环向进气固体火箭冲压发动机补燃室流场数值模拟  

Numerical Simulation of Flow Field in Afterburning Chamber for Ringed-propellant Solid Rocket Ramjet Engine

作　　者：赵春宇[1] 李斌[1] 鞠玉涛[2] 

机构地区：[1]北京航天试验技术研究所,北京100074 [2]南京理工大学,南京210094

出　　处：《弹箭与制导学报》2008年第2期136-138,142,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中采用标准κ-ε双方程湍流模型数值模拟一种环向进气的固体火箭冲压发动机补燃室的掺混燃烧过程,考虑了补燃室的出口反压、空燃比和燃气喷射角度等设计参数对燃烧流场的影响,结果表明:增大出口反压和空燃比,有利于补燃室内掺混和燃烧的进行;增大燃气喷射角度,补燃室头部温度升高,燃料停留时间增大,对燃烧流场特性影响不大。Numerical simulation of mixing and combustion in afterburning chamber for ringed-propellant solid rocket ramjet engine was done by standard κ-ε two equation turbulent models. The influence of the design parameters, such as afterburning chamber＇s exit-pressure, mass-rate ratio of the air and fuel and the fuel＇s injecting angle on the burning efficiency was considered. The results indicate that both exit-pressure and mass-rate ratio increase is good for mixture and combustion. When increasing the fuel＇s injecting angle, the front temperature and the fuel＇s remain time increase, but it doesn＇t influence much on the combustion flow field.

关 键 词：冲压发动机 补燃室 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]