超声速进气道反压引起的不起动/起动现象研究  

Investigation on Unstart/Start Phenomenon of Supersonic Inlet Caused by Back Pressure

作　　者：赵昊 谢旅荣 葛严 黄凯文 曾强 ZHAO Hao;XIE Lyu-rong;GE Yan;HUANG Kai-wen;ZENG qiang(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]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,江苏南京210016

出　　处：《推进技术》2020年第10期2204-2212,共9页Journal of Propulsion Technology

摘　　要：为了探索节流反压变化对进气道起动性能的影响,在来流马赫数为2.0的情况下,采用定常/非定常数值仿真方法对出口可移动壁面运动速率为12,24,36mm/s的进气道进行了研究,分析了不同可移动壁面运动速率引起的堵塞度变化对进气道流场特性及气动性能的影响。结果表明:采用非定常数值仿真获得的进气道性能参数和流场特性变化规律与定常数值仿真时一致,定常/非定常数值仿真时的进气道性能参数均存在"迟滞回路"现象;进气道出口堵塞度变化速率越大,"迟滞回路"现象越明显;堵塞度变化速率越大,进气道进入不起动状态时的堵塞度越高,进气道再次进入起动状态时的堵塞度越低。In order to investigate the throttling pressure on starting performance of supersonic inlets,this paper simulated the inlets with moving outlet wall at rate of 12,24 and 36 mm/s using steady/unsteady approaches under freestream of Mach 2.0.The effects of the caused throttling rates by the various moving wall on inlet flow features and aerodynamics were discussed.Results indicated that the employment of unsteady/steady calculations hardly leads to difference of the obtained outcomes.The"hysteresis loop"appears for inlet performance using both computational methods and the"hysteresis loop"becomes more apparent with the increase in the changing rate of blockage.Also,as the changing rate of blockage goes up,inlet switches to unstart state at a higher throttling rate and the inlet restarting is achieved at lower throttling rate.

关 键 词：超声速进气道 数值仿真 堵塞度 非定常 不起动 起动 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]