考虑周期性溢流水边界的三维热气防冰系统表面温度计算  

Surface Temperature Calculation of 3D Hot-Air Anti-lcing System Considering Periodic Runback Water Boundary

作　　者：黄平 卜雪琴[1] 李伟斌[2] 曾腾辉 王柳 林贵平[1] Huang Ping;Bu Xueqin;Li Weibin;Zeng Tenghuis;Wang Liu;Lin Guiping(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;AVIC Computation Aerodynarnics Institute,China Aerodynarmics Research and Development Center,Mianyang 621000,China;AVIC Wuhan Aviation instrurment Corporation Ltd.,Wuhan 430074,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国空气动力研究与发展中心计算空气动力研究所,四川绵阳621000 [3]航空工业武汉航空仪表有限责任公司,湖北武汉430074

出　　处：《气动研究与试验》2025年第1期16-23,共8页Aerodynamic Research & Experiment

摘　　要：热气防冰系统表面温度是衡量防冰系统性能的重要指标。本文采用松散耦合计算热气防冰系统表面温度,在机翼防冰热载荷和防冰腔内部对流换热计算的基础上,分析机翼蒙皮表面的内外耦合传热过程,得到机翼防冰区域的温度和溢流水分布。提出了一种周期性溢流水边界,改进了现有的松散耦合计算热气防冰系统表面温度的方法。该周期性边界考虑展向相邻防冰区域的影响,避免了由于机翼后掠角导致的蒙皮表面溢流水流入边界设置不合理的问题。研究表明,周期性溢流水边界条件对湿态防冰工况的计算结果影响很大,溢流水区域的表面温度会显著降低,更接近实际防冰系统工作状态。本文方法可为机翼热气防冰系统设计和校核提供一定参考。Surface temperature is an important index to measure the performance of hot-air anti-icing system.The surface temperature of the hot-air anti-icing system is calculated by using loose coupled method.Based on the calculation of the anti-icing heatload of the wing and the convective heat transfer in the anti-icing chamber,the coupled heat transfer process of the wing skin is analyzed,and the distributions of temperature and runback water in the anti-icing area of the wing are obtained.On this basis,a periodic runback flow boundary is proposed to improve the existing loose coupled method for calculating the surface temperature of hot-air anti-icing system.The periodic boundary takes into account the influence of adjacent anti-icing area in spanwise direction and avoids the problem of unreasonable boundary setting of runback flow on skin surface caused by sweep back angle of wing.The results show that the boundary conditions of periodic runback flow have a great influence on the calculation results of wet anti-icing conditions,and the surface temperature in the runback flow area is significantly reduced,which is closer to the actual working state of the anti-icing system.The method presented in this paper can provide some reference for the design and checking of wing hot-air anti-icing system.

关 键 词：机翼 热气防冰系统 内外传热耦合 溢流水周期边界 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]