亚声速涡轮导叶前缘气膜冷却特性实验研究

In order to study the leading edge film cooling characteristics of subsonic turbine guide vane, the film cooling effectiveness and heat transfer coefficient of leading edge film cooling turbine vane in different mainstream inlet Reynolds number (Re=3.0×10⁵~9.0×10⁵), second flow blowing ratio (M=0.5~2.4) and mainstream turbulence intensity (Tu=1.3%, 14.7%) conditions were measured in short-duration high speed wind tunnel. There are 8 laid-back shaped hole rows on the leading edge to obtain a showerhead film cooling. The results show that in the range of blowing ratios studied in the present paper, the film cooling effectiveness on leading edge and pressure side increases with blowing ratio increasing, while the film cooling effectiveness on the suction side increases and decreases with blowing ratio increasing, the optimum blowing ratio is 0.8. In the range of Re=3.0×10⁵~9. 0×10⁵, the change of mainstream inlet Reynolds number has little effect on film cooling effectiveness distribution. The film cooling effectiveness decreases with turbulence intensity increasing, the average film cooling effectiveness at high mainstream turbulence intensity decreases around 50% in M=0.5 condition, while it decreases around 10% in M=2.4 condition; the heat transfer coefficient ratio on the leading edge and the coolant reattachment region of relative arc -0.4<S/S_max<-0.3 on pressure side is high. In high mainstream turbulence intensity condition, the heat transfer coefficient ratio is lower and the effects of blowing ratio on the heat transfer coefficient ratio are smaller.