某型飞机发动机短舱热气防冰系统性能数值模拟  

Numerical simulation of the performance of an engine nacelle hot-air anti-icing system

作　　者：郁嘉[1,2] 赵柏阳 卜雪琴[1] 林贵平[1] 李志茂[4] 

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]航空科学技术国家实验室,北京100191 [3]中航工业第一飞机设计研究院,陕西西安710089 [4]上海飞机设计研究院环控氧气部,上海201203

出　　处：《空气动力学学报》2016年第3期302-307,共6页Acta Aerodynamica Sinica

摘　　要：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。A three-dimensional numerical simulation method with internal-external tightcoupled heat transfer is developed to analysis the performance of an engine nacelle ho--air antiicingsystem. Effect of engine inlet air mass flow rate on the skin temperature is also analyzed. Athree-dimensional Computational Fluid Dynamic （CFD ） method is applied to attain the heattransfer coefficient on both side of skin, and an inverse distance weighting algorithm is presentedfor the interpolation of data exchange between internal and external meshes. The local watercollection coefficient on the engine nacelle, the distribution of the surface temperature and therunback water mass flow rate on the surface are obtained to determine. The simulation resultsindicate that this anti-icing system meets the requirement？ the skin temperature runback water mass flow rate increases as the engine inlet air mass flow rate rising.

关 键 词：发动机 热气防冰系统 表面温度 发动机进气流量 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V244.15