雷诺数对涡轮叶栅流动的影响  

EFFECT OF REYNOLDS NUMBER ON TURBINE CASCADE FLOW

作　　者：邹正平[1] 宁方飞[1] 刘火星[1] 李维[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《工程热物理学报》2004年第2期216-219,共4页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.50206001);航空基础科学基金项目资助(No.03C51030)

摘　　要：本文利用数值模拟手段模拟了涡轮叶栅内部三维流动,分析了雷诺数对涡轮叶栅内部流动图画的影响。结果表明在低于自模化雷诺数条件下,雷诺数的降低将对涡轮叶栅吸力面边界层的发展产生严重的不利影响。雷诺数降低至一定程度,将导致吸力面出现严重的分离,端部二次流流动相应加剧,使低雷诺数情况下涡轮叶栅性能恶化,在设计中应予充分重视。Three dimensional turbine cascade flows were numerically investigated. The effect of Reynolds number on the turbine cascade flow was analyzed. Numerical results showed that at the flow conditions below the critical Reynolds number, a further decrease of Reynolds number will adverse impact the development of boundary layer on the suction side of cascade. As the Reynolds number is below a specific value, separation presents on the suction side, accordingly the secondary flow near end-walls is more intensive, which deteriorate the performance of turbine cascade.

关 键 词：雷诺数 涡轮 边界层 二次流 数值模拟 叶栅 三维流动 

分 类 号：O357.5[理学—流体力学] V235.111[理学—力学]