亚声速涡轮导叶全气膜冷却特性实验研究

In order to study the full film cooling characteristics of subsonic turbine guide vane, the film cooling effectiveness of full coverage film cooling turbine vane at different mainstream inlet Reynolds number (Re=3.0×10 ⁵ ~9.0×10 ⁵ ), second flow mass flow rate ratio (MFR=5.5%~12.5%) and mainstream turbulenceintensity (Tu=1.3%, 14.7%) conditions is measured in short-duration high speed wind tunnel. There are 5 compound angle cylindrical hole rows on the leading edge to obtain a showerhead film cooling, 6 cylindrical holes rows on the pressure side and 3 rows on the suction side. The results show that in the range of mass flow rate ratio studied in the present paper, the film cooling effectiveness on pressure and suction side decreases with mass flow rate ratio increasing, while the effect of mass flow rate ratio on the film cooling effectiveness on the leading edge is opposite. The change of mainstream inlet Reynolds number mainly affects the film cooling effectiveness in the region of relative arc S/S _max <-0.6, at high Reynolds number (Re=9.0×10 ⁵ ) the highest film cooling effectiveness is obtained at high mass flow rate ratio, while at middle and low Reynolds number (Re=3.0×10 ⁵ , 6.4×10 ⁵ ) the highest film cooling effectiveness is obtained at low mass flow rate ratio. The film cooling effectiveness on the leading is not affected obviously by the change of turbulence intensity, while the film cooling effectiveness on pressure and suction side decreases with the mainstream turbulence intensity increasing.