火箭推进2026，Vol.52Issue(4)：56-67,12.DOI:10.3969/j.issn.1672-9374.2026.04.006
气氧/气甲烷火炬点火器燃烧流场与工作性能分析
Analysis of combustion flow field and operational performance for a gaseous oxygen/gaseous methane torch igniter
摘要
Abstract
To address the thermal protection requirement of the combustion chamber wall for a gaseous oxygen/gaseous methane torch igniter,a numerical simulation method was employed to investigate the combustion process within the igniter's combustion chamber.Under the condition of a constant total propellant mass flow rate,the effect of the mixture ratio on the temperature field,species distribution,and wall thermal load was analyzed.With a fixed mixture ratio of 1.0,the influence of the total propellant mass flow rate on combustion performance was examined,and three different methane nozzle arrangement schemes were compared to evaluate their effects on thermal protection performance.The results indicate that increasing the mixture ratio leads to radial expansion of the high-temperature zone and an increase in wall temperature.When the mixture ratio is 1.2,the flame further approaches the combustion chamber wall.Increasing the propellant mass flow rate significantly enhances the pressure within the combustion chamber.However,once the flow rate exceeds 50 g/s,both the exit temperature and the power density begin to decline.The dual-row staggered methane nozzle configuration effectively reduces wall temperature,improves combustion uniformity,and enhances thermal protection performance.These findings provide a theoretical basis for the structural optimization and thermal protection design of torch igniters.关键词
火炬点火器/气氧/气甲烷/燃烧流场/混合比/数值模拟Key words
torch igniter/gaseous oxygen/gaseous methane/combustion flow field/mixture ratio/numerical simulation分类
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茹子超,谷鑫阳,郑怀,刘鑫鹏,陈立,李捷,姬威信..气氧/气甲烷火炬点火器燃烧流场与工作性能分析[J].火箭推进,2026,52(4):56-67,12.基金项目
武汉市科技项目(2023010302020032) （2023010302020032）
