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首页> 外文期刊>Acta astronautica >Investigation of combustion characteristics in a scramjet combustor using a modified flamelet model
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Investigation of combustion characteristics in a scramjet combustor using a modified flamelet model

机译：使用改进的小火焰模型研究超燃冲压燃烧器的燃烧特性

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摘要

In this study, the characteristics of supersonic combustion inside an ethylene-fueled scramjet combustor equipped with multi-cavities were investigated with different injection schemes. Experimental results showed that the flames concentrated in the cavity and separated boundary layer downstream of the cavity, and they occupied the flow channel further enhancing the bulk flow compression. The flame structure in distributed injection scheme differed from that in centralized injection scheme. In numerical simulations, a modified flamelet model was introduced to consider that the pressure distribution is far from homogenous inside the scramjet combustor. Compared with original flamelet model, numerical predictions based on the modified model showed better agreement with the experimental results, validating the reliability of the calculations. Based on the modified model, the simulations with different injection schemes were analysed. The predicted flame agreed reasonably with the experimental observations in structure. The CO masses were concentrated in cavity and subsonic region adjacent to the cavity shear layer leading to intense heat release. Compared with centralized scheme, the higher jet mixing efficiency in distributed scheme induced an intense combustion in posterior upper cavity and downstream of the cavity. From streamline and isolation surfaces, the combustion at trail of lower cavity was depressed since the bulk flow downstream of the cavity is pushed down.
机译：在这项研究中，以不同的喷射方案研究了配备多腔的乙烯燃料超燃燃烧器内部的超音速燃烧特性。实验结果表明，火焰集中在空腔中，并在空腔下游分隔边界层，并占据流道，进一步增强了整体流压缩。分布式喷射方案的火焰结构与集中喷射方案的火焰结构不同。在数值模拟中，引入了改进的小火焰模型，以考虑到超燃冲压燃烧器内部的压力分布远非均匀。与原始火焰模型相比，基于改进模型的数值预测与实验结果吻合较好，验证了计算的可靠性。基于改进的模型，分析了不同注入方案的模拟。预测的火焰与结构上的实验观察结果基本吻合。 CO物质集中在空腔和剪切腔附近的亚音速区域，导致强烈的热量释放。与集中式方案相比，分布式方案中较高的射流混合效率在后上腔和腔的下游引起强烈燃烧。在流线和隔离表面，下腔尾部的燃烧被抑制了，因为下腔下游的大流量被向下推动。

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  • 来源
    《Acta astronautica》 |2018年第7期|32-40|共9页
  • 作者

    Zhao Guoyan; Sun Mingbo; Wang Hongbo; Ouyang Hao;

  • 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;

  • 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

    Combustion characteristics; Scramjet combustor; Flamelet model; Pressure variation;

    机译：燃烧特性;超燃燃烧室;火焰模型;压力变化;

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