基于流-固耦合传热的热气防冰系统干空气飞行蒙皮温度场计算研究

以机翼热气防冰系统为研究对象,建立了包含热气防冰系统防冰腔内外流场对流换热和固体结构导热的三维稳态流-固耦合传热物理模型,对整个计算区域生成混合网格,边界条件为第三类边界条件,采用计算流体力学方法以 FLUENT 软件为工具,对干空气飞行状态下流-固耦合传热模型进行了求解,获得防冰腔蒙皮内外表面对流换热系数分布和温度场结果,并对计算结果进行了分析。结果表明：防冰腔铝合金蒙皮沿展向和厚度方向导热显著,温度分布较均匀,防冰引气温度为200℃时,防冰腔蒙皮内外表面上最高温度为101℃,最低温度为21℃,3 mm厚的蒙皮同一点处内外表面最大温差仅为4℃,防冰腔排气口处气体的平均温度为63℃。热气防冰系统蒙皮温度场计算方法和计算结果,能够为热气防冰系统干空气飞行试验设计和测试中温度传感器的选型与布置提供依据。

Numerical study of skin temperature field on hot air anti-icing system in dry air flight based on fluid-solid coupled heat transfer

The physical and mathematical models for three-dimensional steady fluid-solid coupled heat transfer were presented for wing hot air anti-icing system.These models simulate the effects of internal and external heat transfer as well as thermal conductivity of solid structure on aircraft leading edge skin.Hybrid grid was generated for the entire computational domains. The third kind of boundary conditions was used for the present simulations.Internal and external skin temperature field for fluid-solid coupled heat transfer under dry air flight condition were solved by computational fluid dynamic method with FLUENT tool,and the calculated results were analyzed. The results indicate that heat conducting is significant along leading edge spreading and thickness direction on aluminium alloy skin,temperature distributions on the skin are uniform.When the temperature of inlet bleed air is 200 ℃,the maximal surface temperature of skin on anti-icing system is 101 ℃,the minimal surface temperature is 21 ℃,the maximal temperature difference between the inside and outside surface is only 4 ℃ for 3 mm thick skin,the average temperature of exhaust is 63 ℃. The present method and calculated results of temperature field can provide support for the dry air flight test design of hot air anti-icing system and reasonable choosing and distributing temperature sensors.