短周期风洞叶栅表面冷却特性实验

Experimental Study of Film Cooling Effectiveness of the Blade Surface in Short Duration Wind Tunnel

通过在高速风洞中对带气膜孔叶片进行冷却效率的详细测量,研究了进口雷诺数、出口马赫数以及二次流与主流流量比对气膜冷却效率分布规律的影响,测量了Re为200 000～600 000,Ma为0.37～1.16,流量比Mr为0.05、0.1、0.15时叶片表面的冷却效率。结果表明:叶片表面气膜冷却效率随马赫数的增大而减小,雷诺数对气膜冷却效率没有明显的影响;增大二次流流量可以提高压力面的冷却效率,降低吸力面的冷却效率。

The detailed measurement of cooling effectiveness was carried on the high speed wind tunnel for blade with film hole, and studied the Mach and Reynolds and secondary flow that have influence on the film cooling effectiveness which were measured within Re （Reynolds number） = 200 000 -600 000, Ma （Mach number） =0.37 -1.16, Mr（ Mass flow ratio） =0.05,0.1,0.15. Research results show that as Mach increases, the film cooling effectiveness of the blade surface reduces at the same time. Reynolds number has no obvious effect on the film cooling effectiveness. Increasing the secondary flow can improve the film cooling effectiveness of the pressure surface and reduce the film cooling effectiveness of the suction surface.