Abstract: 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 simulation of cavitation flow in venturi is performed with a mixture model based on Rayleigh-Plesset 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.

Key words: throttling cavitation venturi, throttling rocket engine, mixture ratio adjustment, regulate the propellant flux