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首页> 外文期刊>Acta astronautica >Experimental investigations of cavity parameters leading to combustion oscillation in a supersonic crossflow
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Experimental investigations of cavity parameters leading to combustion oscillation in a supersonic crossflow

机译：超声波横流中燃烧振荡导致腔参数的实验研究

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摘要

The effects of cavity parameters on combustion oscillation inside an ethylene-fueled scramjet combustor equipped with a cavity flameholder are experimentally investigated for Mach 5.5 flight conditions. Three certain cases, such as i) longer length-to-depth ratio, ii) sharper aft degree of cavity, iii) closer air throttling downstream of the cavity, exhibit quasi-periodic combustion oscillation, which can be separately attributed to i) larger re-circulation volume in the cavity and more mass and heat exchange between cavity shear layer and the core flow, ii) the stronger impinging shock wave in the cavity acting on shear layer, iii) improved fuel/air mixing owing to the interaction between separated boundary layer and combustion. High-speed and schlieren images demonstrate that the cavity and downstream of it act as the most sensitive areas, at the same time, the factors mentioned above can form a thermal throat further triggering flame flashback, which is an indispensable key subprocess of combustion oscillation. The quantitative analysis results obtained from iso-luminosity contour have shown the different distribution trends of flame front and distinct differences of quasi-periodic oscillation frequencies, whereas similar flame propagation speed distributions. In addition, a simplified combustion opening system model has been established to analyze combustion oscillation mechanisms, which theoretically demonstrates that above factors can destroy the balance of heat release and dissipation, causing the system cannot self-stabilize once certain temperature fluctuation thresholds in sensitive areas are exceeded.
机译：实验研究了配备有空腔燃料燃烧器内的乙烯燃料炒壳燃烧器内部燃烧振荡的效果。三个某些情况，例如i）较长的长度深入比，ii）较小的腔体，iii）较近空气的空气下游，展示准周期性燃烧振荡，可以单独归因于i）较大在腔体中的再循环体积和腔剪切层和芯流量的更多质量和热交换，ii）在剪切层的腔中作用在剪切层的腔体中的较强的冲击冲击波，由于分离之间的相互作用而改善了燃料/空气混合边界层和燃烧。高速和Schlieren图像表明，它的腔体和下游充当最敏感的区域，同时，上述因素可以形成热喉部进一步触发火焰闪回，这是燃烧振荡的不可缺少的关键子处理。从ISO-亮度轮廓获得的定量分析结果表明了火焰前正面的不同分布趋势和准周期性振荡频率的不同差异，而类似的火焰传播速度分布。此外，已经建立了一种简化的燃烧开口系统模型来分析燃烧振荡机制，从理论上表现出上面的因素可以破坏热释放和耗散的平衡，导致系统不能自稳定，一旦敏感区域的某些温度波动阈值就能自稳定超出。

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  • 来源
    《Acta astronautica》 |2019年第2期|255-263|共9页
  • 作者

    Zhao Guo-Yan; Sun Ming-Bo; Song Xi-Liang; Li Xi-Peng; Wang Hong-Bo;

  • 作者单位

    Natl Univ Def Technol Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R China;

    Natl Univ Def Technol Sci & Technol Scramjet Lab Changsha 410073 Hunan Peoples R 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

    Supersonic combustion; Cavity flameholder; Cavity parameter; Flame flashback; Thermal throat;

    机译：超音速燃烧;腔扑灯;腔参数;火焰闪回;热喉部;

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