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弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 184 - 192

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.008

运载火箭发射过程导流槽喷水降温效果研究

  • 沈博晗 ,
  • 姜毅 ,
  • 王昕宇 ,
  • 宋士泽
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  • 北京理工大学宇航学院, 北京 100081
姜毅(1965—), 男, 教授, 博士。E-mail:

沈博晗(2001—), 男, 硕士研究生。E-mail:

收稿日期: 2025-02-27

  网络出版日期: 2025-05-15

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Research on the Cooling Effect of Water Injection in the Flame Deflector During the Launch Process of Carrier Rockets

  • SHEN Bohan ,
  • JIANG Yi ,
  • WANG Xinyu ,
  • SONG Shize
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  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2025-02-27

  Online published: 2025-05-15

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摘要

在运载火箭的热发射过程中, 火箭发动机产生的高温高压燃气会对导流槽造成明显的高温烧蚀作用。为了实现运载火箭发射过程中导流槽的热防护, 针对带有两个助推级的运载火箭的发射过程, 基于耦合Mixture多相流模型和Lee模型的计算流体力学方法, 分析以不同的喷水速度向单面导流槽表面喷水过程中流场的变化。结果表明, 向导流槽喷水可有效抑制燃气反溅现象, 大幅缩小导流槽表面高温区的分布面积, 对导流槽起到良好的保护作用。在喷水速度较小时, 导流槽表面最大温度发生振荡;随着喷水速度的增加, 导流槽表面最大温度振荡程度逐渐减弱至消失, 导流槽表面最大温度随之降低, 最大汽化速率随之上升。向燃气射流喷水会改变流场形态, 喷水位置不同会导致燃气射流轴线上物理参数的分布情况不同, 水射流直接冲击燃气射流轴线的降温效果更好。该结论可为运载火箭发射过程提供一定参考。

关键词： 燃气射流; 气液两相流; 导流槽; 喷水降温

本文引用格式

沈博晗 , 姜毅 , 王昕宇 , 宋士泽 . 运载火箭发射过程导流槽喷水降温效果研究[J]. 弹箭与制导学报, 2025 , 45(2) : 184 -192 . DOI: 10.15892/j.cnki.djzdxb.2025.02.008

Abstract

During the hot launch process of a carrier rocket, the high-temperature and high-pressure gas generated by the rocket engine will cause significant high-temperature erosion on flame division trough. In order to achieve the thermal protection of the division trough during launch of a rocket, the variation of the flow field during water injection onto the surface of a single-sided division trough was analyzed based on the computational fluid dynamics (CFD) method with coupled mixture multiphase flow model and Lee model for different water injection velocities for a rocket with two booster stages. The results show that spraying water into the division trough effectively suppresses the phenomenon of gas splashing, significantly reduces the distribution area of the high-temperature zone on the surface of the division trough, and provides good protection for the division trough. When the water spraying speed is low, it will cause oscillation of the maximum temperature on the surface of the division trough. As the water spraying speed increases, the degree of oscillation of the maximum temperature on the surface of the division trough gradually weakens until it disappears. As the water spraying speed increases, the maximum temperature on the surface of the division trough decreases, and the maximum vaporization rate also increases. Spraying water onto the gas jet will change the shape of the flow field. Different spraying positions will result in different distributions of physical parameters along the axis of the gas jet. Directly impacting the gas jet with the water jet will have a better cooling effect. This conclusion can provide some reference for the launch process of carrier rockets.

Key words： gas jet; gas-liquid two-phase flow; flame deflector; cooling of water injection

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