摘要
针对一种二元混压式变几何进气道开展了边界层抽吸对进气道气动性能影响规律的研究。初步计算分析可知:设计状态下进气道不起动,主要原因是喉道面积过小,产生的大规模流动分离堵塞喉道。为有效消除分离,采用孔板附面层抽吸的方法,在分离较严重的部分区域进行抽吸,结果表明:对喉道上游抽吸能更有效地减小附面层影响和改善进气道起动性能,对喉道侧板和下游抽吸对起动性能影响较小,在抽吸流量相同时,多区域同时抽吸的效果要优于单个区域。根据抽吸对进气道气动性能参数的影响规律,最终确定一种较优的抽吸方案:在进气道不起动时,能改善进气道的起动性能,进而保证进气道正常起动,在起动后则尽可能地提高进气道的气动性能。
The influence of boundary layer suction on the aerodynamic performance of a twodimensional mixed compression variable geometry inlet is studied.The preliminary calculation results show that the inlet is unstarting.The main reason of unstarting is the obstruction of throat caused by the smaller area of it.In order to effectively eliminate the separation,the suction method of the orifice plate with the surface layer is adopted,and the suction is performed in the part where the separation is severe.The results show that the influence of boundary layer can be reduced and the starting performance of inlet can be improved more effectively by suctioning on the area nearby the upstream than that of sidewall and downstream of throat.The effect of suction on multiple areas is better than single area.Finally,according to the influence on the aerodynamic parameters of inlet,a relatively excellent suction scheme is carried out.When the inlet does not start,the suction scheme can guarantee its starting and improve the aerodynamic performance of inlet as much as possible after its starting.
作者
高明
袁化成
尹涛
郭荣伟
GAO Ming;YUAN Huacheng;YIN Tao;GUO Rongwei(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《重庆理工大学学报（自然科学）》
CAS
北大核心
2020年第1期126-134,共9页
Journal of Chongqing University of Technology：Natural Science
基金
国家自然科学基金资助项目(11772155)
关键词
变几何进气道
边界层
流动分离
孔板抽吸
variable geometry inlet
boundary layer suction
flow separation
porous plate
