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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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)
关键词
凹槽孔
气膜冷却
热色液晶
全表面测量
冷却效率
trench hole
film cooling
liquid crystal
full-surface measurement
cooling effectiveness
