氨/氢混合燃料超燃冲压发动机模拟仿真研究

林泽峰; 姜雪; 张天琦; 张英佳; 黄佐华; 颜应文

doi:10.7652/xjtuxb202506001

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氨/氢混合燃料超燃冲压发动机模拟仿真研究

专题　燃烧过程 | 更新时间：2025-08-26

- 氨/氢混合燃料超燃冲压发动机模拟仿真研究
- Numerical Simulation Study of Ammonia and Hydrogen Blends Fueled Scramjet Combustion
- 西安交通大学学报 2025年59卷第6期页码：1-10
- 作者机构：
  
  1.西安交通大学能源与动力工程学院， 710049，西安
  2.南京航空航天大学能源与动力工程学院， 210016，南京
- 作者简介：
  
  林泽峰（2000—），男，硕士生；
  姜雪，女，副教授，博士生导师。
- 基金信息：
  
  国家自然科学基金资助项目(52376124);航空航天结构力学及控制国家重点实验室开放课题资助项目(MCMS-E0323K01);中国内燃机学会京博吉大专用油品研发联合实验室课题资助项目(CSICE-K202204)
- DOI：10.7652/xjtuxb202506001
  中图分类号： TK40
- 收稿：2024-11-21，
  
  网络首发：2025-02-20，
  
  纸质出版：2025-06-10
- 稿件说明：
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林泽峰, 姜雪, 张天琦, 等. 氨/氢混合燃料超燃冲压发动机模拟仿真研究[J]. 西安交通大学学报, 2025,59(6):1-10.

LIN Zefeng, JIANG Xue, ZHANG Tianqi, et al. Numerical Simulation Study of Ammonia and Hydrogen Blends Fueled Scramjet Combustion[J]. Journal of Xi’an Jiaotong University, 2025, 59(6): 1-10.
林泽峰, 姜雪, 张天琦, 等. 氨/氢混合燃料超燃冲压发动机模拟仿真研究[J]. 西安交通大学学报, 2025,59(6):1-10. DOI： 10.7652/xjtuxb202506001.

LIN Zefeng, JIANG Xue, ZHANG Tianqi, et al. Numerical Simulation Study of Ammonia and Hydrogen Blends Fueled Scramjet Combustion[J]. Journal of Xi’an Jiaotong University, 2025, 59(6): 1-10. DOI： 10.7652/xjtuxb202506001.

摘要

为推进飞行器燃料向无碳、可持续化转型，针对氨/氢混合燃料在超燃冲压发动机中的应用开展了燃烧数值模拟研究。首先，采用德国航空航天中心（DLR）燃烧室结构，建立超燃冲压发动机燃烧室模型，并对该模型在冷态和热态工况下的可靠性进行验证；接着，开展了不同比例氨燃料掺混工况下的数值计算和燃烧特性分析。研究发现：随着整体燃料中氨燃料质量分数的增加，燃烧室内反应温度有所降低，燃料型NO

的产量显著增加；由于氨燃料化学反应活性低，在高速流场中难以充分燃尽，掺混燃料后，燃烧效率相较纯氢气工况有明显下降；当氨燃料质量分数为30%时无法稳定燃烧，提高进气来流压力、进气温度和燃料温度均能够达到稳定燃烧边界拓展的效果。该研究为认识超声速燃烧中湍流与燃烧化学相互作用的规律提供了参考，同时为氨燃料超声发动机的设计与优化提供了性能预测依据。

Abstract

To support the carbon-neutral and sustainable transition to alt

ernative aircraft fuels

numerical simulations of the combustion of ammonia and hydrogen fuel blends in scramjet engines was conducted in this study. A scramjet engine model was developed based on the combustion chamber structure from the German Aerospace Center (DLR). The model was validated against experimental data under both cold and hot operating conditions. Numerical calculations and combustion characteristic analyses were conducted with varying ammonia blending ratios. The results indicated that an increase in the ammonia mass fraction led to a lower temperature in the reaction field temperature and higher fuel NO

emissions. The low chemical reactivity of ammonia resulted in insufficient combustion in high-speed flow fields

leading to a significant reduction in combustion efficiency compared with pure hydrogen. Simulation results indicated that stable combustion could not be achieved when the ammonia mass fraction increased to 30% under the current conditions. However

the stable combustion boundary can be effectively expanded by increasing the intake pressure

intake temperature

or fuel temperature. This study reveals the combustion characteristics of ammonia and hydrogen fuel blends under supersonic flow conditions

providing insights into the interaction between chemistry and turbulence in supersonic combustion. Additionally

it offers considerations regarding performance prediction for the design and optimization of ammonia-fueled scramjet engines.

关键词

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