Abstract: The parameters and performances of two LOX/Hydrocarbon engine systems with different kind of power cycles are obtained through theoretical calculation. Effects of the mixture ratio, turbin inlet temperature and pump efficiency on engine performances are also calculated, The relationships between the turbin bypass ratio and the chamber pressure for gas generater cyele, and between the fuel pump discharge pressure and chamber pressure for stage-combustion cycle are derived from the engine system equations. In the last part of this paper, an analysis of the applicable ranges of the two power cycles is presented.

Key words: Liquid propellant rocket engine

摘要： 本文通过理论计算得出两种循环的液氧/烃类发动机参数和性能,计算了混合比、涡轮进口温度、泵效率等参数对发动机性能的影响。利用涡轮功率平衡方程推导出发生器循环的涡轮流量与总流量比和燃烧室压力的关系;分级燃烧循环的燃料泵出口压力与燃烧室压力的关系。最后分析了两种循环的适应范围。

关键词: 液体推进剂火箭发动机