摘要
以高负荷两级风扇第一级前掠转子为研究对象,通过数值模拟手段对近失速点叶尖流场进行了深入分析。为比较前掠对泄漏涡结构的影响,与同等气动性能下的常规转子进行了对比。结果表明前掠转子在近失速工况下泄漏涡涡心并未发生破碎,气动负荷展向分布更加均匀。对前掠转子不同于常规转子的叶尖泄漏涡结构产生机理提出了新的解释。
We numerically calculate the three-dimensional viscous flow field near the blade tip region at the near stall margin of a highly-loaded and forward-swept fan rotor. We compare the effects of the forward-swept fan rotor on the tip clearance vortex structure with those of a conventionally stacked radial rotor that has aerodynamically equal performance. The comparison results show that both the stall margin of the forward-swept fan rotor and the distribu- tion of its aerodynamic tip loading are improved. Our detailed analysis of its flow field reveals that the tip clearance vortex of the forward-swept fan rotor does not break under the near stall condition, thus providing a novel explanation why the tip clearance vortex structure of a forward-swept fan rotor is different from that of a conventional fan rotor.
出处
《机械科学与技术》
CSCD
北大核心
2012年第6期869-872,共4页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(50976093)资助
关键词
高负荷
前掠
泄漏涡
涡破碎
flow field
stall margin
highly-loaded and forward-swept fan rotor
tip clearance vortex
vortex break
