摘要
对大宽高比大S弯亚音扩压器的流动进行了试验研究,通过流谱观察、壁面静压分布曲线、截面总压分布图和出口截面旋流场分析其流动特性.此外,试验表明在分离点前安装适当结构参数的埋入附面层涡流发生器能够大大缩小分离区的范围,从而使其性能得到改善.
This paper presents the experimental results of the flow characteristic in a high aspect ratio and highly curved S-berid subsonic diffuser.The flow feature is analysed by using the flow visualization,the static pressure distribution,the total pressure contour map and the swirl flow field at exit.The paper also presents the result of separation control in the S-bend diffuser.The experimental result shows that the separation region can be reduced and the diffuser performance can be improved by using the boundary-layer submerged vortex generators if the location installed and the geometrical parameters of the vortex generator are selected property.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1991年第6期17-22,共6页
Journal of Propulsion Technology
关键词
进气道
边界层
扩压器
航空发动机
Inlet,Flow characteristic,Boundary layer control
