飞机短舱加热表面水膜流动分布的数值研究  

Numerical Study of Water Film Flow Distribution on the Heating Surface of Aircraft Nacelle

作　　者：马鸿 MA Hong(Shaanxi Polytechnic Institute,Xianyang 712000,China)

机构地区：[1]陕西工业职业技术学院,陕西咸阳712000

出　　处：《河南科技》2023年第7期28-32,共5页Henan Science and Technology

基　　金：陕西工业职业技术学院2021年自然科学类科研项目“涡轮导向器叶片表面侵蚀及性能影响研究”(2021YKYB-054)。

摘　　要：【目的】通过对飞机发动机短舱加热除冰时表面水膜的流动状况进行分析,为飞机短舱防冰热系统的设计提供参考。【方法】本研究以某型飞机短舱为研究对象,并基于欧拉-拉格朗日框架,采用离散模型(DPM)来建立水膜流动过程的数学模型,对短舱加热表面溢流水的溢流范围和水膜厚度变化情况进行分析。【结果】研究发现,短舱加热表面的水膜厚度呈现出先增大后减小的流动规律,水膜厚度最大为80μm。同时,对比水滴的撞击极限位置,短舱加热表面水膜的溢流范围最大为32%。【结论】受气流驱动,短舱表面水膜出现溢流的现象,研究结果对飞机短舱防冰热系统的设计具有重要参考价值。[Purposes]The flow of water film on the surface of aircraft engine nacelle during heating and de-icing is analyzed to provide reference for the design of aircraft nacelle anti-icing thermal system.[Methods]In this study,a certain type of aircraft nacelle was taken as the research object.Based on the Euler-Lagrangian framework,a discrete model(DPM)was used to establish a mathematical model of the water film flow process.The overflow range and water film thickness of the nacelle heating surface were analyzed.[Findings]It was found that the water film thickness on the heating surface of the nacelle increased first and then decreased,and the maximum water film thickness was 80μm.At the same time,compared with the impact limit position of water droplets,the maximum overflow range of water film on the heating surface of the nacelle is 32%.[Conclusions]Driven by airflow,the water film on the nacelle surface overflows.The research results have important reference value for the design of aircraft nacelle anti-icing thermal system.

关 键 词：水膜流动 溢流水 数值模拟 UDF 

分 类 号：V233.94[航空宇航科学与技术—航空宇航推进理论与工程]