固体发动机喷管喉衬温度场测量与分析  

The measurement and analysis of temperature field in a solid motor nozzle throat insert

作　　者：李佳明[1] 胡春波[1] 张胜敏[1] 何国强[1] 肖虎亮[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,西安710072

出　　处：《实验流体力学》2012年第5期57-60,共4页Journal of Experiments in Fluid Mechanics

基　　金：国家'973'项目(61391)

摘　　要：为了剥离热化学烧蚀吸热的影响并获取固体火箭发动机喷管结构内部的温度场分布,以锻压钨为材料设计喷管,在喷管喉衬径向的一定位置埋置热电偶来测量喷管结构温度。实验结果表明:采用锻压钨制作喷管,该本实验条件下可以忽略热化学烧蚀对锻压钨喷管喉部换热的影响;实验测量结果符合传热规律,与导热计算结果基本吻合。实验结果真实可信,为喷管喉部对流换热模型的建立、完善提供数据支持和实验验证。To peel off the impact of endothermic reaction caused by the chemical ablation, forging tungsten is use＆as material for rocket nozzle insert. In the experiment of a solid motor e- quipped with forging tungsten nozzle, the thermocouples have been embedded at different radial locations of the nozzle throat insert for measuring temperatures, and the temperature distribu- tions in the rocket-nozzle insert have been obtained. Experimental results show that, for the rocket-nozzle insert made of forging tungsten, the impact of endothermic reaction caused by the chemical ablation is negligible in the throat region; the experimental results are basically consist- ent with the calculation results. The results and the method presented in this paper can be a ref- erence to the design of nozzles in rocket motors.

关 键 词：喉衬 温度分布 锻压钨 导热 热电偶 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]