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首页> 外文期刊>Journal of Thermophysics and Heat Transfer >Comparison During a Scramjet Regenerative Cooling and Recooling Cycle
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Comparison During a Scramjet Regenerative Cooling and Recooling Cycle

机译：Scramjet蓄冷和再冷循环过程中的比较

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摘要

A coupled heat-transfer and flow model of a scramjet with a recooling cycle is established, and it includes supersonic combustion, combustion heating, and fuel cooling with real scramjet engine geometry and operating parameters. Under the most insufficient heat sink condition, flow and heat transfer characteristics are compared under real operating conditions during the recooling cycle and regenerative cooling. The comparison results indicate that the total heat sink (physical and recooling) in the recooling cycle adequately meets the cooling requirements of a scramjet under the most insufficient heat sink condition, and overtemperature can be well avoided in the recooling cycle. However, the Mach number constraint can be easily activated in the recooling cycle and, therefore, the design of the second cooling passage merits some special attention.
机译：建立了具有再冷却循环的超燃冲压发动机的传热和流动耦合模型，该模型包括超音速燃烧，燃烧加热和具有实际超燃冲压发动机几何形状和运行参数的燃料冷却。在最不充分的散热条件下，将在实际操作条件下的再冷却循环和再生冷却期间的流动和传热特性进行比较。比较结果表明，在最不充分的散热器条件下，再冷却循环中的总散热器（物理冷却和再冷却）足以满足超燃冲压发动机的冷却要求，并且在再冷却循环中可以很好地避免温度过高。但是，马赫数约束可以在再冷却循环中容易地激活，因此，第二冷却通道的设计值得特别注意。

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  • 来源
    《Journal of Thermophysics and Heat Transfer》 |2012年第4期|612-618|共7页
  • 作者

    Jiang Qin; Wen Bao; Silong Zhang; Weixing Zhou;

  • 作者单位

    Harbin Institute of Technology, 150001 Harbin, People's Republic of China;

    Harbin Institute of Technology, 150001 Harbin, People's Republic of China;

    Harbin Institute of Technology, 150001 Harbin, People's Republic of China;

    Harbin Institute of Technology, 150001 Harbin, People's Republic of China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);美国《生物学医学文摘》(MEDLINE);
  • 原文格式 PDF
  • 正文语种 eng
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