面向超音速燃烧室方案设计的一维流场分析模型  

A One-Dimensional Numerical Analysis of Supersonic Combustor Performance

作　　者：余勇[1] 丁猛[1] 刘卫东[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《弹箭与制导学报》2004年第3期53-57,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家863高技术重点资助项目(2002AA723060)

摘　　要：由气体动力学基本定律,推导出燃烧室性能分析的一种一元流计算方法。该方法考虑了面积变化、质量添加、两相流、多组分效应、化学反应、壁面摩擦、壁面散热等因素的影响。与试验数据的对比分析表明,该方法能够准确描述超音速燃烧室两相参数分布,从而为燃烧室方案设计阶段的快速性能评估和设计优化提供一种有效的手段。Based on basic aerodynamic laws, a one-dimensional model of supersonic combustor performance analysis was obtained. The method can handle internal flow with variable section area, mass addition, two phase flow, multiple species effect, heat release, wall shear and heat transfer to combustor wall. Comparison with experimental data improved that the theoretical analysis gives a good description of the average parameters of the continuous phase and the discrete phase in the supersonic combustor. This provides a rapid methodology for performance prediction and design optimization of supersonic combustor.

关 键 词：超音速燃烧室 两相流 多组分效应 数值模拟 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术]