氢氧燃烧加热器点火试验和数值仿真研究  

Ignition experiment and numerical simulation on a combustion heater with hydrogen and oxygen

作　　者：方昕昕 伍军 康忠涛 王振锋 翟小飞 李宏斌 黄可武 王世茂 刘龙 代雄 FANG Xinxin;WU Jun;KANG Zhongtao;WANG Zhenfeng;ZHAI Xiaofei;LI Hongbin;HUANG Kewu;WANG Shimao;LIU Long;DAI Xiong(Science and Technology on Scramjet Laboratory,Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《航空动力学报》2024年第9期377-383,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(12202480,11902342);高超声速冲压发动机技术重点实验室基金(WDZC6142703202208)。

摘　　要：点火试验和数值仿真研究了氢氧燃烧加热器,对比了二组元和三组元两种不同构型的加热器性能。试验结果表明:二组元和三组元燃烧加热器均实现了“自点火”,相较于三组元燃烧加热器,二组元燃烧加热器点火延迟时间减小约17.0%。试验中二组元和三组元燃烧加热器分别稳定燃烧190 ms和189 ms,没有出现不稳定燃烧。试验和数值仿真得到的高温点火区分布类似,三组元加热器高温点火区更集中于氢气喷孔之后,二组元加热器高温点火区呈现V形。从试验喷嘴图像可见,相较于二组元燃烧加热器,三组元燃烧加热器在喷嘴出口处烧蚀的面积更大,烧蚀部位的温度更高,与数值仿真结果一致。Ignition experiments and numerical simulation were conducted to study a combustion heater with hydrogen and oxygen.Two different types of combustion heater,i.e:bipropellant combustion heater and tripropellant combustion heater,were studied.Both of them achieved self-ingition.Compared with the tripropellant combustion heater,the bipropellant combustion heater had shorter ignition delay time by 17.0%.The bipropellant combustion heater and tripropellant combustion heater worked stably and lasted for 190 ms and 189 ms,separately,in the experiments.The high temperature zones in the experiments and numerical simulations were similar.The high temperature zone in the tripropellant combustion heater located behind the hydrogen ignition hole,while the bipropellant combustion heater had a V-shape high temperature zone.From the experimental images of the injectors,the tripropellant combustion heater had a bigger ablation area,which was in consonance with the numerical results.

关 键 词：燃烧加热器 氢气 喷注结构 点火试验 火焰形状 

分 类 号：V434.22[航空宇航科学与技术—航空宇航推进理论与工程]