一种固体发动机喷管喉衬烧蚀传热计算方法  

A Calculation Method for Ablation Heat Transfer of Solid Rocket Motor Nozzle Throat

作　　者：裴少帅 PEI Shaoshuai(The Institute of Xi’an Aerospace Solid Propulsion Technology, Xi’an 710025, China)

机构地区：[1]西安航天动力技术研究所

出　　处：《机械》2019年第7期26-29,41,共5页Machinery

摘　　要：基于喷管喉衬材料在工作过程中的烧蚀模型,建立了一种喷管喉衬瞬态烧蚀传热计算方法。采用Python语言对MSC.Marc进行二次开发,引入喉衬烧蚀移动边界和瞬变内流场边界,实现了对喷管喉衬工作过程烧蚀传热计算。计算获得了喉衬工作过程中与高温燃气接触表面形貌变化规律和温度分布规律。计算结果表明,喉衬工作过程中考虑烧蚀时,最大径向线烧蚀率发生在瞬时喉部前端;瞬时喉部随工作时间加长向喉衬出口端移动;喉衬整体温度相比未考虑烧蚀的喉衬温度有显著差异。计算方法为喷管喉衬的精细化设计提供了设计依据,对喉衬工作过程可靠性评估具有指导意义。Based on the ablation model of the nozzle throat material during the working process, a calculation method of transient ablation heat transfer of the nozzle throat is established. The secondary development of MSC.Marc is carried out in Python language. The boundary between the ablation and the transient flow field of the throat is introduced, and the ablation heat transfer calculation of the nozzle throat is realized. The variation law and temperature distribution law of surface contact with high temperature gas during the working process of throat are obtained. The calculation results show that the maximum radial line ablation rate occurs at the front end of the instantaneous throat when ablation is considered during the operation of the throat;the instantaneous throat moves with the working time to the exit end of the throat;There is a significant difference in the overall temperature of the throat considered ablation to the overall temperature of the throat not considered. The calculation method provides the design basis for the refined design of the nozzle throat, and has guiding significance for the reliability evaluation of the throat working process.

关 键 词：固体发动机 喷管喉衬 烧蚀 传热 

分 类 号：TB115.1[理学—数学]