离解组分复合对超燃尾喷管性能的影响  

Effects of Radical Recombination on Scramjet Nozzle Performance

作　　者：张晓源[1] 覃粒子[1] 刘宇[1] 何淼生[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2013年第5期589-594,共6页Journal of Propulsion Technology

摘　　要：采用13组分33步反应的H2/Air化学动力学模型,对超燃冲压发动机尾喷管化学非平衡流动和冻结流动进行数值模拟。计算表明,离解组分的复合现象存在于超燃冲压发动机尾喷管内流动中,并对尾喷管性能产生影响。随飞行马赫数的增加,离解组分复合现象更显著,对尾喷管性能产生的影响也越大。在飞行马赫数为8.0的计算工况下,化学非平衡流动模型计算所得尾喷管性能与冻结流动模型相比高出约2%,该条件下忽略NO2,H2O2等组分以简化化学反应机理,对尾喷管性能计算结果的影响甚微。The non-equilibrium and frozen flows of scramjet nozzle were numerically simulated to study the effects of radical recombination on the nozzle performance,based on 13-species and 33-step H2/Air finite-rate chemistry reaction mechanism.The numerical results show that the recombination occurs during the expansion in scramjet nozzle and that is beneficial to the nozzle performance.With the increase in the flight Mach,the effects of radical recombination on the nozzle performance are more significant.The nozzle performance has improved nearly 2% because of the recombination when the flight Mach is 8.0,and there is nearly no effect to neglect the NO2 and H2O2 compositions on the results of nozzle performance computation.

关 键 词：超燃冲压发动机 喷管 化学非平衡流动 离解 性能计算 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]