凹槽孔槽深和动量比对气膜冷却特性的影响  

Effect of trench hole depth and momentum flux ratio on film cooling characteristics

作　　者：王振伟[1] 朱惠人[1] 张宗卫[1] 孟庆昆[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2012年第11期2455-2461,共7页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB707701)

摘　　要：采用瞬态液晶全表面测量技术测量了凹槽孔的气膜冷却特性,研究了动量比和槽深对冷却效率的影响,并和圆柱形孔的测量结果实施了比较.结果表明:冷气在凹槽内横向传播,凹槽抑制了冷气射流分离,凹槽孔比圆柱形孔提供更多的二维气膜.槽深孔径比为0.75是最佳的.随着动量比的增加,冷却效率值逐渐趋于稳定,冷却效率仅有轻微增加.Film cooling characteristics of trench hole were measured using a transient liquid crystal full-surface measurement technique. The influence of momentum flux ratio （I=0.5, 1, 2, 4） and trench depth （s=0. SD, 0.75D, D; D stands for film hole diame- ter） were studied comparison between trench hole and cylindrical hole was conducted. The results show that the trench suppresses coolant jet separation, and the trench hole provides greater lateral film coverage compared with the cylindrical hole. An optimum trench depth is s=0.75D. With a further increase in momentum flux ratio, the cooling effectiveness levels start to plateau, so increased coolant would not be warranted because only a slight increase in film cooling effectiveness would occur.

关 键 词：凹槽孔 气膜冷却 热色液晶 全表面测量 冷却效率 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]