圆管隔离段激波串特性的自适应湍流模拟研究  

Numerical investigation on shock train characteristics in cylindrical isolator via SATES method

作　　者：谢鹏飞 刘一凡 韩省思 XIE Pengfei;LIU Yifan;HAN Xingsi(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空工程进展》2024年第6期244-254,共11页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(52376114,92041001);国家科技重大专项(J2019-Ⅲ-0015-0059)。

摘　　要：在超燃冲压发动机中,隔离段起着“承上启下”的重要作用,在燃烧室高反压作用下的隔离段内存在着激波/边界层相互作用、流动分离以及激波串等复杂流动现象。针对等直圆截面构型隔离段进行自适应湍流模拟研究,重点分析隔离段与燃烧室耦合时可能遇到的问题,如隔离段出口恒定或脉动反压以及壁面温度对隔离段内激波串特性的影响。结果表明:隔离段出口反压值增大、频率降低以及壁面温度升高均会使激波串向隔离段入口移动,造成潜在的不起动风险。在实际工程中,应特别警惕燃烧室燃烧过程中带来的高反压、低频振荡燃烧以及壁面热传导效应,防止激波串被推出隔离段,导致隔离段乃至整个发动机停止工作。In scramjet,the isolator plays a crucial role as a transitional component between the combustor and the inlet.Within the isolator,complex flow phenomena such as shock wave/boundary layer interactions,flow separation,and shock trains are observed under the influence of high back-pressure from the combustor.In this study,the self-adaptive turbulence eddy simulation(SATES)is used to numerically study the shock train characteristics in a cylindrical isolator.The primary focus is to analyze the potential challenges faced when the isolator is coupled with the combustor,including the effects of constant or pulsating back-pressure at the isolator exit and wall temperature on the shock train characteristics within the isolator.The results indicate that an increase in the exit back-pressure of the isolator,a decrease in the frequency of pulsating back-pressure,and an elevation in wall temperature can all cause the shock train to move towards the inlet,leading to potential unstart risks.Therefore,in practical engineering applications,particular attention should be paid to the high back-pressure and low-frequency oscillations induced during the combustor combustion process,as well as the wall heat conduction effects,to prevent the shock train from being expelled from the isolator,which could result in the unstart of not only the isolator but also the entire engine.

关 键 词：隔离段 自适应湍流模拟 反压 激波串 壁温 

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]