冷壁上单个静止过冷液滴冻结过程的数值模拟  

Numerical Simulation of Freezing Process of a Sessile Supercooled Water Droplet on a Cold Wall

作　　者：张旋[1] 吴晓敏[1] 闵敬春[2] 

机构地区：[1]清华大学热能工程系热科学与动力工程教育部重点实验室,北京100084 [2]清华大学航天航空学院工程力学系热科学与动力工程教育部重点实验室,北京100084

出　　处：《工程热物理学报》2018年第1期159-164,共6页Journal of Engineering Thermophysics

基　　金：国家重点基础研究发展计划(973计划)项目(No.2015CB755800)

摘　　要：以飞机飞行过程中过冷液滴撞击飞机表面所发生的结冰现象为背景,数值研究冷壁上单个静止过冷液滴的冻结过程。考虑重力作用下液滴的变形,并将过冷液滴冻结过程中成核再辉阶段的影响转化为物性参数的变化和模拟的初始条件,基于Fluent凝固/融化模型,模拟单个静止过冷液滴的冻结过程,模拟所得液滴冻结过程与文献中的实验结果吻合良好,最终冻结时间偏差为12.5%。进一步研究过冷度、壁面接触角、来流速度对过冷液滴冻结过程的影响,结果表明:过冷度越大,壁面接触角越小,来流速度越大,过冷液滴冻结越快,最终冻结时间越短,为研究飞机结冰机理提供参考。When supercooled droplets in phenomena may occur. The freezing process is therefore numerically investigated. The clouds impinge and stick on aircraft in flight, icing of a sessile supercooled water droplet on a cold surface simulations consider the gravity effect on the droplet shape and include the recalescence stage effect on the droplet freezing by adjusting the droplet physical properties and the simulation initial conditions. Calculations are performed based on the solidification/melting model in Fluent. The numerically calcula.ted droplet freezing process agrees well with the experimental observation in the literature and the difference in the final freezing time is 12.5%. Further calculations are made to investigate the influences of supercooling degree, contact angle and airflow velocity on the freezing process, and the results show that greater supercooling degree, smaller contact angle and larger airflow velocity lead to faster freezing and shorter final freezing time, which may provide a reference for in-depth studies on aircraft icing.

关 键 词：结冰 相变 过冷液滴 冻结 数值模拟 

分 类 号：TK124[动力工程及工程热物理—工程热物理]