基于嵌套网格的脉冲发动机喷管内流场数值模拟  

Numerical simulation research of nozzle inner flow field for pulse motor based on dynamic chimera grid

作　　者：李映坤 韩珺礼[1,2] 陈雄[1] 鞠玉涛[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]北京机电研究所,北京100012

出　　处：《固体火箭技术》2014年第2期178-183,共6页Journal of Solid Rocket Technology

基　　金：中央高校基本科研业务费专项资金资助(NUST2011XQTR13)

摘　　要：为了研究双脉冲固体火箭发动机喷管中运动的隔塞对喷管内流场的影响,采用基于格心的有限体积法求解非定常雷诺平均Navier-Stokes方程,空间离散采用AUSM-PW矢通量分裂格式,利用双时间步LU-SGS方法进行时间推进以提高计算效率,通过动态嵌套网格技术模拟隔塞在喷管内的运动,获得了隔塞运动过程中喷管内流场的演化过程。仿真结果表明,发动机正常工作时,隔塞通过喷管的过程中,发动机的瞬时推力剧烈波动,隔塞位于喷管喉部时,发动机瞬时推力降至最小,相比于初始时刻减小了27.7%;隔塞完全通过喷管喉部后,并位于喷管扩张段上游时,发动机瞬时推力达到最大值,比初始时刻增大了8.9%,这是发动机推力-时间曲线波动的主要原因之一。In order to study the influence of the nozzle flow field in dual pulse solid rocket motor with moving plugs, the un- steady Reynolds-average Navier-Stokes equations were solved with dual-time step LU-SGS iterative algorithm by cell center finite volume method, AUSM-PW scheme was implemented for spatial discretization.The process of the plug moving in the nozzle was sim- ulated by dynamic chimera grid approach.Simulation results show that the instantaneous thrust varies greatly during the plug passing through the nozzle.When the plug is located in the throat of the nozzle ,the maximum instantaneous thrust is declined by nearly 27. 7% compared to the initial time;While the plug is located in the divergent section of the nozzle, the instantaneous thrust is increased by nearly 8.9%. It is one of main causes accounting for of the fluctuation of thrust-time curve.

关 键 词：动态嵌套网格 双脉冲发动机 喷管内流场 数值计算 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]