摘要
为探索改善小角度进气条件下叶栅栅前流动周期性的试验控制方法,以某跨音速压气机平面叶栅试验件为研究对象,采用数值模拟方法研究了小角度进气条件下尾板偏移角度和端壁通道宽度对叶栅栅前周期性分布的影响。研究结果发现:叶栅在小角度进气时栅前周期性分布特性较差,调节下尾板角度对栅前周期性具有一定影响,调节上尾板对近端壁通道气流难以起到导流效果;采用全叶片式叶栅进气方案时,仅端壁附近流道的流动受到边界附面层影响,而中间测量通道内的周期性分布得到明显改善;改变近端壁两端通道宽度可以有效改善栅前流场周期性。
A transonic compressor linear cascade test piece is taken as the research object,and the effect of tailboard deflection angle and passage width close to end wall on flow periodicity distribution of cascade front flow under small stagger angle inlet is numerical studied,which is expected to explore a new experimental method to improve periodicity of cascade front flow.The computational results show that:the flow periodicity distribution in front of cascade is poor,which can be changed by the transformation of deflection angle of lower tailboard,but it is discovered from the flow field analysis that an upper tailboard has no effect on the guidance of air in flow passage;when tailboards are replaced by blades with the same pitch,only the flow near end wall is affected by boundary layer,while the periodic distribution in intermediate measurement channel is obviously improved;the flow periodicity in front of cascade can be improved by change of passage width close to end wall.
作者
杨泳
徐开俊
李珊珊
熊平化
连洁
YANG Yong;XU Kai-jun;LI Shan-shan;XIONG Ping-hua;LIAN Jie(Civil Aviation Flight University of China,Guanghan,Sichuan 618307;AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241;Chengdu Hang Li(Group)Industrial Co.,Ltd.,Pengzhou,Sichuan 611936)
出处
《液压与气动》
北大核心
2018年第9期92-97,共6页
Chinese Hydraulics & Pneumatics
基金
国家自然科学基金民航联合基金(U1533127)
中央高校教育教学改革专项(E20180301)
学校科研基金面上项目(J2015-02)
关键词
平面叶栅
数值模拟
周期性
压气机
linear cascade
numerical simulation
periodicity
compressor
