超声速气流中液体横向射流雾化过程数值模拟

为了更加深入了解超燃冲压发动机燃烧室中的燃料雾化机理，对来流Mach数为1.94的超声速气流中液体横向射流的雾化过程进行了数值模拟研究.计算采用Euler-Lagrange方法，液滴二次破碎模型采用K-H/R-T模型.计算结果表明:考虑液滴二次破碎时，采用雾化锥模型获得的射流穿透深度以及液滴速度分布与实验结果符合得很好；初始液滴直径对射流穿透深度和液滴分布的影响很小；随着初始雾化锥角的增加，相同横截面上的射流穿透深度逐渐减小.当不考虑液滴二次破碎时，液滴穿透深度及分布与所选的初始液滴直径有很大关系. 

Numerical Simulation of Atomization of Liquid Jet in Supersonic Cross Flow

In order to further understand the fuel atomization mechanism in scramjet combustor, the atomization of cross liquid jet in a Ma=1.94 supersonic flow was investigated numerically. Euler-Lagrange method was used for calculation, and K-H/R-T model was used for secondary breakup. The calculation results reveal that when secondary breakup is considered, the spray penetration depth and distribution of droplet velocity obtained by spray cone model agree well with the experimental results. The initial droplet diameter has little effect on the spray penetration depth and droplet distribution. With the increase of the initial spray cone angle, the spray penetration depth on the same cross section decreases gradually. When secondary breakup is not considered, the spray penetration depth and droplet distribution are greatly related to the initial droplet diameter.