水下燃气-蒸汽弹射气-液两相流场数值研究

基于计算流体动力学方法和均质多相流理论,采用汽化模型模拟燃气与冷却水的汽化过程,使用动态网格分层技术模拟导弹的运动,对燃气-蒸汽弹射气-液两相流场进行三维非定常数值研究.通过与固体火箭发动机尾焰喷水效应实验对比,验证了数值方法的有效性.研究了弹射过程中流场结构、二次流现象和变深度弹射载荷和内弹道变化规律.结果表明:导弹弹射过程中汽化现象发生在弯管壁面处,汽化后的燃气-蒸汽高温区随着发射筒体积的增加发生偏移;燃气-蒸汽在发射筒和弯管截面上存在隔离区和二次流动现象,并且形成不同结构形式的漩涡;弯管受到的最大冲击力出现在0.16s附近和30°~ 60°弯曲角范围内;弹射深度每增加10m,观测点压力增加0.25MPa,弹动时间延迟0.01s. 

Numerical study of gas-steam ejection gas-liquid two-phase flow field under water

Based on computational fluid dynamic method and homogeneous multiphase theory,vaporization model was adopted to simulate vaporization between gas and cooling water, and missile's motion was simulated by dynamic zone mesh motion method. Three-dimensional unsteady gas-steam ejection gas-liquid two-phase flow field was studied. Compared with the experiment of solid rocket flow field injection with water, this proved that the numerical method was reliable. The flow field structure, secondary flow, load characteristic and internal trajectory in variable depth ejection during ejection were studied. The results show that the evaporation occurs on the wall of the pipe. The gas-steam high temperature region migrates with the increase of tube volume during ejection. Isolation region and secondary flow exist at cross section of the tube and pipe, and form different eddy structures. The maximum impact force occurs on the wall of the pipe between 30° and 60° bend angle at 0.16s. With the ejection depth increasing 10 m, the pressure of monitor is added by 0.25MPa and time of missile motion is delayed 0.01s.