涡扇型发动机舱温度场分析  

Analysis of Temperature Field in Nacelle for a Turbofan Engine

作　　者：王玉梅[1] 陈战斌[1] 李丽[1] 

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《工程与试验》2015年第3期35-37,50,共4页Engineering and Test

摘　　要：以采用加力涡扇型发动机的飞机短舱为研究对象,对舱内的热环境进行分析。根据发动机炽热部位的壁面温度和短舱内典型截面的环境温度的分布规律,对发动机状态、舱内冷却条件、太阳辐射等因素对短舱内的冷却性能的影响进行了总结,可为采用涡扇型发动机的通风冷却系统的设计鉴定提供技术指导。The nacelle of a turbofan engine is taken as the research object,and the temperature environment of nacelle is analyzed.According to the wall temperature of engine and temperature distribution in the typical section of nacelle,the influences of factors such as engine condition,cooling conditions and solar radiation on the cooling performance of engine nacelle are summarized,which can be used for the design of the ventilation and cooling system of the nacelle for turbofan engine.

关 键 词：通风冷却系统 涡扇发动机 温度 飞行试验 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]