Abstract：The aeroelastic stability of the NASA 67 transonic fan blade is predicted by using the energy method at the near stall condition. The CSD/CFD data transfer is based on the improved 3D linear interpolation method. The FLUENT dynamic mesh technology is used in the simulation of unsteady flow around the oscillating blade. The unsteady aerodynamics of NASA 67 blade with excitation of the first three modes is studied. It is found that the phase angle between unsteady aerodynamic forces and vibration displacements decides the unsteady aerodynamic force do positive or negative work. The analysis of unsteady surface pressures yields that the mode shape and the shock are the most important factors on the aeroelastic stability of the rotor blade.
2011, Vol. 30 
