固体火箭发动机内铝颗粒燃烧特性分析

Analysis of Combustion Characteristics of Aluminum Particles in Solid Rocket Motors

摘要: 火箭发动机的推进系统对于高能量释放的燃料有着极高的需求。由于金属颗粒可以在燃烧过程中释放大量热能，因此其在固体火箭推进剂中被广泛应用。铝颗粒群燃烧过程中的颗粒粒径分布，颗粒温度分布，颗粒与气相间速度差，对火箭推进剂的燃烧效率影响很大。本文基于CFD软件，建立了铝颗粒燃烧的数值模拟模型，针对铝颗粒群燃烧过程中的温度分布、速度差及粒径分布进行了分析。研究表明，燃烧初期温度较低，分布均匀，中期局部高温区域增多，后期温度下降并趋于不均匀；速度差在燃烧中期最大，受燃烧释放的热量和气体流动影响；颗粒粒径随燃烧过程逐渐减小，残渣主要以微米级颗粒形式存在。

Abstract: The propulsion system of rocket engines has a high demand for high-energy released fuel. Due to the ability of metal particles to release a large amount of thermal energy during combustion, they are widely used in solid rocket propellants. The particle size distribution, temperature distribution, and velocity difference between particles and gas during the combustion process of aluminum particle clusters have a significant impact on the combustion efficiency of rocket propellants. This article is based on CFD software to establish a numerical simulation model of aluminum particle combustion, and analyzes the temperature distribution, velocity difference, and particle size distribution during the combustion process of aluminum particle clusters. Research has shown that in the early stages of combustion, the temperature is relatively low and evenly distributed. In the middle stages, there are more localized high-temperature areas, and in the later stages, the temperature decreases and tends to be uneven; the speed difference is maximum during the middle stage of combustion, influenced by the heat released by combustion and gas flow; the particle size gradually decreases during the combustion process, and the residue mainly exists in the form of micrometer sized particles.