A numerical investigation on the effects of blade frequency mistuning on theacoustic emission of a rotor cascade in subsonic flow is shown. A numerical method has beendeveloped and implementd to obtain the mistuned rotor aeroelastic response and theassociated acoustic waves. Both the aeroelastic and acoustic models are based on a linearunsteady small perturbations theory. The dynamic aeroelastic coupling between bending andtorsional responses of each blade and the aerodynamic coupling among the blades areincluded in the formulation.
|Numero di pagine||7|
|Rivista||MECCANICA DEI MATERIALI E DELLE STRUTTURE|
|Stato di pubblicazione||Published - 2012|