Title: Aeroelastic stability of a transonic axial compressor fan blade
Abstract: The aeroelastic stability of a NASA 67 transonic fan blade was predicted by using the energy method in the near stall condition.The CSD/CFD data transfer was based on the improved 3D linear interpolation method.The FLUENT dynamic mesh technology was used in the simulation of unsteady flow around the oscillating blade.The unsteady aerodynamic response of NASA 67 blade under excitation of the first three modes was studied.It was found that the phase angle between unsteady aerodynamic forces and vibration displacements Decides that the unsteady aerodynamic force do positive or negative work;the analysis of unsteady surface pressures reveals that the modal shape and the shock are the main influence factors on the aeroelastic stability of the rotor blade.
Publication Year: 2011
Publication Date: 2011-01-01
Language: en
Type: article
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