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

Effect of Tip-Blade Cutting on the Performance of Large Scale Axial Fan
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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.
出处 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 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)
关键词 large axial fan tip-blade cutting numerical simulation tip-leakage vortex flow capacity large axial fan tip-blade cutting numerical simulation tip-leakage vortex flow capacity
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