某型飞机发动机短舱热气防冰系统性能数值模拟

摘要

A three-dimensional numerical simulation method with internal-external tight coupled heat transfer is developed to analysis the performance of an engine nacelle hot-air anti-icing system.Effect of engine inlet air mass flow rate on the skin temperature is also analyzed.A three-dimensional Computational Fluid Dynamic (CFD)method is applied to attain the heat transfer coefficient on both side of skin,and an inverse distance weighting algorithm is presented for the interpolation of data exchange between internal and external meshes.The local water collection coefficient on the engine nacelle,the distribution of the surface temperature and the runback water mass flow rate on the surface are obtained to determine.The simulation results indicate that this anti-icing system meets the requirement,the skin temperature decreases and the runback water mass flow rate increases as the engine inlet air mass flow rate rising.%使用三维内外强固传热耦合方法计算校核发动机短舱热气防冰系统的性能,并分析发动机进气流量对蒙皮表面温度的影响.内、外部表面传热系数计算均采用纯三维的CFD方法,在内、外部网格数据交互时使用了距离加权反比插值法.通过计算获得发动机短舱的局部水收集系数、蒙皮表面温度的分布情况、各处溢流水量,并由此判定此防冰系统性能是否达到要求.分析表明此发动机短舱热气防冰系统符合防冰性能要求;当发动机进气流量增大时,蒙皮表面温度下降,且溢流水量增加.