短舱进气道热气防冰系统传热特性研究  

Heat Transfer Characteristic Investigation of Nacelle Inlet Hot Air Anti‑icing System

作　　者：秦娜 冯丽娟 尹金鸽 郑梅 QIN Na;FENG Lijuan;YIN Jinge;ZHENG Mei(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海200241

出　　处：《南京航空航天大学学报》2023年第2期274-281,共8页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家科技重大专项(J2019-Ⅲ-0010-0054)。

摘　　要：为了研究短舱笛形管热气防冰系统中防冰腔设计参数对进气道唇口表面传热特性的影响,进行了不同设计参数下进气道防冰腔内外流域和固体域的耦合仿真传热计算。分析得出了不同射流孔孔径和射流孔到进气道前缘表面的距离等参数对进气道唇口表面的温度、对流换热系数和Nusselt(Nu)数分布的影响。分析结果表明:射流孔直径和射流孔到唇口表面距离在一定的范围内,进气道蒙皮表面温度和对流换热系数随射流孔直径的增大而升高,随中间排射流孔到唇口表面距离的减小而升高。To investigate the influence of design parameters of anti-icing chamber of hot air anti-icing systems of piccolo tube on heat transfer characteristics of inlet lip skin,coupled simulation of internal and external flow of anti-icing chamber and solid domain under different parameters are conducted.The impact of different design parameters such as hole diameter,vertical distance between holes and lip skin on temperature,convection heat transfer coefficient and Nusselt(Nu)number distribution of inlet lip skin lower surface are obtained.The results show that while the values of hole diameter and vertical distance between holes and lip skin are within a certain range,the temperature of inlet lip skin and convection heat transfer coefficient increase with the increase of jet hole diameter and with the decrease of distance between middle row holes and lip skin.

关 键 词：短舱进气道 热气防冰系统 笛形管设计参数 传热特性 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]