气膜冷却喷孔附近的流场实验研究

Flow Field Behavior at Exit of Film Cooling Hole

在回流式传热风洞中，利用五孔针对用于航空发动机高温部件气膜冷却孔周围的流场进行了细致的测量，发现了喷孔出口截面存在部分主流被吸入孔内的孔吸流动现象．定义了充满系数Ｃｉ，讨论了该截面上的三维速度场和充满系数Ｃｉ在不同扇形孔几何参数和流动参数下的分布趋势．

Experiments are made to investigate the flow fields at the exit of film cooling hole for a closedcircuit wind tunnel with capability to control heat transfer. A fivehole directional probe is used to collect flow data.It is found that at the hole exit a portion of the main stream is drawn into the hole. Behavior of the 3D flow fields is discussed in detail with reference to the fullness factor Ci for a wide range of flow parameters and geometry of the fanshaped holes.