固体微推力器气粒两相羽流场的数值模拟  

Numerical simulation for gas-particle two-phase plume flow of solid propellant micro-thruster

作　　者：张斌[1] 毛根旺[1] 胡松启[1] 陈茂林[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2011年第3期314-318,共5页Journal of Solid Rocket Technology

基　　金：总装备部预研基金资助项目(9140C5203120960)

摘　　要：采用DSMC/EPSM混合算法,结合稀薄流中气粒耦合作用模型,开展了固体微推力器羽流场中气粒两相稀薄流动的数值研究,研究了羽流场中气粒两相参数的分布规律和气相组分分离效应。结果表明,气相与颗粒相间的动量传递导致颗粒相的轴向速度显著增加,两相间的能量传递导致颗粒相的温度降低,气相对颗粒相作用显著;由于燃气中颗粒相含量较少,颗粒相对气相压强场、温度场和轴向速度场的影响并不明显;羽流场中气相组分分离效应显著,扩散效应导致分子量最小的氢气组分在壁面附近的真实分子数密度远大于其他组分,小分子量气体组分在羽流场中的高度扩散是羽流对固体微推力器壁面产生侵蚀和附着效应的主要原因。Numerical simulation for gas-particle two-phase plume flow of solid propellant micro-thruster was investigated by combining DSMC/EPSM algorithm and gas-particle coupling model.The two phase characteristics and gas component separation effect in the plume field were studied.The results showed that the axial velocity of particle increased significantly due to the momentum transfer between gas molecules and particles,the particle temperature decreased due to the energy transfer between gas molecules and particles,and the effects on particles exerted by gas molecules were obvious;the gas pressure field,temperature field and axial velocity field were not obviously influenced by particles due to the low mass content of particles in the plume flow;the component separation effect in gas phase was obvious and the molecular number of hydrogen near the wall was obviously more than any other components duo to its diffusion effect,the plume erosion effect and plume adherence effect to the wall of micro-thruster were mainly caused by the strong diffusion of the component of low molecular weight.

关 键 词：固体微推力器 DSMC/EPSM 气粒两相流动 羽流 组分分离效应 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]