摘要
根据叶栅内部二次流形成和发展的机理,应用正弦函数和多项式函数建立了一种叶栅非轴对称端壁成型方法.采用三维时均可压缩N-S方程组求解技术,数值研究了采用所建立的非轴对称端壁成型方法设计的跨音速直列叶栅的流动特性,分析讨论了建立的非轴对称端壁成型方法的效果及其对叶栅流动特性的影响.计算结果表明:所建立的非轴对称端壁可以有效地抑制和延迟叶栅通道中二次流涡系的发展,沿整个叶栅流道内总压系数明显降低,成型过程中幅值控制函数中最大幅值约占7.5%叶高为宜,叶栅出口位置处总压损失降低了约5.6%.
Based on the mechanism of secondary flow formation and development in a turbine cascade,SINE function and polynomial function were applied to develop a non-axisymmetric endwall profiling method. Three-dimensional Reynolds-Averaged Navier-Stokes solution was used to study the flow characteristics of the transonic linear turbine cascades designed by non-axisymmetric endwall profiling method. And,the effect of this method and its influence on the flow characteristics of cascade were analyzed and discussed. The numerical results show that, the established non-axisymmetric endwall could suppress and delay efficiently the development of secondary flow vortex system in the cascade passage, and the total pressure coefficient along entire cascade passage declines remarkably. The maximum amplitude of the profiling method is preferably set to 7.5 % span,and the total pressure loss at ex- it reduces by 5.6%.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第9期1487-1491,共5页
Journal of Aerospace Power
基金
国家自然科学基金(50476052)
关键词
航空、航天推进系统
二次损失
非轴对称端壁
透平叶栅
数值模拟
aerospace propulsion system
secondary loss
non-axisymmetric endwall profiling
turbine cascade
numerical simulation
