J.-C. Chassaing, G.A. Gerolymos

In this paper a 3-D unsteady aerodynamic methodology for turbomachinrey flutter is described and evaluated. This aerodynamic operator, based on the time-linearized Euler or Navier-Stokes equations, can be used either to compute the flowfield response to a given vibratory mode of the bladed disk, or, in conjunction with a coupling procedure, to determine the aeromechanical eigenmodes and their stability. The time-linearized method is based on the linearization of a nonlinear numerical scheme. The source terms of the time-linearized aerodynamic operator are validated against semi-analytical linearized theorical results for a subsonic flat-plate cascade with bending vibratory modes. The second test-case is the well-known eleventh International Standard Configuration annular cascade involving both subsonic and transonic flows. The final configuration is a centrifugal vibrating compressor which demonstrates the ability of the present method to investigate the aeroelastic stability of realistic configurations.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-10; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

navier-stokes equation, flutter, euler equation

Bibliothek

2005