Study of the deformation of compressor blades during rotating stall

Abstract

This paper introduces aerodynamic simulations and structural analysis of a high speed centrifugal compressor at the stall condition. Simulations were performed for the compressor when the air injection control is applied and the results of the controlled compressor were compared to that for the uncontrolled compressor. The case of the compressor with air injection control was discussed in details in a previously published paper done by the authors of the current presented work. It was found that the stall effect is maximized at the impeller exit and at the vaneless area due to the strong pressure and velocity fluctuations resulting from the random interaction between the main flow and the tip leakage flow. Results showed that the forces and moments for the controlled compressor case are lower than those for the uncontrolled compressor case during stall. Results showed also that the maximum deformation of the blades near the tip region is located at the area corresponding to end of the axial blade profile up to the start of radial blade profile.