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为了研究小推力液体火箭发动机燃烧室的喷雾燃烧特性,设计了小尺度模拟燃烧室和对撞射流喷嘴,利用多普勒相位粒子动态分析仪(PDA),观测了对撞射流在小尺度空间内的喷雾,重点观测了喷雾压力对于雾化特性参数的影响。实验结果表明:测量截面与喷嘴的距离越远,液滴平均直径越大,轴向速度越小;测量点到中心轴的距离越远,液滴轴向速度越小,径向速度波动越大;喷雾压力越大,液滴平均直径越小,轴向速度越大。由于受到壁面的影响,径向速度的周向分布在不同的喷雾压力下和测量点位置上的差异不明显;模拟燃烧室内液滴平均直径大于大气环境下的液滴平均直径,两者差值随着喷雾向下游发展而增大;模拟燃烧室对于液滴轴向速度影响较小,而对于液滴径向速度影响较明显。
In order to study the spray combustion characteristics of a small thrust liquid rocket engine combustion chamber, a small-scale simulation combustion chamber and a collisional jet nozzle were designed. Using a Doppler Phase Particle Dynamic Analyzer (PDA), the collision jet was observed in a small scale space Of the spray, focusing on the spray pressure on the atomization characteristics of the parameters of the impact. The experimental results show that the farther the distance between the measuring section and the nozzle is, the larger the average diameter of the droplet is and the smaller the axial velocity is. The farther the measuring point is from the central axis, the smaller the axial velocity of the droplet and the larger the radial velocity fluctuation The larger the spray pressure, the smaller the average droplet diameter, the greater the axial velocity. Due to the influence of the wall, the radial distribution of radial velocity is not obvious at different spray pressures and measurement points. The average diameter of the droplets in the simulated combustion chamber is larger than the average diameter of the droplets in the atmospheric environment, and the difference between the two With the development of the spray to the downstream increases; the simulated combustion chamber has little effect on the axial velocity of the droplet, but has obvious effect on the radial velocity of the droplet.