本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。

This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.

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并提出了减少压力最大值的方法，对于低温液体输送参数的确定、管道的设计提供参考。

The ways to reduce the maximum pressure were also proposed in this paper. It provided the reference to determine the parameter in transferring cryogenic liquid and to design the pipes.

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