Abstract: The eigenvalue method is presented for determining the effects of blade mistuning and blade-disk on cascade flutter boundaries in incompressible flow. Results presented illustrate that misturing has a beneficial effect on the cascade flutter. With the mistuning amplitude increasing, the flutter boundaries move more backward and different mistuning orders have different effects on flutter boundaries, depending on the order of the modal cascade flutter. Addition of bladed-disk makes mistued cascade flutter boundaries move forward.