固体火箭发动机液体喷射熄火过程中喷射液体的射流速度和液滴运动与蒸发

JET VELOCITY AND EVAPORATION OF DROPLETS DURING LIQUID QUENCH OF SOLID ROCKT MOTOR

关键词:  固体火箭发动机  液体喷射  推进剂  液体雾化  推进剂熄火

Key words:  Solid rocket engine  liquid injection  Liquid atomization Extinguishment of propellant

摘要:

针对在固体火箭发动机液体喷射熄火研究中所用液体喷射实验装置,推导了液体射流速度,液滴运动与蒸发的控制方程组,并进行丁数值求解,研究了影响射流速度、液滴尺寸及其蒸发速率的因素。结果表明:液滴的初始速度和直径主要受喷射压降、液体表面张力和粘度的影响;影响液滴运动速度的因素有环境压强和温度;环境温度和液体的汽化潜热对液滴的蒸发速率有着重要的影响。上述结果对于合理设计满足固体火箭发动机熄火要求的液体喷射装置,选择合适的液体介质具有一定的指导意义。

Abstract:

The jet velocity and evaporation rate of liquid droplets play an important role in the liquid quench proccess of solid rochet motor. In this paper,the governing equation for liquid jet velocity,and movement and evaporation of liquid droplets are deduced in terms of the condition of the apparatus used in the experimental study on liquid quench of solid rocket motor. The group of equation are solved with a numerical method to study the factors influencing the velocity and evaporation rate of liquid drops. The results are as follows, the initial jet velocity and droplet size are dependent upon injection pressure drop, surface tension and viscosity of li-quid.The environmental pressure and temperature have an important effects on the velocity of liquid droplets. The environmental temperature and eva-poration heat of liquid influence evaporation rate of liquid droplets significantly. The results mentioned above are usefull for the Selection of suitible liquid and for the design of liquid injection system to meet the requirements of liquid quench of solid rocket motor.