Reduced-Order Aerodynamic Models for Mistuned Compressor Blades Mistuning, or blade-to-blade variation, is an important consideration for aeroelastic analysis of bladed disks. The effects of mistuning on blade structural dynamics have been extensively studied and are well understood; however, to date, aerodynamic effects have not been included in such analyses.
In this research, a coupled aerodynamic/structural mistuning framework is formulated. Reduced-order aerodynamic models are derived and coupled with an existing structural mistuning framework. The computational framework will be used to gain insight to the effects of aerodynamic damping on aeroelastic behavior of mistuned bladed disks and to quantify the impact on aerodynamic performance of intentional mistuning.