FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW.
An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane's cascade theory is used to determine the unsteady aerodynamic loads. Parametric studies are performed to determine the effects of mode coupling, Mach number, damping, pitching axis location, solidity, stagger angle, and mistuning. The results show that supersonic axial flow fan and compressors blades are susceptible to a strong torsional mode flutter having critical reduced velocities which can be less than one.