固体火箭发动机碳基材料喷管热化学烧蚀特性

推进技术 ›› 2012, Vol. 33 ›› Issue (1): 93-97.

固体火箭发动机碳基材料喷管热化学烧蚀特性

张晓光,王长辉,刘宇,任军学

北京航空航天大学宇航学院,北京 100191;北京航空航天大学宇航学院,北京 100191;北京航空航天大学宇航学院,北京 100191;北京航空航天大学宇航学院,北京 100191

发布日期:2021-08-15
作者简介:张晓光(1986—),男,博士生,研究领域为航空宇航推进理论与工程。E-mail:zhangxiaoguang1986@126.com

Carbon-Based Nozzle Thermochemical Erosion Characteristics in Solid Rocket Motors

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 为了准确预示固体火箭发动机碳基材料喷管的烧蚀率,依据热化学烧蚀理论,建立了喷管传热烧蚀的二维轴对称气-固-热耦合计算模型,计算通过FLUENT壁面化学反应模型完成,无需事先假设烧蚀控制机制。针对70-lb BATES发动机喷管进行了烧蚀计算,研究了推进剂配方、氧化性组分、燃烧室压强对喷管烧蚀的影响。结果表明:烧蚀率计算值与试验测试值吻合较好；烧蚀率分布遵循喷管内壁热流密度分布规律,在喉部上游入口处达到峰值；烧蚀率随推进剂Al含量增加而降低,随燃烧室压强升高而近似正比例增大；H₂O是决定烧蚀的主要氧化性组分。 

关键词: 固体火箭发动机;喷管;烧蚀;数值仿真

Abstract: Based on the thermochemical erosion theory, a two-dimensional axisymmetric, coupled gas-solid-thermal numerical framework was established to predict the carbon-based nozzle erosion in solid rocket motors. Numerical simulations were carried out using the Wall Surface Reaction model of the commercial code FLUENT and the assumption whether the erosion process was chemical kinetics or diffusion controlled was not needed. The method was introduced to simulate the 70-lb BATES motor nozzle erosion and examine the effects of propellant composition, oxidizing species and chamber pressure. The calculated results agree well with experimental data. The erosion rate follows the trend exhibited by the heat flux distribution, and peaks slightly upstream of the throat. The erosion rate decreases with increasing aluminum content and increases almost linearly with chamber pressure. H₂O is the dominant oxidizing species in dictating nozzle erosion. 

Key words: Solid rocket motor; Nozzle; Erosion; Numerical simulation

张晓光,王长辉,刘宇,任军学. 固体火箭发动机碳基材料喷管热化学烧蚀特性[J]. 推进技术, 2012, 33(1): 93-97.

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