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Supervised by Ministry of Industry and Information Technology of The People's Republic of China Sponsored by Harbin Institute of Technology Editor-in-chief Yu Zhou ISSNISSN 1005-9113 CNCN 23-1378/T

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Related citation:Xue Liang,HuanWanJin.Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan[J].Journal of Harbin Institute Of Technology(New Series),2010,17(1):75-81.DOI:10.11916/j.issn.1005-9113.2010.01.014.
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Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan
Author NameAffiliation
Xue Liang Propulsion Theory and Technic Academy, Harbin Institute of Technology, Harbin 150001, China 
HuanWanJin Propulsion Theory and Technic Academy, Harbin Institute of Technology, Harbin 150001, China 
Abstract:
For a certain type of transonic axial fan, the flow field of a fan rotor with splitter blade was computed by numerical simulation, and the shape of the rotor was modified. The effects of different circumferential distributions concerning the splitter cascades upon the aerodynamic performance were investigated. The studies show that the optimum splitter cascade is not very close to the suction side of main blade. The load between the main blade and the splitter blade can be soundly distributed in terms of the adjustment of circumferential position of the splitter blade. The best aerodynamic performance can be successfully obtained according to the optimum shape of the expanding fluid channel reasonably formed by the splitter blade and the main blade.
Key words:  transonic axial fan  splitter blade  shock wave  flow loss  compressor
DOI：10.11916/j.issn.1005-9113.2010.01.014
Clc Number:TH453
Fund:

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