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Numerical investigation of oblique detonation waves for a shcramjet combustor.

机译：Shcramjet燃烧器倾斜爆轰波的数值研究。

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摘要

Research in hypersonic airbreathing propulsion strives to provide an efficient, cost-effective alternative to rocket propulsion for space transportation systems. The supersonic combustion ramjet (scramjet) is one of the most common hypersonic airbreathing propulsion concepts, but its massive combustor could have detrimental effects on its efficiency. The shock-induced combustion ramjet (shcramjet) overcomes this drawback by using standing oblique detonation waves (coupled shock-combustion fronts) as a means of nearly instantaneous heat addition. A numerical investigation of standing oblique detonation waves for their use in shcramjet propulsion is the main purpose of this investigation. The laminar, two-dimensional Navier-Stokes equations coupled with non-equilibrium hydrogen/air combustion models based on chemical kinetics are used to represent the physical system. The combustion models are incorporated into an in-house computational fluid dynamics solver based on a shock-capturing scheme by Yee scheme and an approximate factorization algorithm with a dual-time stepping technique to regain time-accuracy. The solver is validated with experimental data found in the literature. A time accurate simulation of the formation of a standing oblique detonation wave (ODW) near the Chapman Jouguet (minimum entropy) condition yields a non-oscillatory, stable structure. The stability of the ODW to inhomogeneities in the oncoming fuel/air mixture is assessed through other time-accurate simulations by artificially introducing small disturbances consisting of pure air just upstream of the ODW structure. The ODW is shown to be resilient to these disturbances: an upstream displacement is observed followed by the return of the ODW to its original position. Steady-state simulations are carried out to determine the effect of laminar boundary layers on ODW structures and properties above and below the Chapman-Jouguet point. A comparison with analogous inviscid simulations shows that the effect is minimal and that the shorter induction distance in laminar flow does not entail a significantly earlier onset of the ODW. A novel shcramjet combustor design that makes use of oblique detonation waves stabilized over wedge-shaped flame-holders and configured such that detonation wave-wall interactions are avoided, is presented and analyzed through steady-state simulations. The design is shown to be a viable one for shcramjet propulsion by means of thrust potential calculations.
机译：高超音速呼吸推进的研究致力于为太空运输系统提供一种高效，经济的火箭推进替代方案。超音速燃烧冲压喷气发动机（scramjet）是最常见的高超音速喷气推进概念之一，但其大型燃烧室可能对其效率产生不利影响。冲击诱发的燃烧冲压发动机（shcramjet）通过使用直立的倾斜爆震波（耦合的冲击燃烧前沿）作为近乎瞬时的热量添加手段，克服了这一缺点。对立式爆轰波在超音速喷气推进中的应用进行数值研究是本研究的主要目的。层流二维二维Navier-Stokes方程与基于化学动力学的非平衡氢/空气燃烧模型结合使用来表示物理系统。将燃烧模型并入内部计算机计算流体动力学求解器中，该求解器基于Yee方案的冲击捕获方案和具有双重时间步进技术的近似因式分解算法以重新获得时间精度。通过文献中的实验数据验证了求解器。在Chapman Jouguet（最小熵）条件附近形成直立斜爆震波（ODW）的时间精确模拟产生了非振荡的稳定结构。 ODW对即将到来的燃料/空气混合物中的不均匀性的稳定性是通过其他时间精确的模拟来评估的，方法是在ODW结构的上游人工引入由纯净空气组成的小干扰。 ODW被证明可以抵抗这些干扰：观察到上游位移，随后ODW返回其原始位置。进行稳态模拟以确定层状边界层对ODW结构和Chapman-Jouguet点上方和下方的特性的影响。与类似无粘性模拟的比较表明，这种影响很小，并且层流中更短的感应距离不会导致ODW明显提前。通过稳态仿真，提出并分析了新颖的shcramjet燃烧器设计，该设计利用稳定在楔形火焰架上的倾斜爆轰波进行配置，从而避免了爆轰波与壁的相互作用。通过推力电势计算，该设计表明是一种适用于短波喷气推进的可行设计。

著录项

  • 作者

    Fusina, Giovanni.;

  • 作者单位

    University of Toronto (Canada).;

  • 授予单位 University of Toronto (Canada).;
  • 学科 Engineering Aerospace.
  • 学位 Ph.D.
  • 年度 2003
  • 页码 142 p.
  • 总页数 142
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空、航天技术的研究与探索;
  • 关键词

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