摘要
采用红外热像仪对具有不同孔径和排列方式的离散孔切向进气的气膜冷却结构的绝热壁温进行了测试,获得了气膜冷却效率随吹风比和无量纲流向距离变化的经验关联式。研究结果表明,在本文研究的参数范围内,离散孔切向进气气膜冷却的冷却效率随吹风比和气膜孔直径的增大而上升;在气膜孔板开孔率和吹风比相同时,由排型引起的冷却效率差异不是很大。
The film cooling effectiveness of the tangential discrete holes film cooling configuration with different hole diameters and arrangement was experimentally investigated using infrared camera. The empirical correlations of cooling effectiveness to blowing ratio and non-dimensional flow-wise distance （X/S） were obtained,which agreed well with the experimental results. The results show that ,for the present investigation conditions ,the film cooling effectiveness will be increased with the increase of blowing ratios and the diameter of film hole; with the same blowing ratios and porosity of holes, the hole arrangement has little effect on cooling effectiveness.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期290-296,共7页
Journal of Aerospace Power
关键词
航空
航天推进系统
气膜冷却
冷却效率
实验研究
aerospace propulsion system
film cooling
cooling effectiveness
experimental investigation
