This paper reports on the experimental investigation of the stall inception process of several high-speed transonic compressor rotors at design speed and off design conditions. High response pressure transducers were used to measure the unsteady static pressure at the casing upstream of the stage. A discrete Spatial Fourier Analysis (SFT) is performed as described by Garnier et al. (1991) to obtain information about the magnitude and phase of modal waves. The application of spectral wave energy analysis as an indicator for the onset of stall is discussed. Results show the wide range of stall inception phenomena for different 3D bladed rotors.
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