旋转固体火箭发动机燃烧室内流场分析解  

Analytical solution of combustion chamber flow field for rotating solid rocket motor

作　　者：刘平安[1] 王革[1] 郜冶 

机构地区：[1]哈尔滨工程大学航天工程系,哈尔滨150001

出　　处：《固体火箭技术》2012年第5期597-601,607,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(10972063);中央高校基本科研基金(HEUCF100203)

摘　　要：对带壁面质量注入的旋转通道(具有柱形装药旋转固体火箭发动机通道)内流场进行了研究。通过解析方法求解简化后的欧拉方程,获得了无粘情况下的旋转通道解析解。在此基础上,运用摄动法中的渐进展开匹配法求解引入粘性修正的切向动量方程,并获得解析解,表明切向速度分布解具有组合涡特征。分析了涡核半径与注入雷诺数及旋转转数的关系,得到了可压缩修正条件下的组合涡规律。The flow field of rotating channel which is a cylindrical combustion of rotating solid rocket motor with mass injection from wall surface was investigated.Simplified Euler Equation was solved using analytic methods.Analytical solution of the rotating channel was obtained without considering viscosity.On the basis of this,the tangential momentum equation considering viscosity modification was solved using matched asymptotic expansions of perturbation method,and the analytical solution was obtained.The result shows that tangential velocity distribution has the characteristics of combination vortex.The relationship among vortex core radius and injection Reynolds number and rotation revolution was analyzed.The regularity of the combination vortex was obtained under the condition of compressible modification.

关 键 词：旋转固体火箭发动机 内流场 分析解 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]