TS-36 Numerical Investigation on Stall Flutter of a Compressor Cascade(Session B-4: Unsteady Flow 1)

概要

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Stall flutter of a compressor cascade is studied by numerical analysis of the separated flow around the blades oscillating in a torsional mode. A numerical method is developed for the present study, where used are a discrete vortex modeling to calculate the convection and the diffusion of the vorticity in the separated flow and a grid system deforming together with the blade oscillation. Examinations are performed with respect to a compressor cascade of NACA 65-series blades working at such an inlet flow angle where the rotating stall is also liable to occur. The variations of the flow behavior and the unsteady aerodynamic characteristics with reduced frequency and interblade phase angle of blade oscillation are discussed. Attention is paid in particular to the relationship between the occurrence of the stall flutter and the propagation of the rotating stall.
公益社団法人日本ガスタービン学会の論文
1999-11-14