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Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator

机译：三维超燃喷射隔离器中冲击波跃迁的数值研究

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摘要

The scramjet isolator, which is used to prevent the hypersonic inlet from disturbances that arise from the pressure rise in the scramjet combustor due to the intense turbulent combustion, is one of the most critical components in hypersonic airbreathing propulsion systems. Any engineering error that is possible in the design and manufacturing procedure of the experimental model, and the intense heat release in the scramjet combustor, may cause the performance of the isolator to decrease, leading to its lack of capability in supporting the back pressure. The coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations and the two-equation standard k-ε turbulent model have been employed to numerically simulate the flow fields in a three-dimensional scramjet isolator. The effects of the divergent angle and the back pressure on the shock wave transition and the location of the leading edge of the shock wave train have been estimated and discussed. The obtained results show that the present numerical results are in very good agreement with the available experimental shadow-pictures, and the numerical method is more suitable for capturing the shock wave train and predicting the location of the leading edge of the shock wave train in the scramjet isolator than the present two-dimensional numerical methods. This is due to the small width-to-height ratio of the isolator and the intense three-dimensional flow structures. On increasing the divergent angle of the scramjet isolator, the static pressure along the central symmetrical line of the isolator decreases sharply. This is due to the strong expansion wave generated at the entrance of the isolator, and when the divergent angle of the isolator is sufficiently large, namely 1.5°, a zone of negative pressure is formed just ahead of the leading edge of the shock wave train. At the same time, the shock wave train varies from being oblique to being normal, and then back to oblique. With an increase in the prescribed back pressure at the exit of the scramjet isolator, the leading edge of the shock wave train moves forward towards the entrance of the isolator, and when the back pressure is sufficiently large, unstart conditions in the hypersonic inlet can take place if the shock train reaches the inlet.
机译：超音速喷气隔离器是防止高超音速进气口因剧烈湍流燃烧而因超音速燃烧室压力升高而引起的扰动的隔离器，它是高超音速呼吸推进系统中最关键的组件之一。实验模型的设计和制造过程中可能出现的任何工程错误，以及超燃冲压燃烧器中大量的热量释放，都可能导致隔离器的性能下降，从而导致其缺乏支撑背压的能力。耦合隐式雷诺平均Navier-Stokes（RANS）方程和两方程式标准k-ε湍流模型已被用于数值模拟三维超燃喷射隔离器中的流场。估计并讨论了发散角和背压对冲击波过渡和冲击波列前缘位置的影响。所得结果表明，目前的数值结果与已有的实验阴影图非常吻合，数值方法更适合于捕获激波列，并预测激波列前沿的位置。超燃冲压隔离器比目前的二维数值方法要好。这是由于隔离器的宽高比小和强烈的三维流动结构所致。在增加超燃冲压隔离器的发散角时，沿着隔离器中心对称线的静压力会急剧下降。这是由于在隔离器的入口处产生了强烈的膨胀波，并且当隔离器的发散角足够大时（即1.5°），正好在冲击波列的前端形成了一个负压区域。 。同时，冲击波从倾斜到正常再到倾斜。随着超燃冲压隔离器出口处规定的背压增加，冲击波列的前缘会朝隔离器的入口向前移动，并且当背压足够大时，高超声速进口中的不启动条件可能会发生减震器到达进口处。

著录项

  • 来源
    《Acta astronautica》 |2011年第12期|p.1669-1675|共7页
  • 作者

    Wei Huang; Zhen-guo Wang; Mohamed Pourkashanian; Lin Ma; Derek B. Ingham; Shi-bin Luo; Jing Lei; Jun Liu;

  • 作者单位

    Center of Hypersonic Propulsion, College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, Hunan 410073,People's Republic of China,Centre for CFD, School of Process, Environmental and Materials Engineering, University of Leeds, LS2 9jT, United Kingdom;

    Center of Hypersonic Propulsion, College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, Hunan 410073,People's Republic of China;

    Centre for CFD, School of Process, Environmental and Materials Engineering, University of Leeds, LS2 9jT, United Kingdom;

    Centre for CFD, School of Process, Environmental and Materials Engineering, University of Leeds, LS2 9jT, United Kingdom;

    Centre for CFD, School of Process, Environmental and Materials Engineering, University of Leeds, LS2 9jT, United Kingdom;

    Center of Hypersonic Propulsion, College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, Hunan 410073,People's Republic of China;

    Center of Hypersonic Propulsion, College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, Hunan 410073,People's Republic of China;

    Center of Hypersonic Propulsion, College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, Hunan 410073,People's Republic of China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    aerospace propulsion system; scramjet isolator; shock wave transition; hypersonic vehicle; shock wave train;

    机译：航空航天推进系统;超燃喷射隔离器;冲击波过渡;人体飞行器;冲击波列;

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