摘要
对某亚声速轴流压气机转子进行了全通道三维非定常数值模拟,获得了该压气机近失速工况下的详细流动情况.转子前缘均匀布置的十支静压数值探针监测结果表明,转子圆周上出现两个静压扰动区域,其中一个逐渐发展为突尖波.流场分析表明,叶顶通道中存在频繁的分离涡运动,静压扰动区域中分离涡的强度较大.分离涡诱发间隙流形成"前缘溢流"和"尾缘反流".静压扰动区域沿圆周方向传播是由分离涡在通道之间的传递引起的.传播过程中,分离涡强度的持续增大是突尖波形成的关键因素.通道中较强的"尾缘反流"沿通道上行并绕过叶片形成"前缘溢流"的现象可作为突尖波形成的标志.
Full-annulus unsteady simulations were performed on a subsonic axial compressor rotor,and the detailed flow parameters at near stall condition were achieved.Ten numerical static pressure probes arranged in front of the leading edge could detect two pressure disturbances,one of which was developed into a spike wave.According to analysis of the flow field,tip secondary vortexes exist in almost all passages near the blade tip and the most violent one appears in the disturbing areas.Tip secondary vortex could force tip clearance flow to form ＂leading edge spilling flow＂ and ＂trailing edge back flow＂.The movement of the pressure disturbance along circumference was caused by the spreading of tip secondary vortex from one passage to the next.Continuous growth of tip secondary vortex in its spreading finally led to formation of spike wave.The phenomenon that the ＂trailing edge back flow＂ goes through the inlet and spills into the adjacent passage under the blade tip can be regard as the symbol of spike emergence.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第10期2330-2338,共9页
Journal of Aerospace Power
基金
国家自然科学基金(51076133)
航空科技创新基金(08B53004)
航空科学基金(2010ZB53016)
关键词
全通道
突尖波
分离涡
前缘溢流
尾缘反流
full-annulus
spike wave
tip secondary vortex
leading edge spilling flow
trailing edge back flow
