超声速反应流火焰面/进度变量模型

范周琴; 孙明波; 刘卫东

超声速反应流火焰面/进度变量模型

国防科学技术大学航天与材料工程学院,长沙 410073

基金项目: 国家自然科学基金(50906098); 高等学校博士点新教师专项科研基金(20094307120005)

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- 文章访问数: 2153
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- 被引次数: 0
出版历程
- 收稿日期: 2010-07-21
- 修回日期: 2010-10-13
- 刊出日期: 2011-08-28

Flamelet/progress variable model for supersonic reacting flows

College of Aerospace and Materials Engineering, National University of Defense Technology,Changsha 410073,China

摘要

摘要: 基于Pierce低马赫数条件下的火焰面/进度变量模型,考虑可压缩性和激波的影响,发展了用于超声速湍流反应流的火焰面/进度变量模型.该模型通过求解混合分数和进度变量两个标量方程来描述化学反应,且采用火焰面方程解的完整的三个分支:稳态燃烧分支、具有局部熄火状态的非稳态分支和完全熄火分支.利用该模型对德国宇航中心(DLR)的超燃冲压发动机进行模拟,与稳态火焰面模型得到的附着火焰不同,计算结果捕捉到了熄火和火焰抬举现象;且数值阴影和平均温度分布与实验结果吻合较好.
- 超声速湍流燃烧 /
- 稳态火焰面模型 /
- 火焰面/进度变量模型 /
- 熄火 /
- 抬举火焰
Abstract: The flamelet/progress variable model for supersonic turbulent reacting flows was developed based on Pierce's model for low Mach number flows,in consideration of the compressibility effects and shock waves.The present model solved the mixture fraction and progress variable transport equations,and employed three solution branches of flamelet equation:the steady burning branch,the unstable branch of partially extinguished states and the complete extinction state.The performance of the flame/progress variable model was compared to the steady flamelet model for predicting the product and temperature field of a hydrogen-air supersonic combustion ramjet engine in DLR (Deutsches Zentrum für Luft- und Raumfahrt) for which experimental data are available.With capturing of extinction and lifted flame,the present model is good agreement with the experimental data,and outperforms the steady flamelet model which predicts an attached flame.
- supersonic turbulent combustion /
- steady flamelet model /
- flamelet/progress variable model /
- extinction /
- lifted flame

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参考文献(15)

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