Numerical Investigation of an Active Jet Control Method for Hypersonic Inlet Restart  

基于主动射流控制的高超声速进气道再起动性能研究

作　　者：JIN Yichao YAO Wei 靳一超;姚卫(北京应用物理与计算数学研究所,北京100094;中国科学院力学研究所高温气体动力学国家重点实验室,北京100190;中国科学院大学工程科学学院,北京100049)

机构地区：[1]Institute of Applied Physics and Computational Mathematics,Beijing 100094,P.R.China [2]Key Laboratory of High-Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,P.R.China [3]School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,P.R.China

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2022年第6期651-662,共12页南京航空航天大学学报（英文版）

基　　金：supported by the National Key Research and Development Program of China (No.2021YFA0719204);the National Natural Science Foundation of China (No.12272387)。

摘　　要：A flow control method based on an active jet is developed to restart hypersonic inlets. The dynamic restarting process is numerically reproduced by unsteady Reynolds averaged Navier-Stokes(RANS) modeling to verify the effectiveness and reveal the influence of jet conditions. The active jet improves the inlet unstart status by drawing the high-pressure separation bubble from the internal compression duct and performing a full expansion to alleviate the adverse pressure gradient. Moreover, the favorable pressure gradient in the inlet caused by jet expansion allows for a successful restart after turning off the jet. The influence of the jet momentum ratio is then analyzed to guide the design of the active jet control method and choose the proper momentum ratios. A low jet momentum does not eliminate the high-pressure separation bubble, whereas an excessive jet momentum causes severe momentum loss due to the induced shock. The general rule in restarting the inlet using an active jet is to allow a full jet expansion downstream of the jet slot while avoiding excessive momentum loss upstream and preventing the thick low-speed layer.基于主动射流技术,本文提出了一种应用于高超声速进气道再起动的控制方法。采用URANS(Unsteady Reynolds averaged Navier-Stokes)方法对再起动的动态过程进行了数值模拟,验证了控制方法的有效性,并揭示了射流条件的影响。主动射流将高压分离泡从内缩段转移至上游并充分膨胀,缓解了内缩段的逆压梯度,从而改善了进气道的不起动状态。关闭射流后,进气道在射流膨胀诱导的顺压环境中成功实现再起动。接着,分析了射流动量比的影响以指导射流控制方法的设计并选择合适的动量比。较低的射流动量不足以消除高压分离泡,而过大的射流动量则会诱导较强的弓形激波并造成严重的动量损失。移除射流后,将在下壁面形成较厚的低速层,使进气道回退为不起动状态。因此,使用主动射流辅助进气道再起动的一般原则为确保射流在出口下游充分膨胀,同时避免在上游造成较大的动量损失,并防止形成较厚的低速层。

关 键 词：hypersonic inlet UNSTART RESTART active jet flow control 

分 类 号：O354[理学—流体力学]