摘要
利用数值模拟的方法研究了叶片前缘双出口孔射流冷却效率.该孔型是一种新概念气膜孔.吹风比变化范围为1.0～3.5,主流通道入口湍流度30%.结果表明,圆柱孔射流冷却效率和实验数据吻合较好,随着吹风比增加,单孔射流冷却效率减小.双出口孔有效地改善了叶片前缘冷却效率.吹风比从1.0增加到2.5时,冷却效率显著增加,吹风比为2.5和3.0时的冷却效率没有显著差别,吹风比为3.5时的冷却效率较低.双出口孔射流冷却效率径向分布比较均匀.
The flow and heat transfer of the film cooling from the film holes embedded in different space distributions were investigated numerically in several blowing ratios,so as to reveal the effects of span spaces and flow spaces.In the present study,the Reynolds number（Re） based on mainstream velocity and film hole diameter is 4 797,and the blowing ratio（M） alters from 0.2 to 2.0.Results show that：（1）in different span space models,the optimal span space is 1D;（2） better film cooling effectiveness is obtained in the assistant-behind hole model;（3） less influence of the blowing ration occurs in the assistant-behind hole model;and the level of vortex intensity keeps constant under the flow spaces,while the value and direction change sharply.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第10期2255-2260,共6页
Journal of Aerospace Power
基金
辽宁省教育厅基金
沈阳航空航天大学博士启动基金(09YB13)
关键词
涡轮叶片
气膜冷却
冷却效率
双出口孔
数值模拟
film cooling cooling effectiveness numerical simulation anti-vortex configuration film hole heat transfer
