摘要
在倾斜圆柱形气膜孔中加装一种特制的楔形突片结构,可以改善气膜孔下游平均冷却效率,本文对此进行了数值研究。研究结果表明:突片的高度对冷却效率影响不大;在大吹风比下突片对冷却效率的提高起显著作用;突片的存在使气膜孔下游壁面得到了很好的保护。随着突片边长增大,平均冷却效率提高。
The flow fields and cooling effectiveness of the film cooling from a row of cylindrical angled holes with special sphenoid tabs are investigated numerically at different blowing ratios. The tabs are located along the upstream edge of the holes in order to improve film cooling effectiveness in the downstream area. Results show that the influence of the tab＇s height on the film cooling effectiveness is inconspicuous; the tabs have great influence on the cooling effectiveness under higher blowing ratios, and they protect the downstream blade surface from the detrimental effects of the hot combustion gases. The average film cooling effectiveness improvement is significant in the cases of higher tab blocking ratio.
出处
《燃气涡轮试验与研究》
2007年第2期32-36,共5页
Gas Turbine Experiment and Research
关键词
航空
航天推进系统
气膜冷却
突片
数值计算
aerospace propulsion system
film cooling
tabs
numerical computation
