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Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

机译:液体火箭发动机咽热通量估计的数值方法

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摘要

The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux.
机译:由于实验信息较少,液体火箭发动机喉部的​​热通量预测的问题仍然是挑战。这种问题一般来说是显而易见的,并且在考虑可重复使用的发动机时变得更加重要。不幸的是,只有很少的间接实验数据可用于咽喉热通量预测的验证。在数值方面,详细解决方案需要大量的分辨率和能够在同一时间燃烧,边界层具有可能有限速率反应的边界层的巨大分辨率和代码,扩展到至少声音速度,并且在一些情况下辐射热通量。因此,在文献中提供的少数实验数据,简化了CFD方法是重要的,其目的是在价格实惠的时间内预测喷嘴中的热量通量。基于RAN方法的不同数值模型获得的结果表明了所做的近似的正确性和质量,表明要包括在建模中的主要现象,用于正确预测咽喉热通量的正确预测。

著录项

  • 来源
    《Aerotecnica missili & spazio》 |2021年第1期|33-38|共6页
  • 作者单位

    Dipartimento di Ingegneria Meccanica ed Aerospaziale “La Sapienza”-Università di Roma;

    Dipartimento di Ingegneria Meccanica ed Aerospaziale “La Sapienza”-Università di Roma;

    Dipartimento di Ingegneria Meccanica ed Aerospaziale “La Sapienza”-Università di Roma;

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  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Liquid rocket engines; Heat transfer; CFD;

    机译:液体火箭发动机;传热;CFD;
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