火箭推进2026，Vol.52Issue(3)：1-12,12.DOI:10.3969/j.issn.1672-9374.2026.03.001
固体燃料ATR发动机富燃燃气燃油喷雾冷却方法研究
Research on fuel spray cooling method of fuel-rich gas for solid-propellant ATR engine
摘要
Abstract
To address the issue of the exhaust temperature of fuel-rich gas in solid-propellant ATR engines exceeding the heat resistance limit of turbine blades without internal cooling,a method for cooling the rich combustion gas with fuel was proposed.A step-by-step coupling numerical method called"near-field atomization and far-field mixing"was developed to analyze this process.The effects of using one,two,or four nozzles on cooling efficiency and temperature uniformity were examined.The results indicate that the simulation errors for the atomization cone angle and flow characteristics of the centrifugal nozzle are only 1.18％and 2.51％,respectively.Compared to the round-hole direct-flow nozzle,the centrifugal nozzle is more effective for the cooling and mixing processe of fuel-rich gas.Among them,the dual-nozzle achieves the optimal balance in cooling efficiency,temperature uniformity,and engineering applicability.Under the maximum pressure condition,the average outlet temperature drops to 1 118 K,with a maximum temperature difference of only 60 K.In addtion,the temperature distribution factor(TDF)is as low as 0.113.关键词
固体燃料空气涡轮火箭发动机/富燃燃气/燃油冷却/多喷嘴/温度均匀性Key words
solid-propellant ATR engine/fuel-rich gas/fuel cooling/multiple nozzles/temperature uni-formity分类
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黄鹏飞,杨学森,赵巍,曾文,李繁,赵庆军..固体燃料ATR发动机富燃燃气燃油喷雾冷却方法研究[J].火箭推进,2026,52(3):1-12,12.基金项目
中国科学院工程热物理研究所所长基金(Y951015Z21) （Y951015Z21）
