轴流压气机近失速及旋转失速全通道数值模拟  

Full-annulus numerical simulation of near stall and rotating stall in an axial flow compressor

作　　者：石嵩[1,2] 屠宝锋[1,3] 

机构地区：[1]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,南京210016 [2]中国航空工业集团公司哈尔滨飞机工业集团有限责任公司飞机设计研究所,哈尔滨150060 [3]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第5期1196-1204,共9页Journal of Aerospace Power

基　　金：教育部博士点基金(20113218120006);南京航空航天大学青年科技创新基金(NS2014021)

摘　　要：为研究轴流压气机失速起始的动态过程,对某两级低速轴流压气机的第1级进行整环全通道模拟.结果表明:在近失速点流场中存在周向大尺度的速度波动,该波动与静子叶排首先出现的周向不均匀分布的叶背附面层分离密切相关,并且随着压气机进一步节流,波动幅值逐渐增大,最终诱发转子若干通道出现严重附面层分离,堵塞流道,压气机进入旋转失速.失速团完全发展后的转动频率与试验结果吻合较好.To study stall inception of the axial flow compressor, full-annulus numerical simulation in the first stage of a two-stage low-speed axial flow compressor was presented. Results showed that there existed a kind of velocity fluctuation in the circumference scale in stall inception, which was closely related to the uneven boundary layer separation that first happened on the suction of stator blade rows. With further throttling of the compressor, the fluctuation amplitude increased gradually, and eventually it induced several rotor channels to generate serious boundary layer separation, blocking these channels. The compressor system led to the rotating stall condition. The rotational stall frequency with full development had good coincidence with the experimental result.

关 键 词：低速轴流压气机 全通道模拟 附面层分离 速度波动 旋转失速 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]