涡轮叶片前缘气膜冷却的数值研究

对前缘带有2排冷却孔的高压涡轮叶栅进行了气膜冷却数值计算,在吹风比分别为0、0.7、1.1、1.5的情况下得到了叶片型面的静压分布,并将计算结果与实验数据进行了对比研究.此外,还详细分析了冷却孔出口附近区域的流场特性.结果表明,吹风比对叶片型面的压力分布影响不大,只是在冷却孔附近有较为明显的变化.同时,由于冷气射流的注入,在冷却孔后出现了一对旋转方向相反的肾形涡,此时增大吹风比不会对旋涡产生明显的影响,但对旋涡下游流场的影响比较明显.

Numerical Study on the Effect of Film Cooling at Leading Edges of Turbine Blades

Film cooling of high pressure turbine blade cascades,which are provided with two rows of cooling orifices at their leading edges,had been numerically calculated,the static pressure distribution over the blades' profiled surfaces,respectively for the blowing rates 0,0.7,1.1,and 1.5 obtained,and calculation results compared with experimental results.Moreover,particularities of flow fields near the cooling orifices were analyzed in detail.Results show,that the blowing rate has but a small effect on the blades' profiled surface and only a noticeable effect can be observed in the vicinity of the cooling orifices.Simultaneously,caused by the cooling jet flow,a pair of kidney shaped vortices,rotating in directions opposite to one another,are formed behind each cooling orifice,not markedly effected by increasing blowing rate,which nevertheless exerts a noticeable influence on the flow field downstream the vortices.Figs 5,table 1 and(refs 9.)