Flutter of a fan blade in supersonic axial flow

Published

Journal Article

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 compressor blades are susceptible to a strong torsional mode flutter having critical reduced velocities that can be less than one. © 1989 by ASME.

Full Text

Duke Authors

Cited Authors

  • Kielb, RE; Ramsey, JK

Published Date

  • January 1, 1989

Published In

Volume / Issue

  • 111 / 4

Start / End Page

  • 462 - 467

Electronic International Standard Serial Number (EISSN)

  • 1528-8900

International Standard Serial Number (ISSN)

  • 0889-504X

Digital Object Identifier (DOI)

  • 10.1115/1.3262294

Citation Source

  • Scopus