Abstract: Based on many year cavitation venturi design experience, the effects of the venturi throat contour on its pressure loss coefficient are presented in this paper. The improvement design and thus achieved performance upgrading of two main cavitation venturies used in a large liquid rocket engine is also presented.

Key words: Engine control system;Liquid propellant rocket engine

摘要： 本文根据液体火箭发动机汽蚀管的多年研制经验,阐述了喉部圆角半径R和直线段L₂对压力损失系数δ的影响,并简要介绍了某发动机主系统汽蚀管流道型面的改进设计及其改进效果.

关键词: 发动机控制系统;液体推进剂火箭发动机