喷管喉衬背壁绝热层后效传热炭化分析  

Carbonization analysis on post-effect heat transfer of nozzle throat insulation

作　　者：苏建河[1] 陆贺建[1] 白彦军[1] 唐敏[1] 

机构地区：[1]中国航天科技集团公司四院四十一所固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2017年第4期420-424,共5页Journal of Solid Rocket Technology

摘　　要：针对目前喷管喉衬背壁绝热层后效传热炭化缺乏定量分析的现状,通过材料模型、载荷模型的研究工作,建立能够满足喷管后效传热分析精度要求的喷管温度场有限元计算方法,并通过缩比试验喷管温度场计算与试验测试结果的对比分析进行验证。在此基础上,开展了背壁绝热层后效传热的仿真分析,掌握了后效传热炭化分析方法,并得到了解剖测试结果的验证。研究结果表明,背壁绝热层的炭化大部分发生在后效传热期间。利用该方法进行了全尺寸喷管的背壁绝热层后效炭化分析工作,提出了根据温度计算结果进行裕度评估的方法。评估结果表明,全尺寸喷管的背壁绝热层设计厚度有减薄空间。Aiming at lack of quantitative analysis of nozzle throat insulation＇ s carbide by post-effect of heat transfer, a finite element method was established to calculate the temperature field of nozzle by material model and loading model research.To meet post-effect of heat transfer analysis, this method was verified by the comparative analysis of the nozzle temperature field calculation and experiment tests of shrinkage ratio nozzle. On this basis, the simulation analysis of nozzle throat insulation＇ s carbonization by post-effect of heat transfer was carried out. The method of carbide analysis was mastered and verified by dissection, and the results show that the nozzle throat insulation＇ s carbonization occurs mostly during the post-effect of heat transfer.By using this method,the analysis on full-size nozzle throat insulation＇ s carbonization by post-effect of heat transfer was carried out, and the margin evaluation methods of throat insulation based on temperature was also proposed.The evaluation results show that the thickness of throat insulation could be reduced.

关 键 词：喷管 背壁绝热层 后效传热 炭化 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]