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Numerical investigation of flame appearance and heat flux and in a deep-throttling variable thrust rocket engine

机译：节流型可变推力火箭发动机火焰外观与热通量的数值研究

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摘要

Much attention has been drawn to liquid-propellant rocket engine with thrust that can be varied on demand in recent years. A GO(2)/kerosene deep-throttling variable thrust rocket engine using the newly proposed gas-liquid pintle injector is presented. Three-dimensional numerical simulations are conducted to investigate the flame appearance and heat flux distribution of the engine. The SST k-omega model is used for modeling turbulence and single-step finite-rate kinetics are used for modeling combustion. A grid sensitivity study is performed to examine the validity of the simulation results. The effects of total mass flow-rate, kerosene droplet injection velocity and kerosene droplet size distribution on flame appearance and heat flux distribution of the combustor are studied in detail. Three entirely different flame appearances are observed and it correspondingly causes different heat flux distributions. Details of the flow field structure and mass fraction contour inside the combustor are discussed to explore the cause of heat flux distribution. The work will provide a reference for the design of thermal protection system of the variable-thrust rocket engine operating with a wide range of space. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：近年来，液体推力火箭发动机的推力引起了人们的极大关注，推力可以根据需求而变化。提出了使用新提出的气液枢轴喷射器的GO（2）/煤油深节流可变推力火箭发动机。进行了三维数值模拟，以研究发动机的火焰外观和热通量分布。 SSTk-ω模型用于湍流建模，单步有限速率动力学用于燃烧建模。进行网格敏感性研究以检查仿真结果的有效性。详细研究了总质量流量，煤油滴喷射速度和煤油滴大小分布对燃烧器火焰外观和热通量分布的影响。观察到三个完全不同的火焰外观，并相应地导致不同的热通量分布。讨论了燃烧器内部流场结构和质量分数轮廓的详细信息，以探讨热通量分布的原因。这项工作将为在大空间范围内工作的可变推力火箭发动机的热保护系统设计提供参考。 （C）2019 Elsevier Masson SAS。版权所有。

著录项

  • 来源
    《Aerospace science and technology》 |2019年第5期|457-467|共11页
  • 作者

    Jin Yushu; Xu Xu; Yang Qingchun; Zhu Shaohua;

  • 作者单位

    Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China|CARDC, Hyperson Aerodynam Inst, Mianyang 621000, Peoples R China;

    Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China;

    Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China;

    Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China;

  • 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

    Variable thrust; Heat flux; Flame appearances; Rocket engine; Pintle injector;

    机译：可变推力;热通量;火焰外观;火箭发动机;针式喷油器;

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