线性可调汽蚀文氏管设计与数值仿真研究

On Design and Numerical Simulation for Linear Throttling Cavitation Venturi

可调汽蚀文氏管是变推力火箭发动机实现推进剂流量和推力大范围调节的关键部件.在设计线性可调汽蚀文氏管模型的基础上,采用基于Rayleigh-Plesset方程的混合流体模型,进行了相关的数值分析.计算结果表明:设计的线性可调汽蚀文氏管可以实现流量的大范围调节,并且流量与调节锥行程呈线性变化关系,满足设计要求.

Throttling cavitation venturi, which can control the propellant flux and thrust in a wide range, is an important component of throttling rocket engine. Based on the designed model, a numerical simula tion of cavitation flow in venturi is performed with a mixture model based on RayleighPlesset equation. The results indicate that the linear throttling cavitation venturi can regulate the propellant flux in a wide range. Furthermore, the flux changes linearly with respect to the movement of actuator. The proposed cavitation venturi can satisfy the need of design.