Flutter of turbofan rotors with mistuned blades


Journal Article

A set of aeroelastic equations describing the motion of an arbitrarily mistuned rotor with flexible, pretwisted, nonuniform blades is developed using an extended Hamilton's principle. The derivation of the equations has its basis in the geometric nonlinear theory of elasticity in which the elongations and shears are negligible compared to unity. A general expression for foreshortening of a blade is derived and is explicitly used in the formulation. The blade aerodynamic loading in the subsonic and supersonic flow regimes is obtained from two-dimensional, unsteady, cascade theories. The aerodynamic, inertial, and structural coupling between the bending (in two planes) and torsional motions of the blade is included. The equations are used to investigate the aeroelastic stability and to quantify the effect of frequency mistuning on flutter in turbofans. Results indicate that a moderate amount of intentional mistuning has enough potential to alleviate flutter problems in unshrouded, high-aspect-ratio turbofans. © 1984 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

Full Text

Duke Authors

Cited Authors

  • Kaza, KRV; Kielb, RE

Published Date

  • January 1, 1984

Published In

Volume / Issue

  • 22 / 11

Start / End Page

  • 1618 - 1625

International Standard Serial Number (ISSN)

  • 0001-1452

Digital Object Identifier (DOI)

  • 10.2514/3.8827

Citation Source

  • Scopus