董天洋1 ,林志勇 1 ,席文雄 2,3 ,张定瑞 1.自点火氢燃料超燃火焰形成与传播过程数值模拟及分析[J].航空发动机,2024,50(1):79-86
Numerical Simulation on Flame Formation and Propagation of Hydrogen Fueled Scramjet with Auto-ignition
DOI:
Key Words:scramjet  supersonic combustor  cavity  flame stability  hydrogen
作者单位
董天洋1 ,林志勇 1 ,席文雄 2,3 ,张定瑞 1 1.中山大学 航空航天学院广东深圳 518107 2.中南大学 航空航天技术研究院长沙 410083 3.湖南中盛高科技研究院长沙 410011 
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Abstract:In response to combustion details of hydrogen fueled scramjet combustor, the numerical simulation method was used to investigate the formation and propagation of hydrogen flame with auto-ignition in a scramjet combustor with different injection positions and equivalence ratios during the initial injection stage. The fine flow field structure of flame in the ignition combustion process was analyzed by combination with the distribution of OH, HO 2 radicals, and temperature. The results show that when the downstream nozzle of the cavity is close to the rear edge of the cavity, if the injection pressure exceeds 2 MPa, the downstream flame will be drawn into the cav? ity through the recirculation area; The arrangement of nozzle in the cavity will form a stable reaction surface at the front of the cavity shear layer, resulting in the separation of the reaction zone; With the injection pressure is the same and the nozzle is arranged upstream, the oxygen consumption rate at the outlet of the combustor will be higher and the total pressure recovery coefficient will be lower, while the injection position is the same, the oxygen consumption rate at the outlet of combustion chamber increases with the increase of injection pressure, and the total pressure recovery coefficient decreases; Different injection equivalence ratio will not affect the stable position and structure of the flame, with lower equivalence ratio, hydrogen combustion mainly occurs in the cavity, shear layer and downstream of the combustor, while with higher global equivalence ratio, it occurs downstream of the combustor.
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