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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喷管流动的数值计算模型,并通过算例进行验证。通过对发动机喷管内部流场的研究,发现收敛段中压力首先降到初始温度对应的饱和压强,然后继续降低,并且在喉部的位置开始发生相变,从而使流动变为气液两相流,而且喷管出口处气相体积分数高达99%以上;由于变声速的原因,可以使两相流的流动在喉部之后达到超声速;把喷管的流动分为三个过程:单向流动过程、降压闪蒸过程和膨胀加速过程,与常规的化学能火箭发动机相比有类似性,但是由于闪蒸相变的存在,使其存在一定的复杂性。
In order to understand the working characteristics of hot water rocket engine better, a numerical model of nozzle flow of hot water rocket engine is established and validated by an example. By studying the internal flow field in the engine nozzle, it is found that the pressure in the convergent section first drops to the saturation pressure corresponding to the initial temperature and then continues to decrease, and the phase change begins at the throat so that the flow becomes gas-liquid two-phase Flow, and the nozzle outlet gas volume fraction of up to 99% or more; due to variable sound velocity, the flow of two-phase flow can be achieved after the throat supersonic flow; the nozzle flow is divided into three processes: one-way flow process , The flashback process and the expansion process are similar to the conventional chemical-capable rocket engines, but due to the existence of flash-phase transition, there is some complexity.