超声速燃烧室性能一维数值模拟  

A one-dimensional numerical analysis of supersonic combustor performance

作　　者：余勇[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：《流体力学实验与测量》2004年第3期36-41,共6页Experiments and Measurements in Fluid Mechanics

基　　金：国家"八六三"基金重点资助项目(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声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了一种有效的手段。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. Comparing with experimental data,it is proved 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：超声速燃烧室 数值模拟 两相流 多组分效应 超燃冲压发动机 

分 类 号：V233.756[航空宇航科学与技术—航空宇航推进理论与工程]