Abstract
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.
Lingua originale | English |
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pagine (da-a) | 14-20 |
Numero di pagine | 7 |
Rivista | MECCANICA DEI MATERIALI E DELLE STRUTTURE |
Volume | 3 |
Stato di pubblicazione | Published - 2012 |