Numerical Investigation of the Unsteady Flow in a Transonic Compressor with Curved Rotors
The unsteady 3D flow fields in a single-stage transonic compressor under designed conditions are simulated numerically to inves- tigate the effects of the curved rotors on the stage performance and the aerodynamic interaction between the blade rows. The results show that, compared to the compressor with un-curved rotors, the compressor under scrutiny acquires remarkable increases in efficiency with significantly reduced amplitudes of the time-dependent fluctuation. The amplitude of the pressure fluctuation around the stator leading edge decreases at both endwalls, but increases at the mid-span in the curved rotors. The pressure fluctuation near the stator lead- ing edge, therefore, becomes more uniform in the radial direction of this compressor. Except for the leading edge area, the pressure fluc- tuation amplitude declines remarkably in the tip region of stator surface downstream of the curved rotor, but hardly changes in the mid- dle and at the hub.
作 者: Mao Mingming Song Yanping Wang Zhongqi 作者单位: School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China 刊 名: 中国航空学报(英文版) ISTIC 英文刊名: CHINESE JOURNAL OF AERONAUTICS 年,卷(期): 2008 21(2) 分类号: V2 关键词: transonic compressor ,unsteady flow field curved rotor aerodynamic interaction