出流角对旋转涡轮叶片前缘气膜冷却影响  

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

作　　者：韩枫 李海旺 HAN Feng;LI Hai-Wang(National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室

出　　处：《工程热物理学报》2020年第2期320-328,共9页Journal of Engineering Thermophysics

摘　　要：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<X/D<3范围内,出流角α=30°的气膜孔总能产生最高水平的平均冷效。当吹风比M=0.5,0.75和1.0,面平均气膜冷效随出流角度的增加而减小,当M=1.25时,面平均冷效随着出流角度的增大先降低后稍增大。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<X/D<3.When M=0.5,0.75 and 1.0,the area average film cooling effectiveness decreases as the injection angle increases.When M=1.25,the area average film cooling effectiveness first decreases and then increases slightly as the injection angle increases.

关 键 词：旋转 涡轮叶片 前缘 气膜冷却 冷却效率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]