Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan  

作　　者：薛亮 韩万金 

机构地区：[1]Propulsion Theory and Technic Academy, Harbin Institute of Technology

出　　处：《Journal of Harbin Institute of Technology(New Series)》2010年第1期75-81,共7页哈尔滨工业大学学报（英文版）

摘　　要：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.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.

关 键 词：transonic axial fan splitter blade shock wave flow loss compressor 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] TH452[机械工程—机械制造及自动化]