摘要
利用CFD技术,重点研究了来流周向预旋对多级离心压缩机级间弯道与回流叶栅等静止部件内气动性能的影响。结果表明:弯道内均存在不同程度的流动分离,且分离区的大小随来流周向预旋的增强而增大;降低来流周向预旋能有效地抑制弯道内流动分离,并能使弯道出口(即回流叶栅进口)气流更趋于均匀,这有助于提高回流叶栅的气动性能;回流叶栅内的流动是非均匀、不稳定、剧烈分离的旋涡流动,沿主流方向存在着复杂的二次涡结构,这些二次流旋涡随主流经历着明显的“初生、发展、耗散、溃灭”的过程。
The effects on the aerodynamic performance inside the standstill parts as crossover bend and de-swirl cascade of the multistage centrifugal compressor caused by the circumferentially pre-swirling coming flow have been specially studied by using of CFD. The results indicated that the flow separation occurs inside the bend with various degrees. The flow separation area will be larger with the circumferentially pre-swirling stronger. Decreased circumferentially pre- swirling of the coming flow may effectively restrain the flow separation inside the crossover bend and make the outflow from it（i. e. the inlet of de-swirl cascade） more uniform. It will be helpful to improve the flow performance for the successive de-swirl cascade because of the flow inside the de-swirl cascade is non-uniform, unstable and vortex flow with violent separation. Along the main flow, there exists the complex secondary flow. It experiences a process of generation, development, dissipation and collapse along the main flow. Figs 10 and refs 6.
出处
《动力工程》
EI
CSCD
北大核心
2007年第1期24-28,49,共6页
Power Engineering
基金
上海市科委重点项目"‘能源岛’关键技术的研究"
关键词
动力机械工程
多级离心压缩机
回流叶栅
弯道
来流周向预旋
气动性能
二次流
power and mechanical engineering
multistage centrifugal compressor
de-swirl cascade
crossover
circumfcrentially pre-swirling coming flow
aerodynamic performance
secondary flow
