涡轮静叶表面全气膜冷却换热实验研究

Heat Transfer Experimental Investigation on Full Film Cooling of Turbine Vane Surface

采用放大的涡轮静叶模型,利用大尺度低速线性叶栅风洞进行实验,测量了涡轮导向叶片表面完全气膜覆盖情况下局部换热系数分布特性。风洞实验段由三个叶片组成,中间叶片为实验叶片,由有机玻璃制成。叶片表面共有54排孔,前缘8排,压力面21排,吸力面25排。对叶片前腔和后腔表面的换热情况分别进行实验,主要研究了不同质流比对换热特性的影响。研究结果表明:气膜的完全覆盖使叶片表面的换热情况得以明显改善,换热系数的具体分布随质流比的变化有所不同。

Detailed heat transfer performance on turbine vane surface with full coverage film cooling was studied experimentally. A three-vane liner cascade in a large-scale low-speed opening wind tunnel was used in the experiment. There were 54 rows of film cooling holes in all on the surface of middle vane made of polymethyl methacrylate, 8 rows on the leading edge, 21 rows on the concave surface and 25 rows on the convex surface. The experiments were carried out on anterior cavity and posterior cavity of vane respectively under various mass ratios. The results reveal that significant improvement for heat transfer level is obtained because of full coverage film on vane. The distributions of local heat transfer coefficient are different with various mass ratios.