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    Enhanced cooling apparatus for gas turbine engine airfoils
    2.
    发明授权
    Enhanced cooling apparatus for gas turbine engine airfoils 失效
    用于燃气涡轮发动机翼型的增强型冷却装置

    公开(公告)号：US5472316A

    公开(公告)日：1995-12-05

    申请号：US308227

    申请日：1994-09-19

    申请人： Mohammad E. Taslim ,  Samuel D. Spring ,  Thomas E. Demarche

    发明人： Mohammad E. Taslim ,  Samuel D. Spring ,  Thomas E. Demarche

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2260/2212

    摘要： An improved cooling passage configuration for a gas turbine engine airfoil is disclosed for enhancing convective cooling over that afforded by conventional wall turbulator ribs. An internal cooling passage bounded by pressure and suction side walls and at least one partition has raised turbulator ribs disposed on at least one side wall and the partition. A side wall turbulator rib extends over at least a portion of the side wall and abuts the partition. A turbulator rib disposed on the partition extends from a point spaced from the wall rib to the opposed side wall. The gap formed between the partition rib and wall rib accelerates a coolant flow passing therethrough, locally enhancing convective heat transfer. Partition ribs may be aligned with or offset from the wall ribs in the spanwise direction and may be normal to the primary direction of cooling flow or angled thereto. Convective heat transfer is particularly enhanced in flow passages having cavity height blockage due to wall ribs greater than about 10%.

    摘要翻译： 公开了一种用于燃气涡轮发动机翼型的改进的冷却通道构造，用于增强由传统的壁湍流肋提供的对流冷却。 由压力和吸力侧壁和至少一个隔板限定的内部冷却通道具有设置在至少一个侧壁和隔板上的湍流肋。 侧壁湍流肋在侧壁的至少一部分上延伸并邻接隔板。 设置在隔板上的湍流肋从与壁肋间隔开的位置延伸到相对的侧壁。 在分隔肋和壁肋之间形成的间隙加速了通过其中的冷却剂流，局部增强了对流热传递。 分隔肋可以在翼展方向上与壁肋对准或偏离，并且可以垂直于冷却流的主要方向或与其成角度。 由于壁肋大于约10％，具有腔高度阻塞的流动通道，对流传热特别增强。