摘要
对平板表面的双扇形孔排气膜冷却特性进行了研究,包括孔节距、动量比和主流湍流度对气膜冷却效率的影响.气膜孔的直径为d,气膜孔与主流方向的夹角为45°.孔节距有2d,3d和4d,动量比有1,2和4,主流湍流度有0.4%和8%.结果表明,气膜冷却效率随孔节距增大而降低;孔节距为2d时,动量比增大会引起气膜冷却效率显著增加;孔节距为4d时,气膜冷却效率受动量比的影响相对较小;在孔节距及动量比均较大时,主流湍流度的增大会导致气膜冷却效率较为明显的下降.
This paper presents detail measurements of film cooling effectiveness in a flat plan for a row double fan shaped holes. The streamwise angle of hole was 45°and thediame ter of hole was d. The pitch to diameter ratio（p/d） contained 2,3 and 4. The momentum flux ratios varied from 1 to 4 and the turbulence level contained 0.4% and 8%. The result in dicated that the double fan shaped holes made significant improvement of film cooling effec tiveness compared with the round holes. The variety of the p/d had great effects on film cooling effectiveness. Increasing the momentum flux ratio lead to large improvement of film cooling effectiveness at the p/d=2, while the momentum flux ratio had small effects on it at the p/d=4. The enhancement of turbulence level lead to obvious decrease in film coolingef fectiveness when p/d is large and the momentum ratio is high.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期2082-2087,共6页
Journal of Aerospace Power
关键词
气膜冷却
双扇形孔
孔节距
湍流度
film cooling, double fan-shaped hole, hole pitch, turbulence level
