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为揭示圆盘形燃烧室内旋转爆震波的传播特性,以2H_2+O_2+3.76N_2为反应混合物,开展该结构下的二维数值研究。实现了旋转爆震波的成功起爆并得到了两种稳定的流场结构;详细分析了两种流场的特点,以及不同直径处爆震波参数及出口马赫数的变化规律。结果表明,旋转爆震波在壁面形成的反射激波对流场中的温度、压力分布以及流线都产生影响;随着直径的不断减小,旋转爆震波压力、温度以及传播速度都不断减小;流场稳定后,出口马赫数随时间的变化趋势与压力趋势相符,呈现“双波峰”特征。喷注总压为0.4MPa时,喷注入口的阻塞比为21%,超声速流动占整个出口流动的52.17%,出口流动的平均马赫数为0.98;当喷注总压降为0.2MPa时,入口阻塞比为20%,超声速流动占21.99%,出口流动的平均马赫数为0.95。
In order to reveal the propagation characteristics of the rotational detonation wave in a disc-shaped combustion chamber, a two-dimensional numerical study of this structure was carried out using 2H_2 + O_2 + 3.76N_2 as the reaction mixture. The successful initiation of the rotary detonation wave was achieved and two stable flow field structures were obtained. The characteristics of the two kinds of flow fields, as well as the variation of the detonation wave parameters and the outlet Mach number at different diameters, were analyzed in detail. The results show that the reflected shock waves formed on the wall by the rotary detonation wave have an impact on the temperature, pressure distribution and flow line in the flow field. As the diameter decreases, the pressure, the temperature and the propagation velocity of the rotary detonation wave continuously decrease After the flow field was stabilized, the trend of Mach number at exit coincided with the trend of pressure, showing the characteristic of “double crest”. When the total injection pressure was 0.4MPa, the blockage ratio of injection inlet was 21%, the supersonic flow accounted for 52.17% of the total outlet flow and the average Mach number of outlet flow was 0.98. When the total pressure drop of injection was 0.2MPa, The blockage ratio was 20%, the supersonic flow accounted for 21.99% and the average Mach number for the exit flow was 0.95.