摘要
针对无通道激波单纯由强逆压梯度诱导的附面层分离进行了吸附式数值与实验研究.研究对象为某大转折角高负荷吸附式压气机叶栅,利用准三维叶栅通道计算程序(MISES)进行抽吸流场数值模拟,在确定抽吸位置后进行了风洞实验验证.结果表明:抽吸后总压损失系数大幅度降低,对于单纯由强逆压梯度诱导的附面层分离,最佳抽吸位置应该位于附面层分离之后尚未充分发展之处;在确定抽吸位置时可以根据设计状态的分离状况进行;实际中需要的抽吸流量小于计算值;在数值计算中,具体的抽吸模型还有待进一步改进和修正,以使数值模拟更加准确.
Numerical calculation and experiment were conducted on suction of boundary layer whose separation was induced merely by strong adverse pressure gradient without passage shock. The research was performed for a highly loaded aspirated compressor cascade with large turning angle. Numerical simulation was conducted using MISES which was used for simulating the flow field of quasi-3-D cascade. After deciding the suction position, wind tunnel experiment was conducted. The results show that, loss coefficient is reduced remarkably after suction, and for the boundary layer whose separation is induced merely by strong adverse pressure gradient, the best position for suction lies in where separation has already happened but not fully developed; the suction position can be decided according to the separation in design condition; the suction mass flow required in practice is less than that in calculation; in the numerical calculation, the concrete suction model needs further improvement and correction, in order to make the simulation more accurate.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第1期133-139,共7页
Journal of Aerospace Power
基金
国家自然科学基金重点资助项目(51236006)
国家高技术研究发展计划(2008AA05Z202)
关键词
吸附式叶栅
附面层分离
抽吸位置
抽吸流量
风洞实验
aspirated cascade
boundary layer separation
suction position
suction mass flow
wind tunnel experiment
