Effect of Tip-Blade Cutting on the Performance of Large Scale Axial Fan  

作　　者：尹超 胡骏 严伟 张晨凯 

机构地区：[1]Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power,Nanjing University of Aeronautics and Astronautics

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2015年第6期623-630,共8页南京航空航天大学学报（英文版）

基　　金：supported by the Specialized Research Fund for the Doctoral Program of Higher Education (No. 20113218120006)

摘　　要：The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using computational fluid dynamics(CFD)methods.Experiments verified the numerical simulations.The original fan was compared with the one with tip-cutting in terms of dimensionless characteristic and aerodynamic performance in tip region under the conditions of the maximum efficiency point and near-stall point.The results showed that double leakage flow occurred in tip clearance at maximum efficiency point and spillage of leakage flow from leading edge occurred in tip-blade region at near-stall point for the both two fans;and that tip-cutting with 6% of blade height could reduce the intensity of tip-leakage vortex and increase flow capacity in tip blade region,and hold the stall margin almost the same as the original fan.The maximum efficiency of the fan with tip-cutting was improved by1%,and the ability of total pressure rising was obviously greater than the original fan.The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using compu- tational fluid dynamics （CFD） methods. Experiments verified the numerical simulations. The original fan was compared with the one with tip-cutting in terms of dimensionless characteristic and aerodynamic performance in tip region under the conditions of the maximum efficiency point and near-stall point. The results showed that double leakage flow occurred in tip clearance at maximum efficiency point and spillage of leakage flow from leading edge occurred in tip-blade region at near-stall point for the both two fans; and that tip-cutting with 6% of blade height could reduce the intensity of tip-leakage vortex and increase flow capacity in tip blade region, and hold the stall margin almost the same as the original fan. The maximum efficiency of the fan with tip-cutting was improved by 1%, and the ability of total pressure rising was obviously greater than the original fan.

关 键 词：large axial fan tip-blade cutting numerical simulation tip-leakage vortex flow capacity 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]