAL COOLING SYSTEM 有权
    具有内部冷却系统的侧向扩展的涡轮机的涡轮机

    公开(公告)号：US20150132147A1

    公开(公告)日：2015-05-14

    申请号：US14074930

    申请日：2013-11-08

    申请人： Carmen Andrew Scribner ,  Stephen John Messmann ,  Jan H. Marsh

    发明人： Carmen Andrew Scribner ,  Stephen John Messmann ,  Jan H. Marsh

    IPC分类号： F01D5/18

    CPC分类号： F01D5/188 ,  F01D5/187 ,  F01D5/22 ,  F01D5/3007 ,  F05D2260/201

    摘要： A turbine airfoil usable in a turbine engine and having at least one snubber with a snubber cooling system positioned therein and in communication with an airfoil cooling system is disclosed. The snubber may extend from the outer housing of the airfoil toward an adjacent turbine airfoil positioned within a row of airfoils. The snubber cooling system may include an inner cooling channel separated from an outer cooling channel by an inner wall. The inner wall may include a plurality of impingement cooling orifices that direct impingement fluid against an outer wall defining the outer cooling channel. In one embodiment, the cooling fluids may be exhausted from the snubber, and in another embodiment, the cooling fluids may be returned to the airfoil cooling system. Flow guides may be positioned in the outer cooling channel, which may reduce cross-flow by the impingement orifices, thereby increasing effectiveness.

    摘要翻译： 公开了一种可用于涡轮发动机并且具有至少一个具有缓冲冷却系统的缓冲器并且与翼型件冷却系统连通的涡轮机翼型。 缓冲器可以从翼型的外壳延伸到位于一排翼型内的相邻的涡轮机翼型。 缓冲冷却系统可以包括通过内壁与外部冷却通道分离的内部冷却通道。 内壁可以包括多个冲击冷却孔，其将冲击流体引导到限定外部冷却通道的外壁。 在一个实施例中，冷却流体可以从缓冲器排出，并且在另一个实施例中，冷却流体可以返回到翼型冷却系统。 流动引导件可以定位在外部冷却通道中，这可以减少冲击孔的交叉流动，从而增加效率。