固体火箭技术2018，Vol.41Issue(2)：156-161,168,7.DOI:10.7673/j.issn.1006-2793.2018.02.004
含铝复合推进剂分布燃烧数值模拟
Numerical simulation of distributed combustion of the aluminized composite propellant
摘要
Abstract
For the research of combustion and flow of aluminized composite propellants and multiphase combustion of aluminum particles in the rocket motor,the numerical simulation of aluminized composite propellants was carried out. Based on the EDC com-bustion model and particle surface reaction model in FLUENT software,a two-dimensional and two-phase distributed combustion model of aluminized composite propellants was established according to the combustion theory of aluminum.The computing fluid filed was used to simulate the reacting flow in a solid rocket motor with AP/Al/HTPB propellant.The result shows that the relatively slow combustion rate of aluminum can result in an extended combustion zone in the chamber rather than a thin reaction region. The pres-ence of the extended combustion zone results in the combustor flow field being far from isothermal,and the chemical composition be-ing far from uniform.The temperature in the chamber increases from about 2600 K at the propellant surface to about 3600 K in the combustor,whereas the temperature is 3200 K in the core.The combustion of aluminum is a complex physical and chemical process, which has a great impact on the engine flow field.Particle phase is maintained throughout the entire engine and these particles are fi-nally ejected out of the nozzle.关键词
铝/分布燃烧/EDC燃烧模型/颗粒表面反应模型/数值计算Key words
aluminum/distributed combustion/combustion of aluminum/EDC combustion model/particle surface reaction mod-el/numerical simulation分类
航空航天引用本文复制引用
刘平安,常浩,李树声,王文超..含铝复合推进剂分布燃烧数值模拟[J].固体火箭技术,2018,41(2):156-161,168,7.基金项目
国家自然科学基金(11402061) （11402061）
中央高校基本科研业务费专项基金(HEUCFP201780). （HEUCFP201780）
