摘要
对弯曲壁上的多孔气膜冷却方式的流量系数进行了实验研究,目的是确定在一定曲率的弯曲壁上不同开孔倾角冷却孔的平均流量系数随压力参数的变化规律,并从流动损失方面进行深入分析.研究结果表明,对于几何参数一定的多孔冷却方式,影响其流量系数的气动因素用压力参数来表示是合理的,但对于不同的开孔倾角,压力参数对流量系数的影响效果有很大差别.
An experimental investigation was conducted on the discharge coefficient of multi-holes cooling with different inclined angles in the curved wall for an aircraft engine combustor. The research purpose is to obtain the tendency of the average discharge coefficients with the pressure parameter,one of the most important influencing factors,and to analyze the flow dynamics. The research results indicate that as an aerodynamics factor the pressure parameter has significant impact on the discharge coefficient of the discrete holes for a given geometrical configuration, and for different inclined angles it has different effects.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第7期1127-1131,共5页
Journal of Aerospace Power
关键词
航空
航天推进系统
航空发动机
弯曲壁
多孔气膜冷却
流量系数
压力参数
aerospace propulsion system
aircraft engine
curved wall
multi-holes cooling
discharge coefficient
pressure parameter
