Flutter of a fan blade in supersonic axial flowAn 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 compressor blades are susceptible to a strong torsional mode flutter having critical reduced velocities which can be less than one.
Document ID
19880066979
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kielb, Robert E. (NASA Lewis Research Center Cleveland, OH, United States)
Ramsey, John K. (NASA Lewis Research Center Cleveland, OH, United States)