Experimental and Numerical Analysis of a Compressor Stage under Flow Distortion

On many occasions, fan or compressor stages have to face azimuthal flow distortion at inlet, which affects their performance and stability. These distortions can be caused by external events some particular geometrical features. The aim of this work is propose a joined numerical experimental analysis the behavior in single axial stage under distortion. are generated different grids that placed upstream rotor. Experimentally, based on measurements obtained series unsteady pressure sensors flush-mounted casing machine URANS computations conducted using elsA software. simulated drop stagnation ratio inlet boundary condition. study focusing first ability drop, imposed as an condition CFD, reproduce accurately effect singular value decomposition (SVD) dynamic mode (DMD). A special attention then paid, level, arising rotating stall, from onset instability up completely developed stall cells.