火箭推进2018，Vol.44Issue(1)：36-43,8.
不同横向距离下双射流孔流动与冷却特性实验研究
Experimental study on flow and cooling characteristics of double-jet film-cooling holes at different spanwise distances
摘要
Abstract
Double-jet film-cooling structures on a flat plate at different spanwise distances(p/d=0, 0.5,1.0,1.5,2.0) are investigated experimentally.The time-averaged flow field at several cross-sections in downstream of the holes is measured by a seven-hole probe,and the film-cooling effectiveness on sur-face of the flat plate is measured with pressure sensitive paint (PSP).The measured results indicate that the streamwise distance (s/d) is 3.0,and the blowing ratio (M) is 0.5,1.0,1.5,and 2.0 while the density ratio (DR) is 1.0.The interaction between the two jets, its influence on the flow and cooling characters are investigated.The results show that,as p/d=0,the interaction between the holes is presen-ted as pressing effect,that is,the downstream jet is pressed on the wall surface by the upstream one and keeps attached to the surface,and the film-cooling effectiveness is not sensitive to blowing ratios;as p/d=0.5 and 1.0,the anti-kidney vortex effect dominates,both of the jets are pressed down on the surface, and the film coverage is good and the effectiveness is relatively high;as p/d≥1.5,the pressing effect al-most disappears,the anti-kidney vortex effect weakens,the distance between the jets increases,and the film coverage degrades.关键词
气膜冷却/双射流/压力敏感漆Key words
film-cooling/double-jet/pressure sensitive paint分类
航空航天引用本文复制引用
姚家旭,雷蒋..不同横向距离下双射流孔流动与冷却特性实验研究[J].火箭推进,2018,44(1):36-43,8.基金项目
国家自然科学基金(51776153) （51776153）
