基于内外传热耦合的热气防冰系统仿真计算  

Simulation calculation of hot air anti-icing system based on internal-external comjugate heat transfer

作　　者：郭涛[1,2] 林丽[2] 朱程香[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]中国航空工业集团公司第一飞机设计研究院,西安710089

出　　处：《航空动力学报》2016年第11期2621-2627,共7页Journal of Aerospace Power

摘　　要：基于内外传热耦合原理,建立了热气防冰系统的AMESim仿真模型,研究热气防冰系统在不同引气状态下,管路流量、压力及蒙皮温度的变化规律.采用所建立的仿真方法,计算飞机机翼热气防冰系统的内部流动特性和内外耦合传热特性,将计算结果与热气防冰系统流量分配试验结果进行对比.结果表明:管路流量、压力和蒙皮温度的仿真计算结果与试验结果最大误差为9%,验证了该仿真模型的正确性.在此基础上,对飞机短舱热气防冰系统进行了仿真,分析了飞行包线下系统内外的换热、温度变化、加热效率等关键参数的瞬态特性.仿真结果为热气防冰系统的设计、分析与优化提供依据.Based on the principle of conjugate heat transfer between the external and internal chamber,AMESim simulation model was established for the hot air anti-icing system.The change rules of the flux,pressure and skin temperature in different bleeding conditions were researched.The internal flow characteristics and the conjugate heat transfer characteristics of the aircraft wing anti-icing system were calculated using this model.The predictions of the flux,temperature and pressure were verified against those in the flow distribution experimental data of the wing anti-icing system,showing a satisfactory agreement.The maximum error was less than 9%.Its accuracy and validity were validated with the comparison of results.On the basis of modeling,a nacelle hot air anti-icing system was simulated.The transient characteristics of key parameters under a certain flight envelop,such as the heat flux,temperature and heating efficiency,were analyzed.The results can be provided as a reference for design,analysis and optimization of hot air anti-icing system.

关 键 词：热气防冰系统 传热耦合 防冰腔 瞬态特性 AMESim仿真模型 

分 类 号：V244.1[航空宇航科学与技术—飞行器设计]