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Inlet Geometry and Equivalence Ratio Effects on Combustion in a Ducted Rocket

机译:进气道几何形状和当量比对管道火箭燃烧的影响

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摘要

The scope of this study is to predict the combustion performance of a ducted rocket combustor. Connected-pipe combustion experiments and numerical analysis of the internal reacting flow in a ducted rocket combustor were conducted at various equivalence ratios with an emphasis on the air inlet geometry effect The considered equivalence ratio in experimental and numerical investigations varied between 0.35 and 1.57 in order to reflect the variable-flow conditions of the ducted rockets. Three kinds of combustors have been used in order to evaluate the air inlet geometry effect: a two-inlet combustor with an inlet angle of 90 deg, a two-inlet combustor with an inlet angle of 180 deg, and a four-inlet combustor with an inlet angle of 90 deg. The behavior of the carbon particles within the fuel-rich gas stream was investigated and found to have a major effect on the temperature rising. The four-inlet combustor exhibited the best combustion efficiency, and the two-inlet combustors did not show large differences in terms of performance. The numerical model showed sufficient predictability within 6% accuracy in comparison with experimental temperature for all test conditions.
机译:本研究的范围是预测管道火箭燃烧器的燃烧性能。管式火箭燃烧器内的连接管燃烧实验和内部反应流的数值分析在各种当量比下进行,着重于进气口几何效应。在实验和数值研究中考虑的当量比在0.35和1.57之间变化,以便反映管道火箭的可变流量条件。为了评估进气口几何形状的影响,已使用了三种燃烧器:进气角度为90度的两入口燃烧器,进气角度为180度的两入口燃烧器以及进气角度为4的燃烧器。入口角为90度研究了富含燃料的气流中碳颗粒的行为,发现其对温度升高有重大影响。四入口燃烧器表现出最佳的燃烧效率,而两入口燃烧器在性能方面没有显示出很大差异。在所有测试条件下,与实验温度相比,该数值模型均显示出6%的准确度,具有足够的可预测性。

著录项

  • 来源
    《Journal of propulsion and power》 |2015年第2期|619-631|共13页
  • 作者

    Soojong Kim; Benveniste Natan;

  • 作者单位

    Technion-Israel Institute of Technology, 32000 Haifa, Israel;

    Technion-Israel Institute of Technology, 32000 Haifa, Israel;

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  • 正文语种 eng
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