出流角对旋转涡轮叶片前缘气膜冷却影响

基于频闪拍照和稳态液晶测温技术,实验研究了不同气膜孔出流角对旋转态整级涡轮叶片前缘外壁面的气膜冷却特性的影响。实验中,叶片前缘处的主流雷诺数为6.3378×104。实验转速为574 r/min,对应的旋转数为0.0018。平均吹风比从0.5变化到1.25。射流采用N2,其对应的密度比为1.04。结果表明:展向平均气膜冷效是随吹风比的增加而单调增加的,其中最佳吹风比为M=1.25。对于所有吹风比,在-4.3

Effect of the Injection Angle on the Leading Edge Film Cooling of a Rotating Turbine Blade

Experimental investigations were performed to study the effect of the injection angle of cylindrical holes on the leading edge region film cooling of a turbine blade under rotating conditions based on stroboscopic imaging technique and thermochromic liquid crystal.The Reynolds number was 6.3378×104 at the leading edge.Turbine speed was 574 r/min and the rotating number was0.0018.The average blowing ratio ranging from 0.5 to 1.25.N2 was used as the coolant to achieve a density ratio of 1.04.Results show that the span-wise average film cooling effectiveness monotonously increases as the blowing ratio increases with the best blowing ratio M=1.25.At each blowing ratio,the a=300 case always yields the highest average film cooling effectiveness in the region of-4.3