摘要
采用数值模拟方法,对旋转状态下曲率表面的气膜冷却进行研究.通过不同的曲率半径和吹风比,得到了冷却效率的分布情况,从而获得吹风比和曲率两因素对气膜冷却效率的影响规律.研究结果表明:低吹风比下,冷却效率较好;高吹风比下,气膜容易脱离壁面;凸表面的冷却效率随着曲率半径的增加而逐渐减小;而凹表面的冷却效率随着曲率半径的增加而逐渐增大;凸表面上曲率的影响作用随着旋转数的增加而逐渐弱化;而凹表面上曲率的作用随着旋转数的增大而逐渐增强.
Numerical method was conducted to investigate film cooling performance over different rotating surfaces. Compared different models, the influences of curve and blowing ration were obtained with different conditions. The results show that： more film cooling effectiveness is obtained in low blowing ratio, and less effectiveness is occurred in high blowing ratio; For convex surfaces, the increasing curvature radius bring less efficiency; and while for concave surfaces, the increasing curvature radius create more efficiency ; The increasing Rotation number weakens curvature effect on convex surfaces, while strengthens curvature effect on concave surfaces.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2009年第7期812-816,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金资助项目(59675022)
关键词
气膜冷却
曲率
旋转
吹风比
film cooling
curvature
rotating
blowing ratio
