A time-linearized quasi-3D solver for flutter analysis in turbomachinery flows was modified in order to deal with incoming perturbations due to unsteady interactions with upstream/downstream rows. To do this, exact two-dimensional single-frequency non-reflecting boundary conditions of Giles were implemented at inlet/outlet boundaries. A matrix dissipation model was used to reduce the artificial damping of propagating waves in the computational domain. Various applications for both uniform and non-uniform steady mean flows are presented for cascade configurations of turbomachinery interest, and results are compared with quasi-analytical and numerical data available in literature. Analyses of preliminary results are promising for future applications to turbomachinery configurations and fully three-dimensional flows.

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