冷气掺混对涡轮叶栅气动损失影响的试验研究

Experimental study influence of cooling-air injection on the aerodynamic performance of rectangular turbine blade

对某型涡轮平面叶栅,在不同的主流雷诺数下,以多种喷射方式和不同的流量比喷射冷气,研究型面压力分布及出口气流场参数的变化。试验结果表明,冷气入射对叶片表面静压分布几乎没有影响,只对冷气孔位置附近压力产生影响,相对来说,压力面入射冷气导致的变化小于吸力面。随进口马赫数升高,在相同的冷气流量比下流动总压降低。然而,在相同的马赫数下,随着冷气流量比增大,压力面入射跟吸力面入射导致的总压变化规律不一样。

Experiments have been performed to measure the aerodynamic loss and display the distributions of state pressure on the blade exterior through a two- dimensional turbine blade with different mainstream flows. The results show that different locations to inject secondary flow for the change of state pressure on the blade exterior has not anything influcnee, just for the locations of cooling air injection. Correspondingly the change of cooling air injection from pressure side is less than from suction side. With the mainstream flow inereasing, the total prassure loss fall down. However, on the same mainstream flow, the rule of total pressure from pressure side is different to the rule from suction side with cooling airflow inscreaing.