超燃冲压发动机不同燃烧室结构流场数值模拟  

Numerical Simulation of the Flow Field in Scramjet with Different Structure Combustion

作　　者：杨事民[1] 唐豪[1] 梁德旺[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《飞机设计》2008年第2期11-15,24,共6页Aircraft Design

基　　金：国家863基金资助项目(2006AA705306)

摘　　要：对带不同长深比凹腔结构(燃烧室)的二维超燃冲压发动机流场进行数值模拟,采用迎风二阶精度NND格式求解二维欧拉方程,对流场进行冷态数值计算,能够更加清楚地捕捉、分析激波的特点,反映流场的状态和旋流特点;结果证明凹腔可以使流场中形成低速高压回流区,以达到燃料混合燃烧的目的。凹腔长深比对流场特性、总压恢复、燃烧室阻力影响显著。随着长深比的越大,凹腔旋流强度越强,总压损失越大,燃烧室阻力越大。The flow fields in scrarnjet with different length depth ratio （L/D） cavities （combustion） were simulated numerically in cold by using two steps up-wind NND scheme for Euler equations. Shock could be catch and analyzed trait clearly, the trait of flow field and vortex could be imaged clearly; The conclusions are as follows： the low velocity, high pressure and vortex area were obtained with cavity to mix fuel and burn. Cavity length depth ratio strongly influences flow field, total pressure recovery, drag coefficient, the bigger the ratio of length to depth is, the stronger the vortex is, the bigger the total pressure loss is, the bigger the drag is.

关 键 词：激波系 剪切层 凹腔 长高比 总压恢复 阻力系数 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]