The paper presents the results of a study focusing on aerodynamic non-uniformities and their effect on frequency and damping variations. Small tolerances of stagger angle or camber can affect the aerodynamic loading of rotor blades, without significantly altering the structural properties. This investigation looks into the degree of change of natural frequencies and damping of the aeroelastic model caused by blade stagger angle variations. The model used in the study is a simplified aero-engine fan model. The investigation involved three different patterns at two operating speeds. The results suggest that damping in a mis-staggered structure is more prone to variation than frequencies.

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