基于PSP实验技术的双射流气膜冷却特性研究  

Characteristic of double-jet film cooling tested by pressure sensitive paint

作　　者：韩昌[1] 李佳[1] 李雪英[1] 任静[1] 蒋洪德[1] 

机构地区：[1]清华大学机械工程学院热能工程系燃气轮机研究中心,北京100084

出　　处：《航空动力学报》2010年第12期2770-2778,共9页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB210100)

摘　　要：基于压力敏感漆(PSP)实验技术研究了具有双射流、圆孔和扇形孔的气膜冷却系统在主流湍流度为6%,吹风比分别为0.5,0.8,1.0,1.2和1.5时的冷却特性.圆孔平均气膜冷却效率在吹风比为0.8到1.5范围内逐渐降低;而双射流和扇形孔在整个实验范围内随吹风比的增大而升高,这表明双射流很好地抑制了射流与壁面的吹离.在同等条件下,双射流气膜冷却效率优于圆孔,而低于扇形孔.实验条件下的数值模拟结果清楚地表明了圆孔、双射流和扇形孔分别形成的肾形涡系、反肾形涡系和弱肾形涡系是形成各自气膜冷却特性的主要因素.The characteristics of the film cooling system with double-jet,round and shaped holes were investigated under the condition of mainstream turbulence 6% and blowing ratio 0.5,0.8,1.0,1.2,1.5 in the study.The pressure sensitive paint（PSP） was implemented in the tests as the main measurement technique.The film cooling effectiveness decreases between blowing ratio 0.8 and 1.5 in the case of round holes,but increases in the whole experimental blowing ratio in the case of shaped holes and double-jet.It indicates that the double-jet restrains the lift-off of the cooling jet.The film cooling effectiveness of double-jet is better than that of the round holes,but poor than that of the shaped holes in the same conditions.Meanwhile,the vortex structures near the three focused holes obtained from the corresponding computations are major causes of the characteristics of the investigated film cooling systems.

关 键 词：燃气轮机 气膜冷却 双射流 压力敏感漆 反肾形涡 

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]