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弹箭与制导学报 >

2016 , Vol. 36 >Issue 2: 87 - 90

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2016.02.021

火箭技术

高温燃气射流对固冲发动机二次燃烧效率影响研究

  • 曹军伟 ,
  • 何国强 ,
  • 单睿子 ,
  • 莫展
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  • 1 西北工业大学固体火箭发动机燃烧、热结构与内流场重点实验室, 西安 710072
    2 中国空空导弹研究院, 河南 洛阳 471099

曹军伟(1973-), 男, 河南商水人, 博士研究生, 研究方向:固体火箭冲压发动机研究。

收稿日期: 2015-04-27

  网络出版日期: 2025-05-30

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Research on Effect of High Temperature Gas Injection on Secondary Combustion Efficiency of Solid Rocket Ramjet

  • CAO Junwei ,
  • HE Guoqiang ,
  • SHAN Ruizi ,
  • MO Zhan
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  • 1 National Key Laboratory of Combustion Flow and Thermal-structure, Northwestern PolytechnicalUniversity, Xi'an 710072, China
    2 China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2015-04-27

  Online published: 2025-05-30

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摘要

为进一步提高固冲发动机的二次燃烧效率,文中提出了在固冲发动机补燃室头部引入高温燃气射流增强掺混燃烧的技术思路,并开展了仿真和验证试验工作。仿真分析表明:当在补燃室头部引入高温燃气射流时,能够提高补燃室头部流场的温度,使得燃料更易于燃烧,从而提高了固冲发动机的二次燃烧效率;试验结果也验证了在固冲发动机头部引入高温燃气射流,能够使固冲发动机的二次燃烧效率由81.3%提高到88.7%。

关键词： 燃气射流; 固冲发动机; 燃烧效率; 富燃料推进剂

本文引用格式

曹军伟 , 何国强 , 单睿子 , 莫展 . 高温燃气射流对固冲发动机二次燃烧效率影响研究[J]. 弹箭与制导学报, 2016 , 36(2) : 87 -90 . DOI: 10.15892/j.cnki.djzdxb.2016.02.021

Abstract

To improve secondary combustion efficiency of solid rocket ramjet, the method of introducing high temperature gas injection into front end of combustor to enhance mixture and combustion was proposed in this paper. Also, numerical simulation and test were conducted to study feasibility of the method. The simulation results show that the introduction of gas injection could increase temperature in front part of combustor, thereby facilitating combustion of propellant and improving combustion efficiency of solid rocket ramjet. Besides, the method was validated by test data that indicated rise of secondary combustion efficiency from 81.3% to 88.7%.

Key words： gas injection; solid rocket ramjet; combustion efficiency; fuel rich propellant

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