论文部分内容阅读
为了更好地了解热水火箭发动机的工作特性,建立了热水火箭发动机内流场的数值计算模型,对发动机非稳态的工作过程进行模拟,并与实验数据对比进行验证。通过对发动机工作过程的研究,发现在发动机工作过程中,喷管之前相变较缓慢,而在喷管中相变比较剧烈,从而使得喷管部分的气体体积分数梯度较大,越靠近出口,气体体积分数越大,出口气体体积分数高达90%以上,其温度越低。发动机内部压力首先急剧降到初始温度对应的饱和压强,然后缓慢降低。把热水火箭发动机的工作过程分为三个阶段:初始段、中间段和拖尾段。发动机的总冲主要集中在中间段,约占总比冲的70%以上。
In order to better understand the working characteristics of hot water rocket engine, a numerical model of the internal flow field of hot water rocket engine is established. The unsteady working process of the engine is simulated and compared with the experimental data. Through the study of the working process of the engine, it was found that during the working process of the engine, the phase change before the nozzle is relatively slow and the phase transition is relatively intense in the nozzle so that the gradient of gas volume fraction in the nozzle part is larger and closer to the outlet, The larger the gas volume fraction, the outlet gas volume fraction of up to 90%, the lower the temperature. The internal pressure of the engine first drops sharply to the saturation pressure corresponding to the initial temperature and then decreases slowly. The hot water rocket engine work process is divided into three stages: the initial section, the middle section and the tail section. The main engine of the total red in the middle section, accounting for more than 70% of the total than red.