Numerical Study Of Kerosene's Spray In Supersonic Cross Flow

Fuel's atomization has an important effect on the scramjet. The quality of atomization makes great contribution to the efficiency of scramjet engine.In supersonic cross flow, fuel's breakup time is very short.This cause some difficulties for experiment.Numerical method can show the detail of the flow field, and show the particle's distribution which is difficult for experiment.So it's necessary to invest fuel's atomization in supersonic cross flow with numerical method.KH/RT break up model is used by the numerical study of kerosene's spray in supersonic cross flow. KH/RT breakup model is consists of KH breakup model and RT breakup model.KH breakup model is based on Reitz's dispersion equation which was proposed in 1987.The hydrodynamic boundary conditions were simplified in Reitz's dispersion equation.Which will effect KH breakup model.In this paper,we will modified the traditional KH breakup model according to Li's dispersion,which was proposed in 1995.Firstly, we get the numerical solution of Li's dispersion equation.And analysed the infulence of gas-liquid density ratio?liquid webber number and ohnesorge number to dispersion equation's numerical solution.The results shows that:The maximum wave growth rate is increased with gas-liuid density ratio and liquid webber number.The maximum was decreased when ohnesorge number increased.Then we modified the traditional KH breakup model according to the maximum wave growth rate and dominate wave number.We simulated water's breakup in supersonic cross flow with OpenFOAM.We found that the modified KH breakup model works better than traditional KH breakup model.At last,we simulated kerosene's atomization in supersonic cross flow. The result shows that the penetration depth increased with injector orifice diameter and jet-to-freestream momentum flux ratio.Near the orifice area,the lower jet-to-freestream momentum flux ratio,the more widely distribution of the particle in spanwise direction.Otherwise,the particle's distribution in spanwise direction increased with jet-to-freestream momentum flux ratio.