摘要
液体火箭发动机喷雾液滴在表面剪切力的作用下形成内部环流,影响液滴内部传热特性,进而影响喷雾蒸发燃烧过程。将一种基于光滑压力修正的非交错网格SIMPLE算法推广到一般曲线坐标系,并对液滴表面特殊边界条件进行数值处理,然后采用代数法生成正交贴体结构网格,求解气相及液相轴对称不可压流动控制方程,得到运动液滴内部稳态流场及其温度演化过程。仿真结果表明,运动液滴内部形成了稳定的内部环流;在初始传热阶段,液滴内部传热过程主要受热传导控制而形成对称的温度分布,但内部环流会随时间逐渐控制其传热过程,使内部温度不再服从对称分布,并在环流中心区出现局部低温。
Internal recirculation is formed in the liquid rocket spray droplet because of the surface tangent stress,which would influence the internal heat transfer of droplet greatly,and then the spray evaporation and combustion procedure.A smoothing pressure correction non-staggered SIMPLE algorithm is introduced into the curvilinear coordinates along with numerically processing for the special boundary condition of droplet surface,and then the axi-ymmetrical incompressible flow control equations of the gas and liquid phases were solved to obtain the steady velocity field and temperature evolvement basing on the orthogonal boundary-fitted structure cell generated by algebraic method.The simulation result shows that the steady recirculation appears inside the moving droplet.The temperature symmetrically distribution inside the droplet was dominated by the thermal conduction at the beginning of heat transfer,which would no longer symmetry distribute with a partial low temperature region in the recirculation center because of recirculation controlling heat transfer gradually.
出处
《导弹与航天运载技术》
北大核心
2011年第2期38-41,57,共5页
Missiles and Space Vehicles
基金
"973"项目(613102030101)
国家自然科学基金(50576105)
