Flutter of turbofan rotors with mistuned blades

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.

Duke Scholars

Author Robert Kielb Thomas Lord Department of Mechanical Engineering and Materia ...