Motion and Combustion of Non-Spherical Metal Particle in Channel Flow Induced by Wall Injection

摘要

Aluminized composite propellant used in solid rocket motors (SRMs) contains a lot of aluminium particles because high combustion energy is generated and propulsion efficiency increases by burning aluminium particles. The development of robust models of aluminum particle dynamics and morphology is essential in the design of advanced propulsion systems. The study focuses on the numerical analysis of reacting turbulent gas-particle flows inside combustion chamber of SRMs. The mathematical model of two-phase flow around a single aluminum droplet with oxide cap is developed and validated against experimental data. The model solves the continuity, momentum, energy and species continuity equations simultaneously to obtain the species and temperature profiles and the burning time of droplet. These equations allow calculating force and angular moment acting on the aluminium droplet. Geometry of the aluminium droplet and its oxide cap changes as mass is removed from the aluminium particle and oxide cap mass increases during aluminium combustion. The flow fields over inert and reacting particle of spherical and non-spherical shape are computed. Effects of the convective stream showed that a symmetry hypothesis usually used in many models is not suitable for configurations typical for combustion chambers of SRMs.