摘要
采用分区网格处理方法并发展了基于分块结构的三维N-S方程流体求解器,用以模拟压气机间隙区域复杂的流动现象。以一压气机叶栅为研究对象,计算分析了端壁静止和端壁移动情况下叶栅内部的三维流场,并考虑了间隙大小的影响。通过详细分析叶栅通道内部及尾迹区域的流动并与已有的实验结果对比分析表明,程序较好地模拟出了移动壁效应对间隙区域二次流动形成和发展的影响。数值和实验结果均表明,端壁移动情况下间隙区域的二次流动特征是刮削泄漏涡的形成和发展。
Blocked structure three dimensional Navier Stokes flow solver has beendeveloped and applied to investigate the complex flow phenomena in the tip gap of axial flow compressor cascade. Numerical analysis was carried out to investigate the influence of tip clearance on the flow-field in a compressor cascade with a moving end-wall. The calculated results were compared with the available experimental data and good agreements were achieved. Secondary traverse flow velocity vector plots show the scrapping of the tip leakage vortex from the suction surface of one blade across the blade pitch to the pressure surface of the adjacent blade.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第1期112-118,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助(50506026)
航空科学基金资助(05C53016)
中国博士后科学基金资助(2005037790)
关键词
航空、航天推进系统
压气机叶栅
移动壁
刮削泄漏涡
间隙流动
aerospace propulsion system
compressor cascade
moving end-wall
scrapped tip leakage vortex
tip clearance flow
