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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L_2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.
According to years of research experience of liquid rocket engine cavitation tube, this paper expounds the influence of the fillet radius R of the throat and the pressure loss coefficient δ of the straight line segment L_2, and briefly introduces the improvement of the flow channel profile of the main system of the engine. Design and its effects.