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Modelling of liquid oxygen nozzle flows under subcritical and supercritical pressure conditions

机译：亚临界和超临界压力条件下液氧喷嘴流动的建模

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摘要

The two-phase flow of liquid oxygen in a converging-diverging nozzle has been numerically predicted at conditions resembling those that prevail in the lower-stage boosters of rocket engines realising lift off, as well as in the respective upper stages operating in sub-atmospheric pressures. A comparative evaluation of the predictive capability of a pressure and a density-based solver with various approaches regarding the imposed phase-change rate and thermodynamics closure have been performed. The departure from thermodynamic equilibrium during phase-change has been taken into account via implementation of a bubble-dynamics model employing the Hertz-Knudsen equation in the pressure based solver, whereas thermodynamic equilibrium is adopted in the density-based solver. Tabulated data for the variation of the fluid thermodynamic properties have been derived by the Helmholtz Equation of State (EoS) in a modelling approach universal for both the sub- and supercritical states. This approach has been comparatively assessed in the sub-critical regime against the bubble-dynamics-based model including different EoS for the liquid/vapour phases and against a different tabulated approach based on the NIST dataset for supercritical injection. In terms of flow physics, more severe flow expansion in the diverging part of the nozzle has been detected for subcritical pressures, leading to supersonic flow velocities and significant cooling of the fluid mixture. Complementary Detached Eddy Simulations (DES) have provided detailed insight on the complex expansion phenomena and flow instabilities manifesting on the divergent part of the nozzle for subcritical-injection conditions. The comparison of the numerical predictions against available experimental data and analytical solutions demonstrates the suitability of the employed methodologies in describing the evolution of the cryogenic oxygen flow expansion and phase-change.
机译：在具有在实现升降机的火箭发动机的下级助剂中占上阶段的条件的条件下，已经在数值上预测了液态氧气的两相流动，以及在亚大气中运行的各个上阶段压力。已经进行了对压力的预测能力和基于密度的求解器的比较评估，其具有关于施加的相变率和热力学闭合的各种方法。通过在基于压力的求解器中采用Hertz-Chaudsen方程的气泡动力学模型的实现，已经考虑了在相变期间的热力学平衡的偏离，而基于密度为基于密度的求解器，采用热力学平衡。用于流体热动力学特性的变化的列表数据由状态（EOS）的亥姆霍兹方程在模型方法中推导出普通和超临界状态。这种方法在亚临界制度中对基于气泡动力学的模型进行了相对评估的，包括用于液体/蒸气阶段的不同EOS，并根据基于NIST数据集进行超临界注射的不同表格方法。在流动物理学方面，针对亚临界压力检测到喷嘴的发散部分中的更严重的流动膨胀，导致超声波的流速和流体混合物的显着冷却。互补独立的涡流模拟（DES）提供了对复杂的膨胀现象和流动不稳定性的详细洞察，该流动不置于喷嘴的发散部分以进行亚临界条件。用于可用实验数据和分析解决方案的数值预测的比较显示了所采用的方法的适用性在描述低温氧流量膨胀和相变的演变。

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  • 来源
    《International Journal of Heat and Mass Transfer》 |2021年第10期|121559.1-121559.21|共21页
  • 作者

    T. Lyras; I.K. Karathanassis; N. Kyriazis; P. Koukouvinis; M. Gavaises;

  • 作者单位

    School of Mathematics Computer Science and Engineering City University of London Northampton Square EC1V 0HB London United Kingdom;

    School of Mathematics Computer Science and Engineering City University of London Northampton Square EC1V 0HB London United Kingdom;

    School of Mathematics Computer Science and Engineering City University of London Northampton Square EC1V 0HB London United Kingdom;

    School of Mathematics Computer Science and Engineering City University of London Northampton Square EC1V 0HB London United Kingdom;

    School of Mathematics Computer Science and Engineering City University of London Northampton Square EC1V 0HB London United Kingdom;

  • 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

    Cryogenic LOx; Rocket engine; Real-fluid thermodynamics; Flash boiling; Compressible flow;

    机译：低温lox;火箭发动机;真正流体热力学;闪烁;压缩流量;

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