发动机短舱过冷大水滴结冰数值模拟  

Numerical Simulation of Engine Nacelle Icing under Supercooled Large Droplet Conditions

作　　者：曹宇 王正之[1] 朱春玲[1] CAO Yu;WANG Zheng-zhi;ZHU Chun-ling(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《航空计算技术》2019年第1期59-63,共5页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(51806105;11832012);国家重点基础研究发展计划(973计划)基金项目资助(2015CB755800)

摘　　要：发动机短舱结冰会对飞机飞行安全造成重大影响。过冷大水滴在撞击物面前存在变形、破碎,撞击时可能出现飞溅、反弹等物理现象,与过冷小水滴存在差异。为更好地模拟过冷大水滴条件下发动机短舱结冰情况,建立了考虑水滴破碎、飞溅、反弹等影响的过冷大水滴运动模型,对某型发动机短舱进行了结冰数值模拟,并研究了边界条件、水滴直径等对结冰外形的影响。计算结果表明,水滴直径越大,局部水收集系数越大,水滴上下撞击极限越大,结冰越厚。短舱风扇处不同边界条件设置对过冷大水滴结冰结果存在影响,边界条件为压力出口和流量出口时计算结果吻合度较高。Engine nacelle icing would do major impact on aircraft flight safety.Supercooled large droplets(SLD)may deform and break before impacting on the wall,and physical phenomena such as splashing and rebound may occur during the process of impact,which is different from the supercooled small droplets.In order to simulate nacelle icing more precisely under SLD conditions,this paper established a model of supercooled large droplets considering the effects of droplet breaking,splashing,rebound,etc.,and a certain type of engine nacelle′s icing was simulated numerically while the influence of boundary conditions and droplet diameter on the shape of ice was studied.The results showed that the larger diameter of the droplet,the larger local water collection coefficient,the greater upper and lower impact limit,and the thicker ice.Different boundary conditions at the fan of the nacelle have influence on the icing results.The results are in good agreement when the outlet conditions are set as pressure outlet and mass outlet.

关 键 词：结冰 发动机短舱 过冷大水滴 边界条件 数值模拟 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]