喷管喉部热流密度测量实验研究  

Experimental investigation on heat flux measurement of nozzle throat

作　　者：肖虎亮[1] 胡春波[1] 张胜敏[1] 邓哲[1] 秦飞[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：《固体火箭技术》2013年第1期138-142,共5页Journal of Solid Rocket Technology

摘　　要：为剥离热化学烧蚀对喷管喉部热流密度测量的影响,将HT50-20热流计安装在喷管喉部,使之直接接触燃气,测量不同燃气温度条件下喷管喉部的热流密度,并获得了来流燃气的参数,在此基础上,对喷管喉部热流密度进行了数值模拟计算。实验结果表明,当喉部燃气温度分别为611、551、457 K时,热流密度分别为0.496、0.471、0.317 MW/m2,实验数据可为相关数值模拟提供实验验证。In order to isolate the effect of thermochemistry ablation on measuring the heat flux of nozzle throat, the experiments were carried out by using a HT50-20 heat flux transducer to obtain the heat flux density in nozzle throat under various incoming flow conditions as well as the parameters of the burning gases. Meanwhile, on the basis of experiments, numerical simulation was conduc- ted to investigate the heat flux of nozzle throat. The experimental results show that the heat flux density is 0. 496 MW/m2 ,0. 471 MW/m2 ,0. 317 MW/m2 when the temperature of burning gases at the nozzle throat is 611 K,551 K,457 K respectively. Further- more, the data of experiments can be used to validate the numerical simulation.

关 键 词：喷管喉部 热流计 热流密度 实验测量 

分 类 号：V554.3[航空宇航科学与技术—人机与环境工程]