Effects of flow parameters on thermal performance of an inner-liner anti-icing system with jets impingement heat transfer  

作　　者：Zhiqiang GUO Mei ZHENG Qian YANG Xiaofeng GUO Wei DONG 

机构地区：[1]School of Mechanical Engineering,Shanghai Jiaotong University,Shanghai 200240,China

出　　处：《Chinese Journal of Aeronautics》2021年第9期119-132,共14页中国航空学报（英文版）

基　　金：co-supported by the National Numerical Wind Tunnel Project(No.NNW2018-ZT2B04);the “973”Program of China(No.2015CB755800)。

摘　　要：The multiple jets impingement heat transfer is widely applied in the wing anti-icing system.It is challenging to apply the similarity criterion to carry out the anti-icing experiments due to the complex flow and heat transfer behavior.In the present study,the full-scale slat model is used to carry out anti-icing experimental researches in a 2 m×3 m icing wind tunnel of China Aerodynamics Research and Development Center.The effects of icing parameters Liquid Water Content(LWC)and Median Volume Diameter(MVD)and hot air parameters(mass flow rate and temperature)on the thermal performance of an inner-liner anti-icing system with jets impingement heat transfer are studied.The effects of the experimental parameters are analyzed in detail by combining impingement and evaporation heat transfer mechanisms.The impingement hot air mass flow rate dramatically affects the heat transfer performance of the impingement stagnation region within the range of the experimental parameters.The temperature of impingement hot air and that of wing skin are approximately linear correlated.The experimental results show the effects of LWC and MVD on water film formation and runback ice accretion.The formation of water film is analyzed by an analytical method based on the wing skin temperature difference of dry and wet air conditions.

关 键 词：Hot air anti-icing system ICING Icing wind tunnel Jets impingement heat transfer Thermal performance 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]