哈尔滨工业大学学报（英文版）2010，Vol.17Issue(1)：75-81,7.
Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan
Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan
XUE Liang 1HAN Wan-jin1
作者信息
- 1. Propulsion Theory and Technic Academy, Harbin Institute of Technology, Harbin 150001, China
- 折叠
摘要
关键词
transonic axial fan/splitter blade/shock wave/flow loss/compressorKey words
transonic axial fan/splitter blade/shock wave/flow loss/compressor分类
能源科技引用本文复制引用
XUE Liang,HAN Wan-jin..Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan [J].哈尔滨工业大学学报（英文版）,2010,17(1):75-81,7.
