Numerical method was applied to the unsteady flow simulation at the mid span of a two-stage low speed compressor,and the blade boundary layer flow under rotor/stator interaction was investigated.By the model of wake/boundary layer interaction provided in this paper,the simulated blade frictional force and the boundary layer turbulent kinetic energy,the influence of wake/potential flow interaction on the blade boundary layer flow was analyzed in detail.The results show that under the condition of rotor/stator interaction,the wake is able to induce the stator laminar boundary layer flow to develop into turbulent flow within a certain range of wake interaction.In the stator suction boundary layer,an undisturbed region occurs behind the rotor wake,which extends the laminar flow range,and the wake with high turbulent intensity has the capability to control the boundary layer separation under adverse pressure gradient. Numerical method was applied to the unsteady flow simulation at the mid span of a two-stage low speed compressor, and the blade boundary layer flow under rotor / stator interaction was investigated. BY the model of wake / boundary layer interaction provided in this paper, the simulated blade frictional force and the boundary layer turbulent kinetic energy, the influence of wake / potential flow interaction on the blade boundary layer flow was analyzed in detail. The results show that under the condition of rotor / stator interaction, the wake is able to induce the stator laminar boundary layer flow to develop into turbulent flow in a certain range of wake interaction, where extends the laminar flow range, and the wake with high turbulent intensity has the capability to control the boundary layer separation under adverse pressure gradient.