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首页> 外文期刊>International journal of aerospace engineering >Inlet Pressure Effects on Subatmospheric Flame Stabilization with an Optimum Size of a Cavity-Based Combustor
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Inlet Pressure Effects on Subatmospheric Flame Stabilization with an Optimum Size of a Cavity-Based Combustor

机译：具有基于空腔的燃烧器的最佳尺寸的腔体火焰稳定的入口压力效应

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摘要

Experimental studies are conducted to find an optimum size of the cavity flameholder, which is a new combustion concept of a turbine-based combined-cycle (TBCC) engine with an excellent flame stabilization. Besides, the effect of inlet pressure on the subatmospheric performance is investigated. The experimental results indicate that the increase of the cavity length improves the flame stability with an enlarged fuel/air mixture residence time, which suggests that the big length-height ratio in a proper range of the cavity with a stable dual-vortex should be chosen when designing the cavity-based combustor. In addition, the decrease in lean ignition and the lean blowout equivalence ratios can be attributed by either increase in the inlet pressure and temperature or decrease in the Mach number. The increase in inlet pressure will lead to a linear decrease in the lean blowout equivalence ratio with a slope of 0.66 per 0.1 MPa, whereas the lean ignition equivalence ratio has a rapid drop with the increase of pressure from 0.06 MPa to 0.08 MPa and reduces slowly with the growth of pressure in the range of 0.08 MPa to 0.1 MPa. The detailed analysis of the flow field indicates that the characteristic time-scale theory can ideally explain and predict the change of flame stability in the trapped vortex cavity.
机译：进行实验研究以找到腔体持有者的最佳尺​​寸，这是一种新的涡轮机的组合循环（TBCC）发动机的新燃烧概念，具有出色的火焰稳定。此外，研究了入口压力对子摩擦层性能的影响。实验结果表明，腔长的增加提高了具有扩大燃料/空气混合物停留时间的火焰稳定性，这表明应选择具有稳定双涡流的适当范围的腔体中的大长度高比率在设计基于腔的燃烧器时。另外，贫射点的降低和贫吹水等效比率可以归因于入口压力和温度或马赫数的减少。入口压力的增加将导致贫吹水等效率的线性降低，其斜率为0.1MPa，而贫射点等效率随着0.06MPa至0.08MPa的增加而迅速下降，缓慢减少随着0.08MPa至0.1MPa的压力的增长。流场的详细分析表明，特征时间级理论可以理想地解释并预测被捕获的涡流中的火焰稳定性的变化。

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  • 来源
    《International journal of aerospace engineering》 |2020年第2期|4126753.1-4126753.8|共8页
  • 作者

    Huang Yakun; He Xiaomin; Zhu Zhixin; Zhu Huanyu;

  • 作者单位

    Nanjing Univ Aeronaut & Astronaut Coll Energy & Power Engn Jiangsu Prov Key Lab Aerosp Power Syst Nanjing 210016 Peoples R China;

    Nanjing Univ Aeronaut & Astronaut Coll Energy & Power Engn Jiangsu Prov Key Lab Aerosp Power Syst Nanjing 210016 Peoples R China|Coinnovat Ctr Adv Aeroengine Beijing 100191 Peoples R China;

    Zhejiang Key Lab Hlth Intelligence Kitchen Syst I Ningbo Peoples R China;

    Nanjing Univ Aeronaut & Astronaut Coll Energy & Power Engn Jiangsu Prov Key Lab Aerosp Power Syst Nanjing 210016 Peoples R China;

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