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

被引：0

作者：

Fang, Xinxin ^{[1
]}

Wu, Jun ^{[1
]}

Kang, Zhongtao ^{[1
]}

Wang, Zhenfeng ^{[1
]}

Zhai, Xiaofei ^{[1
]}

Li, Hongbin ^{[1
]}

Huang, Kewu ^{[1
]}

Wang, Shimao ^{[1
]}

Liu, Long ^{[1
]}

Dai, Xiong ^{[1
]}

机构：

[1] Science and Technology on Scramjet Laboratory, Aerospace Technology Institute, China Aerodynamics Research and Development Center, Mianyang,621000, China

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 09期

关键词：

Combustion equipment;

D O I：

10.13224/j.cnki.jasp.20220821

中图分类号：

学科分类号：

摘要：

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. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

引用

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