发动机舱内部传热和蒙皮的降温规律  

Internal heat transfer and skin temperature reduction law of engine nacelle

作　　者：王杏涛[1] 张靖周[1,2] 单勇[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第5期1121-1126,共6页Journal of Aerospace Power

摘　　要：建立了简化的发动机舱物理模型,对通风冷却和辐射遮挡的蒙皮降温效果进行了数值模拟和实验研究,并对发动机舱内部传热规律进行了分析.结果表明:数值计算得到的发动机舱蒙皮表面沿程分布与实验结果吻合良好.在加热壁面分段的热边界条件下,无辐射遮挡且无通风时蒙皮内侧表面接受的热流占热壁面加热热流的比值约为78%,当发动机舱通风速度达到1m/s时该比值降至20%;当通风速度从0m/s增大至3.5m/s时,发动机舱蒙皮峰值温度的降幅约为10%;无通风条件下有辐射遮挡的蒙皮峰值温度相对于无辐射遮挡的情形降幅约为6%;在通风冷却和辐射遮挡的综合作用下,蒙皮峰值温度相对于无通风且无辐射遮挡的基准状况可降低约50K,相对降幅约为14%.A simplified physical model of engine nacelle was established. The effects of ventilation cooling and radiation shelter on reducing skin temperature were investigated by numerical simulation and experimental research. The internal heat transfer of the engine na- celle was also analyzed. Results show that the computational temperature distribution on the skin surface is in good accordance with the experimental result. Under the present zonal thermal boundary conditions of the heated wall, the ratio of total heat flux imposing on the inner surface of skin to the heat flux of heated wall is about 78% in case of no ventilation and radiation shelter. This ratio reduces to 20% when the ventilating velocity of the engine na-celle is 1 m/s. When the ventilating velocity is increased from 0 m/s to 3.5 m/s, the maxi- mum temperature on the skin is reduced about 10% relatively. The maximum temperature on the skin with radiation shelter is reduced about 6 % in relative to the case without radiation shelter under no ventilation condition. Combination of ventilation and radiation shelter can achieve 50K reduction of maximum skin temperature in relative to the case of no ventila tion and radiation shelter, with about 14 % relative reduction.

关 键 词：发动机舱 通风冷却 辐射遮挡 传热分析 降温规律 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]