Mistuned Bladed Disk Analysis with Unsteady Aerodynamics Using Turbo-REDUCE

In this paper, the effect of structural and aerodynamic coupling with mistuning on flutter and forced response is studied. A reduced order model (ROM) analysis procedure available in the turbo-REDUCE code is used for this purpose. The study validated the inclusion of the unsteady aerodynamic effects and the implementation of the ANSYS structural analysis into the turboREDUCE code. The calculations from turbo-REDUCE are compared with those obtained from the ASTROP2-LE code, an aeroelastic analysis code that was developed earlier for a rotor with a rigid disk. For the case studied, the effects of unsteady aerodynamic forces on flutter of the bladed disk were minimal. However, the response amplitudes increased about 60% for random mistuning and 9% for alternate mistuning due to mistuning.

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