长时间小过载情况下固体火箭发动机两相流流场数值模拟  

Numerical simulation of two-phase flow field under low acceleration with long operation time conditions for solid rocket motor

作　　者：那旭东 夏智勋[1] 马立坤[1] 颜小婷 NA Xudong;XIA Zhixun;MA Likun;YAN Xiaoting(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《固体火箭技术》2018年第6期694-701,共8页Journal of Solid Rocket Technology

摘　　要：对某飞行失效固体火箭发动机在长时间小过载情况下的三维两相流内流场进行数值模拟。在计算过程中,考虑了发动机实际飞行过程中由于自身旋转所带来的科氏加速度的影响。针对3个典型时刻,采用DPM模型和Sommerfeld数为判定准则的颗粒壁面碰撞模型,模拟固体火箭发动机的两相流流动,分析两相流流场特点,并给出了颗粒沉积分布区域以及沉积区域最大处颗粒冲刷的角度、速度及粒径统计分布。结果表明,在长时间小过载的情况下,发动机内流场原有的轴对称流动形态发生了改变,颗粒相在承载方向浓度增大,且颗粒沉积的最大浓度区域主要分布在发动机后封头的圆弧过渡段。数值仿真结果可为该类发动机后续的热防护设计提供一定的指导依据。Under the conditions of low acceleration with long operation time,numerical simulation of three-dimensional twophase flow field for some solid rocket motors with flight failure has been performed.Coriolis acceleration was considered in the simulation,which caused by self-rotation in the actual flight of the motors.Two-phase flow field in solid rocket motor has been simulated based on DPM model for three typical moments.Particle-wall collision model,which takes Sommerfeld number as the criteria,was adopted.The characteristics of two-phase flow field have been analyzed,and the distributed area of the particles concentration was also given.The particles erosion angle,velocity and particles diameter were statistically obtained at the maximum particles concentration area.The simulation results show that,under the conditions of low acceleration with long operation time,the original axisymmetric flow pattern of internal flow filed of motor has been changed,and the particles concentration increases in the direction of acceleration.The maximum particles concentration is mainly distributed at the circular arc transition section of aft dome.The simulation results can provide some guidance for subsequent thermal protection design of this kind of solid rocket motor.

关 键 词：固体火箭发动机 小过载 两相流 颗粒沉积 科氏加速度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]