Flow of the passage mid span section in a low speed axial compressor is simulated using two dimensional Navier Stokes equations.It is found that the calculated results are in good agreement with the experimental data.The characteristics of blade force frequency chart are investigated by using the Fourier series method.Results show that for different axial gaps between the rotor and stator
fluctuation of the unsteady blade force is mostly determined by the first rank Fourier component.Simplifying the fluctuation as sine function
it can be derived that as long as the number ratio of the disturbing to the disturbed blade row is not integer
the total unsteady blade force fluctuation from the disturbed blade row will approach to zero.
Analysis of matching characteristic of transonic tandem stator airfoil and its optimization
Intensity analysis of blades in axial compressor with inlet distortion
Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor
Research on turbofan engine HP-compressor rotor-12 blade tip clearance control
Investigation of off design performance of a transonic compressor with circumferential grooves
Related Author
TAO Yuan
YU Xian-jun
LIU Bao-jie
ZHANG Ming-ming
HOU An-ping
HE Xiao-fan
LI Shao-bin
LIANG Chao
Related Institution
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics
School of Aerospace, Tsinghua University
School of Power and Energy,Northwestern Polytechnical University