Abstract: The nozzle performance of a small LRE for space propulsion was calculated using chemical equilibrium and chemical kinetic methods. For small LRE, kinetic loss is larger and nozzle performance is closed to frozen state. Kinetic loss is mainly produced in the divergence area near throat. High area ratio tends to have larger kinetic losses.

Key words: Liquid propellant rocket engine;Nozzle;Performance;Chemical equilibrium;Chemical kinetics~+

摘要： 应用化学平衡流动和化学反应动力学的方法对某液体发动机喷管进行计算,得到了不同面积比下的燃气参数和发动机性能参数分布。小型液体火箭发动机的化学动力学损失比较大,性能接近冻结流动的结果。化学动力学损失主要产生在喷管初始膨胀部分,随着面积比的增加,化学动力学损失增大。

关键词: 液体推进剂火箭发动机;喷管;性能;化学平衡;化学动力学+