融合式叶尖小翼对低速压气机转子气动性能的影响

Effects of Blended Tip Winglet on Aerodynamic Performance of a Low Speed Compressor Rotor

关键词:  融合式叶尖小翼  低速压气机转子  间隙流动  数值研究

Key words:  Blended tip winglet  Low speed compressor rotor  Tip leakage flow  Numerical simulation

摘要:

为了进一步揭示融合式叶尖小翼对压气机转子间隙流动的影响机理，采用数值模拟方法对低速压气机转子加装叶尖小翼控制间隙流动进行研究，着重考察了不同几何宽度及安装方式小翼对转子气动性能的影响。结果显示，叶尖小翼改变了转子中的泄漏涡轨迹，影响着叶片吸力面附面层的分离程度，适当几何宽度的压力面小翼可以在压气机转子效率略有降低的情况下使其失速点流量系数减小8.20%。

Abstract:

In order to further reveal the effects and action mechanics of the blended winglet on the tip leakage flow of compressor rotor，a numerical simulation has been carried out to investigate the effects of blade tip winglet on controlling tip clearance flow in an axial compressor rotor. Emphasis was put on the analysis of effectiveness of blade tip winglet with different winglet geometries，suction side winglet and pressure side winglet. The simulation results show that rotor tip leakage vortex trajectories are changed by the blended tip winglets. Thus the degree of suction surface boundary layer separation is also changed. The specific pressure side winglet is found highly effective to reduce the compressor rotor stalling flow coefficient by 8.20% with a slight reduction of efficiency.