固体火箭发动机燃烧室中的颗粒轨迹

PARTICLE TRAJECTORIES IN COMBUSTION CHAMBER OF SOLID ROCKET MOTOR

关键词:  固体推进剂火箭发动机  燃烧室  二相流  颗粒大小  颗粒轨迹

Key words:  Solid propellant rocket engine  Combustion chamber  Two phase flow  Particle size  Particle trajectory

摘要:

用气相与颗粒场耦合的轨迹模型法计算了固体火箭发动机燃烧室两相流中的颗粒运动轨迹。结果表明： 颗粒轨迹受颗粒尺寸大小、颗粒初始速度的大小和方向以及气相运动特性等影响。燃烧室中的两相流动是一种非常滞后的非平衡流动。颗粒尺寸越大， 惯性越大， 随流性越差。尺寸相差较大的颗粒可能有完全不同的轨迹。在一定条件下，颗粒会穿过通道的中心线，甚至打到对面壁上并反弹。颗粒会受气相旋涡的影响， 甚至有可能卷入旋涡

Abstract:

The particle motion trajectories in two phase flow of solid rocket motor combustion chamber are calculated by the PSIC(Particle Source in Cell)method.The gas phase axisymmetric N S and k ε equations in two phase flow are solved by SIMPLE method and finite volume method on nonstaggered grid system.Study results for combustion chamber with conocyl type grain specify that:the particle trajectories will be effected by particle dimension,initial velocity,gas phase flow property,etc.The two phase flow in combustion chamber is non equilibrium and non constant delay flow.The more particle dimension and inertia are,the worse property with gas phase flow is.The particles which dimensional difference is greater may possesses all different trajectories.On certain conditions,the particle can pass through the mean line of passage,even strike at opposite wall and eject back.The particle will be effected by gas phase vortex,even can be involved in vortex +