摘要
为研究辅助动力装置(APU)排气系统的冷却空气引射孔、引射缝以及飞机后整流罩形状等对冷却效果的影响,采用商业CFD软件Fluent,选用realizable k-ε湍流模型和DO热辐射模型建立了13个有不同引射孔位置、引射缝尺寸和飞机尾罩形状的排气系统流动和传热数值计算模型,得到了流场、温度场和热流分布。计算结果表明,冷却空气引射缝大小、引射孔的位置与形状面积以及后整流罩形状对APU排气系统的气膜冷却效果有重要影响。
To study the influence on cooling effectiveness of APU＇s cooling air injection holes and injection slots and the shape of the plane tail fairing,13 numerical computation models with different injection hole locations and slot sizes and different plane tail fairing shapes are setup by using commercial CFD software Fluent and incorporating the realizable k-ε turbulent model with the DO thermal radiation model,to calculate flow and heat transfer in the APU exhaust system.The flow field,temperature field and heat flow distribution are acquired.The calculation results show that the size of cooling air injection slot,the location,shape and area of injection hole,and the shape of tail fairing play important roles in the cooling system.
出处
《沈阳航空航天大学学报》
2012年第1期6-10,共5页
Journal of Shenyang Aerospace University
关键词
辅助动力装置
排气引射
温度
气膜冷却
数值计算
auxiliary power unit（APU）
exhaust gas injection
temperature
film cooling
numerical computation
