叶片前缘喷气对大转角涡轮平面叶栅气动性能的影响

Influence of cooling-air injection from leading edge on the aerodynamic performance of rectangular turbine cascade with large turning angle

对具有前缘逆主流不同位置喷射冷气的大转折角气冷涡轮直叶栅进行了详细的流道内部测量。实验结果表明,冷气喷射改变了叶片型面静压分布规律;前缘不同位置喷气对流道内部通道涡和端壁附面层的影响差异较大;不同冷却方案导致损失增加的机理不同,损失增加量级也有所不同。

Measurements of flow passage inside a rectangular turbine cascade with large turning angle while cooling-air injection upstream from three different rows at leading edge were performed. Experimental results show that the static pressure distributions are changed due to the coolant air. The cooling-air injections form different rows have different effects on the passage vortex and end-wall boundary layer; the amount of loss increase differs from each other in three cases due to the different mechanism of loss increase.