固体燃料冲压发动机燃烧室燃烧特性数值模拟  

Numerical Simulation of Combustion Characteristic in Combustion Chamber of SFRJ

作　　者：李泽勇[1] 郭健[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹道学报》2009年第1期75-78,共4页Journal of Ballistics

基　　金：国家自然科学基金项目(50376072)

摘　　要：采用12组分1、7个化学反应的模型和二阶矩湍流燃烧模型,通过计算药柱表面热传导率,得到了燃面退移速率,对固体燃料冲压发动机燃烧室内部的燃烧流动进行了数值模拟,分析了空气流量、空气总温和入口直径对燃烧室温度分布、C4H6分布和燃面退移速率的影响.分析表明,减小空气入口直径、增加空气流量和总温都会使燃面退移速率增加.The 12-species 17-steps model and the second-moment turbulent combustion model were used, and the heat conductivity of laminar sub-layer on surface of grain was calculated to achieve the fuel regression rate. The numerical simulation of the combustion and flow inside the combustion chamber of Solid Fuel Ramjet （SFRJ） was carried out. The effects of air flux, total temperature of air and inlet diameter on temperature distribution in combustion chamber, C4 H4 distribution and fuel regression rate were analyzed. The result shows that the fuel regression rate increases with the decrease of the air inlet diameter, the increase of the air flux and total temperature of the air.

关 键 词：固体燃料冲压发动机 燃烧室 热传导率 燃面退移速率 二阶矩湍流燃烧模型 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]