埋入式冲压空气进气口性能及影响因素研究  

Research on performance and influencing factors of submerged ram air inlet

作　　者：孔犇犇 裴后举 崔永龙 李志茂[3] 蒋彦龙[1] KONG Benben;PEI Houju;CUI Yonglong;LI Zhimao;JIANG Yanlong(Key Laboratory of Aircraft Environment Control and Life Support,MIIT,Nanjing University of Aeronautics and Astronautics,210016 Nanjing,China;Marine Design&,Research Institute of China,200011 Shanghai,China;Environment Control and Oxygen System Department,Shanghai Aircraft Design and Research Institute,201210 Shanghai,China)

机构地区：[1]南京航空航天大学飞行器环境控制与生命保障工业和信息化部重点实验室,南京210016 [2]中国船舶及海洋工程设计研究院,上海200011 [3]上海飞机设计研究院环控氧气部,上海201210

出　　处：《应用力学学报》2022年第3期490-497,共8页Chinese Journal of Applied Mechanics

基　　金：飞行器环境控制与生命保障工信部重点实验室开放课题资助项目(No.KLAECLS-E-202001)。

摘　　要：随着高性能航空电子设备在飞机上的大量应用,冷却空气需求量的不断增加,亟需发展高效节能的民机冲压空气系统。针对某飞机NACA型进气口,建立其物理模型并基于k-ωSST湍流模型开展其内外流场的耦合特性分析,研究了NACA埋入式进气口的进气机理。在此基础上,提出了采用反映进气口气流能量损失的关键性指标冲压效率及进气质量流量作为进气口性能的评价方法,并分析了飞行参数如马赫数、攻角和侧滑角对NACA埋入式进气口性能的影响。研究结果表明:马赫数从0.5增加到0.9时,冲压效率增加了9.26%,质量流量增加3.82 kg/s;攻角从0°增加到5°时,冲压效率增加了7.35%,质量流量增加0.38 kg/s;侧滑角从0°增加到4°,冲压效率降低6%,而质量流量呈先增大后减小的趋势。研究结果为我国大型民用飞机的自主研制提供一定的理论依据。The demand for cooling air is continuously increasing as a result of the extensive application of high-performance avionics in aircraft.Therefore,it is urgent to develop an efficient and energy-saving ram air system for civil aircraft.Based on k-ωSST turbulence model,the coupling characteristics of internal and external flow fields of aircraft NACA inlet were studied,and the intake mechanism of NACA inlet was obtained.On this basis,the evaluation method and index of inlet performance were proposed,and the influences of flight parameters such as Mach number,angle of attack and side-slip angle on aircraft NACA inlet performance were studied.The results show that the ram efficiency and the mass flow rate increase by 9.26%and 3.82 kg/s,respectively when Mach number increases from 0.5 to 0.9.As the angle of attack increases from 0°to 5°,the ram efficiency and the mass flow rate increase by 7.35%and 0.38 kg/s,respectively.The side-slip angle increases from 0°to 4°,and the ram efficiency decreases by 6%,while the mass flow rate increases at first and then decreases.The present results provide a theoretical basis for the independent development of large-scale civil aircraft in China.

关 键 词：冲压空气系统 NACA埋入式进气口 飞行参数 冲压效率 质量流量 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]