双模态燃烧室隔离段激波串位置的测量及控制  

Dual-mode Scramjet Isolator Shock Train Leading Edge Measurement and Control

作　　者：浮强[1] 宋文艳[1] 韩小宝[1] 王艳华[1] 石德永[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空计算技术》2017年第2期20-24,共5页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(51506177)

摘　　要：隔离段是双模态超燃冲压发动机隔离进气道和燃烧室相互干扰、实现亚燃-超燃双模态的重要部件。在发动机实际工作过程中,燃烧室反压引起的进气道不起动在飞行器加速爬升阶段是需要极力避免和预防的。针对双模态超燃冲压发动机整机模型和燃烧室模型进行了数值模拟研究,分析了激波串前沿位置与隔离段压力分布的关系,在此基础上介绍了三种通过隔离段壁面压力实时测量和监控隔离段激波串前沿位置的方法,并完成了验证实验。结果表明,所使用的计算方法有效可行;隔离段壁面压力分布能够很好地反应隔离段的激波串前沿位置,通过监控隔离段壁面压力分布,控制隔离段激波串前沿位置,能够有效避免和预防燃烧室反压过高引起的进气道不起动问题。solator is one of the most important components of a scramjet. It can isolate inlet and combustor influence each other and realize mode transition. In the process of the scramjet working especially the speed and climb state, inlet unstart which is induced by the combustor pressure increase needs to be pro-tected. In this paper, numerical studies has been carried out both on a scramjet and a combustor models to analyze the relationship between the wall pressure in the isolator and shock train leading edge. On this ba-sis, three measurement methods of shock train leading edge were discussed to realize shock train leading edge real time control. As a result, the wall pressure in the isolator was a good indication of shock train leading edge, and it is possible to control the shock train leading edge by control the pressure distribution in the isolator.

关 键 词：超燃冲压发动机 数值模拟 隔离段 激波串 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]