摘要
为了研究前缘凸脊结构对气膜冷却的影响规律,设计3种不同堵塞比的凸脊模型,研究气膜冷却效率随吹风比、堵塞比的变化规律,并运用数值模拟方法分析再附区域的流场分布。研究结果表明,与典型的圆柱形气膜孔相比,前缘凸脊的存在可以使气膜冷却效率提高130%以上;前缘凸脊在大吹风比下的作用更加明显;堵塞比B为0.21时气膜冷却效率最高;数值模拟结果与试验结果吻合得较好;在特定范围内,吹风比的增大或凸脊堵塞比的增大有利于提高气膜再附区域的展向覆盖,进而提高气膜冷却效率。
In order to study the effect of the tabs-ridged located along the upstream edge of declining holes on the film cooling, three types of the fill cooling holes with different blockage ratio are designed to study the change of the film cooling efficiency with the blowing ratio and blockage ratio, and the velocity fields near the reattachment are studied by using numerical simulation. The results show that the film cooling efficiency of the film cooling holes with the tabs-ridged is higher than the typical round film cooling holes by 130% at least. The film cooling efficiency is increased as the blowing ratio increases. The film cooling efficiency is highest when the blockage ratio is 0.21. The numerical results agree well with the experimental results. Increase of blowing ratio or blockage ratio improves the spanwise coverage of reattachrnent area and then the film cooling effectiveness in a definite range.
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2009年第9期312-316,共5页
Journal of Mechanical Engineering
基金
高等学校博士学科点专项科研基金资助项目(20070287040)
关键词
航空和航天推进系统
凸脊
气膜冷却效率
Aerospace propulsion system Tabs-ridged Film cooling effectiveness
