压气机静叶栅层流分离泡转捩与角区分离数值模拟与实验

采用γ-Reθ转捩模型对某可控扩散叶型(CDA)平面叶栅全攻角范围进行了三维数值计算，通过对比数值计算结果与叶栅实验吻合较好。在此基础上，分析了进口来流湍流度和雷诺数变化对叶栅表面层流分离、转捩以及角区分离的影响。结果表明:进口湍流度低于5%时，吸力面存在层流分离，当进口湍流度大于5%后，层流分离移除，但转捩会一直存在；随着进口湍流度或雷诺数增加，吸力面和压力面转捩位置均会前移；随着进口湍流度增加，吸力面角区分离会有所减小，雷诺数增加对角区分离的影响不大。 

Numerical simulation and experiment of laminar separation bubble transition and corner separation of compressor stator cascade

Three-dimensional numerical simulation of the controlled diffusion airfoil (CDA) linear cascade in whole range of incidences was implemented by the γ-Reθ transition turbulence model.The numerical results were in good agreement with the experiments.Based on these,the effect of the turbulence intensity and Reynolds number on the laminar separation,transition and corner separation on the blade was studied.Result showed that,the laminar separation bubble can be found when the turbulence intensity was lower than 5％.If the turbulence intensity increased greater than 5％,the laminar separation could be removed totally.However,the transition from laminar to turbulence retained.With the increase of turbulence intensity and Reynolds number,the transition point moved forward.Otherwise,the corner separation on the suction side of cascade reduced a little when the turbulence intensity went up.The corner separation was independent of the Reynolds number.