The flow through most turbomachinery blade rows is dominated by unsteady phenomena. Accurately predicting the behavior of complex unsteady flows with computational analyses can require enormous computer resources. To make the computational problem more tractable, the time dependence of the solution has traditionally been removed. Thus, during the past decade many steady flow procedures have been developed and validated for turbomachinery applications. Less attention has been given to the rigorous development of unsteady flow computational procedures. The purpose of this investigation is to extend, validate, and perform numerical experiments with two existing computational procedures for the study of inviscid, compressible, unsteady flow in axial turbomachinery. Results are presented for unsteady subsonic and transonic flows subject to inlet vortical distortions.

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