轴对称激波诱导矢量喷管三维两相流数值模拟  

Numerical Study on 3-D Two-Phase Flow of Axisymmetric Shock Induction Controlled Vectoring Exhaust Nozzle

作　　者：宋亚飞[1] 高峰[1] 马岑睿[1] 文科[1] 

机构地区：[1]空军工程大学导弹学院,陕西三原713800

出　　处：《推进技术》2012年第2期239-244,共6页Journal of Propulsion Technology

摘　　要：运用颗粒轨道模型对轴对称激波诱导矢量喷管内流场进行了数值模拟,并与纯气相条件下的计算结果进行了对比分析,研究了1～30μm不同直径颗粒的运动轨迹和内流场参数的分布特征,并对矢量喷管的推力性能进行了研究。结果表明,颗粒相的加入对射流推力矢量喷管内流场和推力性能都带来很大影响,影响规律与颗粒直径密切相关。为两相流条件下射流矢量喷管的试验研究提供了一定依据。Numerical simulations of on gas-solid two-phase in axisymmetric shock induction controlled vectoring exhaust nozzle were carried out using particle trajectory model. The simulation results were compared with that under the situation of pure gas. The particle track, parameters in internal flow, as while as the thrust performance were studied when particles diam- eter changed in the range of 1 -30μ m. The results showed that the addition of particle phase influenced the internal flow field as well as the thrust characteristic of nozzle. Such influence varied with the diameter of particle. These conclusions are helpful for the experiment on vectoring nozzle.

关 键 词：推力矢量 射流推力矢量喷管 三维两相流 颗粒轨道模型 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]