高温氧化铝液滴沉积条件下绝热材料烧蚀特性研究  

Ablation Characteristics of Insulation Material under High Temperature Alumina Droplet Deposition Condition

作　　者：关轶文[1] 李江[1] 刘洋[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,陕西西安710072

出　　处：《推进技术》2017年第8期1833-1839,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目NSFC(51576165;51276150);中央高校基本科研业务费(3102014ZD0032)

摘　　要：为了研究三元乙丙绝热材料在高温氧化铝液滴沉积条件下的烧蚀特性,基于模拟沉积实验装置,开展了烧蚀实验研究。利用SEM与XRD等分析了烧蚀后炭化层断面形貌特征和化学组分分布,探讨了火箭发动机工作环境中氧化铝液滴与炭化层间热化学烧蚀的主要反应机理,确定了沉积条件下的化学反应方程式。研究结果表明:(1)高温氧化铝沉积条件下,三元乙丙绝热材料材料炭化层断面呈现"致密/疏松"的多孔结构;(2)推导并建立了固体火箭发动机高温高压环境中氧化铝与炭化层的七步热化学反应方程;(3)利用热力学软件分析可知,发动机工作条件下氧化铝与炭化层反应首先生成Al4C3,随着温度的升高继而生成Al单质与碳-氧-铝化合物Al2OC并释放出还原性CO气体。In order to investigate the ablation characteristics and mechanism of EPDM insulation material in high temperature alumina droplet deposition condition, based on the lab-scale experimental device, the abla- tion experiment was performed. SEM and XRD were used to analyze the surface morphology and chemical compo- sition of the charring layer after ablation experiment, the main reaction mechanism of the alumina droplet and charting equation charring layer in Solid Rocket Motor （SRM） operating condition was discussed, then the chemical reaction under deposition condition was determined. The results shows that： （1） the EPDM insulation material layer section presents porous structure of ＂tight/loose＂ under the condition of alumina droplet deposi- tion. （2） The seven-step thermo-chemical reaction equation of alumina and charring layer in high temperature and high pressure environment of SRM was deduced and established. （3） Thermodynamic analysis shows that under the SRM operating condition, the reaction of alumina and charring layer first formed A14C3, with the tem- perature increased, A1 elemental and carbon-oxygen-aluminum compound AI：OC were formed and then re- leased the gas of CO.

关 键 词：固体火箭发动机 绝热层 沉积 烧蚀 实验装置 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]