空气动力学学报2016，Vol.34Issue(3)：302-307,6.DOI:10.7638/kqdlxxb-2015.0212
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
郁嘉 1赵柏阳 2卜雪琴 3林贵平 1李志茂1
作者信息
- 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
- 折叠
摘要
Abstract
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.关键词
发动机/热气防冰系统/表面温度/发动机进气流量Key words
engine/hot-air anti-icing system/surface temperature/engine inlet air mass flux分类
航空航天引用本文复制引用
郁嘉,赵柏阳,卜雪琴,林贵平,李志茂..某型飞机发动机短舱热气防冰系统性能数值模拟[J].空气动力学学报,2016,34(3):302-307,6.
