摘要
为探究液气动量比对内混式直流气液喷嘴雾化特性的影响,采用基于Gerris的VOF方法和自适应加密算法,对不同液气动量比下的两液相孔内混式直流气液喷嘴雾化过程进行数值计算。结果表明:Gerris可以清晰地捕捉到射流柱从变形、弯曲到雾化为液滴的全过程细节特征,雾化过程图像与实验拍摄的基本吻合,获得液滴空间分布,计算得到的全场液滴SMD为50~60μm。当液气动量比较小时,内混式直流气液喷嘴的射流不发生相撞,雾化机制为气动破碎。随着液气动量比的增加,两股射流破碎长度和穿透深度均增大,射流发生相撞,雾化机制为气动破碎和撞击破碎。
In order to research the effects of liquid-gas momentum ratio on atomization characteristics of internal mixing gas-liquid injector, the internal mixing gas liquid injector with two jet holes was numerically computed under various liquid-gas momentum ratio by the VOF method and adaptive mesh refinement algorithm based on Gerris.The results show that the characteristics of the whole spray process are captured accurately in Gerris, which consists of column distortion,bending and disintegrating into droplets.The computational results are basically in good agreement with the breakup process images in experiment.The spatial distributions of droplets were obtained and the droplets SMD of full flow field is 50~60 μm. When liquid-gas momentum ratio is small, the liquid jets of internal mixing gas liquid injector do not collide with each other, and the atomization mechanism is pneumatic atomization.With the increase of the liquid-gas momentum ratio, two liquid jets’ breakup length and penetration depth are increased, and liquid jets collide, at that time atomization mechanism is pneumatic atomization and impact atomization.
作者
杨国华
张波涛
周立新
王凯
YANG Guohua;ZHANG Botao;ZHOU Lixin;WANG Kai(Science Technology on Combustion, Internal Flow and Thermal-structure Laboratory,Northwestern Polytechnical University,Xi'an 710072, China;Science and Technology on Liquid Rocket Engines Laboratory,Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)
出处
《火箭推进》
CAS
2019年第5期66-73,共8页
Journal of Rocket Propulsion
基金
国家重大基础研究项目(613193)
