摘要
为了研究非常规扩张孔的流动特性,测量了一排7个双向扩张孔的平均流量系数.气膜孔的前倾角为20°,45°和90°,径向角为0°,30°和65°,孔间距与孔径比为2,3和4.动量比变化范围为1到8.结果表明,径向角为0°的流量系数随前倾角的增加显著增加.前倾角为20°的流量系数随径向角的增加略有减小.前倾角为90°的流量系数随孔间距的增加而增加.
This paper presented discharge coefficients of the expanded holes at inlet and outlet with plane angles of 20°,45°,90°,radial angles of 0°,30°,65° and the ratios of pitch to diameter of 2,3,4.The momentum flux ratios varied in the range from 1 to 8.The results show that discharge coefficients of radial angle =0° increase significantly when the plane angles increase from 20° to 90°.The effect of plane angle becomes weak with the increasing radial angles.Radial angles have weak influence on the discharge coef...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第3期499-506,共8页
Journal of Aerospace Power
关键词
涡轮叶片
气膜冷却
流量系数
实验
turbine
film cooling
discharge coefficient
experiment
