Temperature and Runback Ice Prediction Method for Three-Dimensional Hot Air Anti-Icing System

2016 2nd International Conference on Mechanical and Aeronautical Engineering (ICMAE 2016)

机械制造;航空航天工程

Zhou, Ying^1 ; Lin, Guiping^1 ; Bu, Xueqin^1 ; Mu, Zuodong^1 ; Pan, Rui^1 ; Ge, Qimo^2 ; Qiao, Xudong^2

School of Aeronautic Science and Engineering, Beihang University, Beijing

100191, China^1

Jiangxi Hongdu Aviation Industry Group Corporation Limited, AVIC, Nanchang, Jiangxi

330024, China^2

关键词: Computational approach;    Convective heat transfer Coefficient;    Droplet collection efficiency;    External conditions;    Hot-air anti-icing systems;    Prediction methods;    Surface temperature changes;    Surface temperatures;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/187/1/012017/pdf
DOI  :  10.1088/1757-899X/187/1/012017

学科分类：航空航天科学

来源: IOP

【 摘 要 】

A prediction method of surface temperature and runback ice for a three-dimensional hot air anti-icing system was proposed. Computational approach to realize this method was introduced. Both the external and internal flows were separately calculated, results of which were set as boundary conditions of heat conduction computation in airfoil skin. The results of external and internal flow calculations show that the effect of surface temperature on convective heat transfer coefficients and local droplet collection efficiency is negligible and the calculations can be decoupled. The prediction method based on heat flux was used to calculate surface temperature and runback ice results. The results show that, the effects of LWC and Mach number are much more significant than the effect of external flow temperature. The surface temperature at impinging interaction point is more sensitive to the change of external conditions than that at stagnation point. The surface temperature changes significantly with changing Mach number because both the mass rate of droplet and the impact limit are changed.