The nonlinear coupled vibration response of the compressor blade under subsonic flow and the condition of 1∶2 internal resonance was studied. The transverse aerodynamic loads of three-dimensional compressor blades were obtained by the vortex lattice method (VL). The mode functions of the first torsional mode and the second bending mode of the rotating blade were obtained by the Chebyshev-Ritz method and the first three frequencies were compared with the finite element results. By using Galerkin method

the partial differential equations of the system were truncated

and the two-degree-of-freedom ordinary differential equations of the torsional mode and the bending mode were obtained. By solving the equations with linear coupling stiffness term

two possible solutions were obtained and the stability analysis was investigated. Through analysis of the energy transfer between these two modes of the system

the force amplitude curve of the torsional mode and the bending mode of the system was calculated when the tuning parameter was σ=0

σ1≠0 and the tuning parameter was σ=0

σ1=0. The saturation behavior and the phenomenon of energy transfer between the modal amplitudes were analyzed. When the external excitation tuning parameter was σ1=0

the jump phenomenon of the torsional mode amplitude disappeared. At the same time

the influences of different parameters on force frequency and amplitude frequency characteristics were analyzed.