Based on the structural characteristics of bird-wing bifurcation, the blade tip groove structure of a linear compressor cascade for controlling separation of suction corner was studied with the use of numerical calculation. The obtained results indicated that the effects of the tip groove on the aerodynamic performance and the flow field structure could be improved. The tip groove design caused high-pressure fluid to be injected into the corner position of separation, causing the initial corner position of separation to move backward, so the pitchwise and spanwise corner separation to be controlled. Under the conditions of positive angle of incidence, the blade tip groove had a good loss reduction effect. When the angle of incidence was less than the angle of incidence with the minimum loss, the flow loss in the cascade increased by the adoption of the tip groove. The tip groove needed to be installed near the initial position of the corner separation. As in the groove height increases, the suppression effect of the tip groove on the corner separation initially increases and then decreases. When the groove height is equal to 4% of the blade height (H), the flow loss in the cascade reduces by 14.42%.