固冲发动机补燃室凝相碳颗粒燃烧研究.doc

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第 32 卷第 3 期
JOURNAL OF NATIONAL UNIVERSITY OF DEFENSE TECHNOLOGY
Vol. 32 No. 3 2010
文章编号: 1001- 2486( 2010) 03- 0037- 05
固冲发动机补燃室凝相碳颗粒燃烧研究
王德全, 夏智勋, 胡建新

X
( 国防科技大学航天与材料工程学院, 湖南长沙
410073)
摘

要: 应用改进的移动火焰锋面( MFF) 模型, 分析了环境压力、温度等参数对碳颗粒燃烧过程的影响。
在此基础上, 研究了固冲发动机补燃室内碳颗粒的燃烧过程, 得到了固冲补燃室环境中的碳颗粒燃烧特性, 并
通过固冲直连式试验验证了数值模拟结果。结果表明: 补燃室中大部分碳颗粒在进气道出口附近燃烧。
关键词: 固体火箭冲压发动机; 燃烧; 数值模拟; 碳颗粒; 两相流
中图分类号: V438
文献标识码: A
Combustion Study of Condensed Carbon Particle in the Secondary
Combustion Chamber of Solid Rocket Ramjet
WANG De- quan, XIA Zh-ixun,HU Jian- xin
( College Aerospace and M aterial Engineering, National U niv. of Def ense Technology, Changsha 410073, China)
Abstract: The effect of pressure and temperature on carbon bustion was studied by an improved Moving Flame Front
( MFF) model. On the basis of the above discussion, the carbon bustion in solid rocket ramjet was analyzed. As a result,
the carbon bustion mechanism in solid rocket ramjet was achieved. Moreover, numerical results were validated by direc-t
connect test of solid rocket ramjet. The result shows that most of carbon particle in the bustion chamber burned near the
inlet exit.
Key words: solid rocket ramjet; combustion; numerical simulation; carbon particle; two phase flow
目前固体火箭冲压发动机所用的推进剂中, 大多添加铝镁等金属成分, 随着对推进剂能量特性要求
越来越高, 推进剂中金属含量也相应提高, 随着金属含量的不断增加, A