电加热防/除冰过程中溢流水再冻结数值模拟  

Simulation of Electrothermal Anti-icing/Deicing Process Including Runback Water Ice Accretion

作　　者：刘小暄 朱春玲[1,2] 朱程香[1] 曹岩 LIU Xiaoxuan;ZHU Chunling;ZHU Chengxiang;CAO Yan(College of Aerospace Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空学院,南京210016 [2]南京航空航天大学航空航天结构力学及控制全国重点实验室,南京210016

出　　处：《南京航空航天大学学报》2024年第2期281-290,共10页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：当飞机飞行过程中遇到结冰工况时,为保证飞机的飞行安全以及气动性能,常使用热防护方法作为飞机防除冰的重要手段。本文通过使用共轭耦合方法建立了机翼内部多层导热与水膜流动的耦合计算模型,并针对电加热防除冰过程进行了一系列数值模拟计算。研究选取了可进行非稳态计算的Myers水膜模型,电加热组件导热模型则采用有限体积法隐式离散进行计算,水膜模型与导热模型通过交换边界值的共轭传热方法实现松耦合。研究发现在电加热防除冰过程中,由于积冰融化和水膜流动会产生溢流水再冻结现象。对电加热系统开启后期的积冰外形进行了流场计算与气动分析,发现机翼上下翼面溢流水冻结部位会对流场产生扰动。通过Q准则判断积冰后侧产生了涡结构,对比未发生结冰的干净翼型,机翼前缘位置溢流水冻结导致压力系数曲线发生较大震荡,因此溢流水再冻结问题影响了机翼的气动性能,未能使电加热防除冰系统达到理想的防护效果。The electrothermal anti⁃icing and deicing system is often used to ensure flight safety and aerody⁃namic performance when aircraft encounters icing conditions.This paper establishes a coupled calculation model of multi-layer heat conduction and water film flow by using the conjugate coupling method,and devel⁃ops a series of numerical simulation calculations for the electrothermal anti-icing and deicing process.Myers water film model is able to stimulate non-stationary calculations,while the internal thermal conductivity mod⁃el of the electrothermal component is implicitly discretized by using the finite volume method.The water film model and thermal conductivity model are loosely coupled through the conjugate heat transfer method by ex⁃changing boundary values.Research has found that during the process of electrothermal anti-icing,the phe⁃nomenon of runback water refreezing occurs due to the melting of ice accumulation and the flow of water film.A flow field calculation and aerodynamic analysis are conducted on the icing shape of the electrothermal sys⁃tem in the later stage.It shows that the frozen overflow water on the upper and lower wing surfaces of the wing will cause disturbance to the flow field.The Q-criterion is used to determine the vortex structure behind the icing.Compared with clean airfoils without icing,the freezing of runback water at the leading edge of the wing causes significant oscillations in the pressure coefficient curve.Therefore,the problem of refreezing run⁃back water affects the aerodynamic performance of the wing,which leads to the undesired protective effect of the electrothermal system.

关 键 词：飞机防/除冰 电加热防除冰 耦合传热 非稳态导热 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]