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直流自击式喷嘴广泛应用于液体火箭发动机喷注器,但对于其雾化机理及特性的研究基本上都是建立在冷态试验和发动机热试车的基础之上。从喷嘴射流的受力分析着手,建立了射流破碎的物理模型,计算中考虑了影响该型喷嘴雾化特性的主要因素,并与相关实验结果进行了对比分析,说明了该物理模型具有一定的参考价值。该模型可以在燃烧流场计算时作为雾化初始条件使用。
DC self-propelled nozzles are widely used in liquid rocket motor injectors, but their atomization mechanism and characteristics are basically based on cold test and engine thermal test. Starting from the force analysis of the nozzle jet, the physical model of the jet broken is established. The main factors that affect the atomization characteristics of the nozzle are taken into account in the calculation. The comparative analysis of the experimental results with the experimental results shows that the physical model has a certain Reference value. The model can be used as initial conditions of atomization in the calculation of combustion flow field.