This paper describes a numerical investigation of rotating stall in an axial multi-stage compressor using an in-house CFD (Computational Fluid Dynamics) based aeroelasticity code. This study investigates the effects of VSV (variable stator vanes) schedule on the occurrence of rotating stall at engine part-speed. Moreover, the effects of VSV circumferential mis-stagger angles (e.g. vane stagger angle variation) on the inception of rotating stall are also investigated. Virtual pressure probes are used here in the CFD models to extract unsteady pressure levels at locations of interest. These numerical studies have also enabled to evaluate the blade peak displacements due to rotating stall and hence to predict the blade vibration levels. In general, the numerical results would appear to be in line with past experience from rig and development engine data.

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