摘要
对弯曲多孔壁气膜冷却整体冷却效率进行了深入研究.弯曲多孔壁由等曲率凹壁面多孔壁实验板来模拟,实验研究了相同排列方式下2种不同小孔倾角方案整体气膜冷却效率,分析了弯曲通道曲率对冷却效率的影响,得到了沿流程的展向平均冷却效率及x/d=21.8和x/d=65.3处展向冷却效率分布.研究结果表明,吹风比是影响凹壁面小孔气膜冷却效率的关键因素;随着吹风比的增大,2种孔倾角冷却效率的差异变小;主流通道中气体的流动规律对冷却效率有较大影响.
Overall cooling effectiveness of curved wails with discrete angled holes has been studied in the paper through approximate simulation employing experimental concave wails with a constant curvature, which were applied intensively in the curved duct for turboshaft engine reverse-flow combustor. An experiment by heat transfer method for the overall cooling effectiveness was performed and the effect of blowing ratio on the overall spanwise averaged cooling effectiveness was obtained. The experimental result shows an improved overall cooling performance for the curved wall and the insignificant difference between the discrete holes with 30° inclined angle and normal to the concave wall at high blowing ratio. The flow in the curved duct has influence on the overall cooling effectiveness significantly.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第2期210-215,共6页
Journal of Aerospace Power
关键词
航空
航天推进系统
航空发动机
回流燃烧室
弯曲通道
冷却效率
aerospace propulsion system
aircraft engine
reverse-flow combustion chambers
curved tube flow
cooling effectiveness
