发动机舱通风冷却和遮挡隔热综合降温效果  

Conjugated Action of Ventilation-Shelter-Insulation on Reducing Skin Temperature of Engine Nacelle

作　　者：王杏涛[1] 张靖周[1] 单勇[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2013年第5期652-657,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：对某型发动机舱进行二维结构简化,通过数值计算的方法,研究了发动机舱通风冷却、辐射遮挡和隔热层等对发动机舱蒙皮的冷却降温效果。在发动机舱冷却流量0.1～1.0kg/s范围内,通过增加通风冷却流量虽能取得一定的壁面降温效果,但并不显著;加装辐射遮挡板能够有效地降低发动机壁面对发动机舱蒙皮的辐射加热,在发动机舱中部具有显著的降温效果;在发动机舱蒙皮内侧加隔热层能够有效提高导热热阻,在发动机舱尾部的降温效果显著;综合采用通风冷却、辐射遮挡及隔热层等措施能够大幅度降低发动机舱蒙皮外表面的温度,使其接近环境温度。A two-dimensional model for a certain engine nacelle is simplified,and a numerical simulation for the flow and heat transfer process inside engine nacelle is carried out to illustrate the conjugated action of ventilation cooling,radiation shelter and thermal insulation on reducing skin temperature of engine nacelle.The skin temperature decreases with the increase of the ventilation air flow,but the individual action is not significant when the ventilation flowmate varies from 0.1 kg/s to 1.0 kg/s.Radiative heating of the engine wall to internal skin surface can be reduced effectively by setting radiation shelter,resulting in obvious reduction of skin temperature in the middle section of nacelle.The additional thermal insulation layer on the inside of engine nacelle will increase heat conduction resistance,resulting in skin temperature reduction in overall length,especially significant near trailing edge of nacelle.By using a combination of ventilation cooling,radiation shelter and thermal insulation layer,the skin temperature can be decreased close to ambient temperature.

关 键 词：发动机舱 通风冷气 辐射遮挡 隔热层 表面降温 

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]