Abstract: The nozzle performance of a small LRE for space propulsion was calculated using chemical equilibrium and chemical kinetic methods. Parameters influencing thruster chamber performance, such as the chamber pressure, mixture ratio, mass fraction of the cool film, and the scale of nozzle geometry, etc., were analysed quantitatively. These can be used to evaluate engine performance and find ways to increase it.

Key words: Liquid propellant rocket engine;Thrust chamber;Nozzle;Reaction kinetics;Influence factor

摘要： 针对某液体发动机进行化学动力学计算,研究了各种推力室参数,如燃烧室压强、混合比、边区冷却流量以及喷管的尺寸等对喷管性能的影响。由计算结果可以得到参数变化引起性能变化的定量的规律,分析推力室设计的优劣,提出改善发动机性能的具体措施。

关键词: 液体推进剂火箭发动机;推力燃烧室;喷管;反应动力学;影响因素