咽式进气道/等直隔离段的反压特性  

Back pressure characteristics of jaws inlet with constant-area isolator

作　　者：辜天来 张帅[1] 郑耀[1] 

机构地区：[1]浙江大学航空航天学院,浙江杭州310027

出　　处：《浙江大学学报（工学版）》2016年第7期1418-1424,共7页Journal of Zhejiang University：Engineering Science

基　　金：浙江省自然科学基金资助项目(LY13E060002)

摘　　要：对带等直隔离段的咽式进气道进行Ma 5飞行条件下流场的数值模拟,对比起动状态反压对内部复杂的流场结构及性能参数的影响,分析高反压引起的进气道不起动现象与机理.研究表明,起动状态下隔离段中激波串主要在俯仰方向上发展且不对称性明显,激波串出现初期进气道/隔离段的性能参数变化最快,超声速主流受到附面层挤压偏向隔离段底部和中心轴线的偏航两侧.高反压引起咽式进气道不起动后,分离结构被限制在俯仰压缩段,流量损失主要发生在侧向唇口,偏航压缩段内均为亚声速、高温高压气流.由于高内收缩比和几何构型影响,仅采用降低反压的方式难以实现再起动.The jaws inlet with a constant-area isolator was numerically analyzed under conditions of Ma 5 free stream and changing back pressures. Complicated flow field structures in starting and unstarting states were obtained and compared. Effects of the back pressure on performance of the inlet/isolator model were analyzed. Results show that the shock train is asymmetrical and it primarily develops in the pitching direction when the jaws inlet works in starting states. Performance of the inlet/isolator model decreases fastest at the early stage of occurrence of the shock train. Affected by the boundary layer development, supersonic flows in the constant-area isolator are crowded towards the bottom and two sides of the yaw direction. When the jaws inlet unstarts owing to high back pressures, the separation structure locates totally in the pitching compression section. The loss of inflow mass primarily bleeds off from the lateral lip. Flows in the yaw compression section are subsonic with high static temperature and high static pressure. It is hard to achieve restarting by only decreasing the back pressure because of the high contraction ratio and the unique geometry of the jaws inlet. © 2016, Zhejiang University Press. All right reserved.

关 键 词：高超声速 咽式进气道 等直隔离段 反压 激波串 不起动 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]