Effects of mistuning on bending-torsion flutter and response of a cascade in incompressible flow

Abstract

a base for natural, logarithmThis paper presents an investigation of the [G], [Ga] matrices defined in equation (11); effects of blade mistiming on the aeroelastic sta-

Aeroelastic Characteristics of a Cascade of Mistuned Blades in Subsonic and Supersonic Flows

“…The effects of blade mistuning on coupled bending-torsion flutter and aeroelastic respon se due to wakes in incompressi -2 ble flow have been studied in Ref. 10. The purpose of this paper is to continue and to extend the work of Ref .…”

“…It should be mentioned that this rotor was analyzed for incompressible flow in Ref. 10. The blade bending-to-torsion frequency ratio for the tuned rotor is 0.357, and the elastic axis and c.g.…”

“…10, the disk is assumed to be rigid and the rotor i s modeled as an infinite, twodimensional cascade of airfoils capable of plunging and pitching motions . The geometry of a tuned cascade is shown in Fig.…”

“…10. In the present paper, the unsteady aerodynamic loads are calculated by using Smith'sll theory in subsonic flow and Adamczyk and Goldstein's12 theory in supersonic flow with a subsonic leading edge.…”

“…The purpose of this paper is to continue and to extend the work of Ref . 10 into the subsonic and supersonic flow regimes. To the best of the authors' knowledge, the aeroelastic characteristics of mistuned cascades in subsonic and supersonic flows using a multi-degree of freedom model for the blades have not been studied in the published literature.…”