摘要
针对带肋和双排出流孔通道,研究了肋角度和出流孔位置对流量系数分布和总压系数分布的影响.研究的肋角度为60°,90°和120°.出流孔分别位于相邻两肋之间距前肋1/4肋距、两肋中间、距后肋1/4肋距.研究表明:不同的肋角度和出流孔位置不改变流量系数和总压系数沿流向的分布规律;流量系数随肋角度增大而增大;60°和120°肋通道中总压系数绝对值接近且小于90°肋通道中的绝对值;两肋之间,出流孔位置靠近下游,将使流量系数增大,总压系数绝对值增大.
According to the flow in the channel with rib turbulators and double-row bleed holes,the effects of the rib turbulator orientation and the bleed hole location on the discharge coefficient and the total pressure coefficient distribution had been investigated.The rib tubulator orientation angles were 60°,90° and 120°.The bleed holes were located at 1/4 rib distance downstream from the front rib,the middle of rib distance,1/4 rib distance upstream from the behind rib.The results indicate that the rib turbulato...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第3期537-541,共5页
Journal of Aerospace Power
基金
国家"973"计划(2007CB0707701)
关键词
肋
出流孔
流量系数
压力分布
rib turbulators
bleed holes
discharge coefficient
pressure distribution
