An experimental and numerical study was conducted to investigate the forced response of blade vibration induced by rotating stall in a low speed axial compressor. Measurements have been made of the transient stalling process in a low speed axial compressor stage. The CFD study was performed using solution of 3-dimensional Navier-Stokes equations

coupled with structure finite element models for the blades to identify modal shapes and structural deformations simultaneously. Interactions between fluid and structure were managed in a coupled manner

based on the interface information exchange until convergence in each time step. Based on the rotating stall measurement data obtained from a low speed axial compressor

the blade aeroelastic response induced by the rotating stall flow field was analyzed to study the vibration characteristics and the correlation between the phenomena. With this approach

good agreement between the numerical results and the experimental data was observed. The flow phenomena were well captured

and the results indicate that the rotating field stall plays a significant role in the blade vibration and stress affected by the flow excitation.