In order to solve the problem of turbine blade stall, based on active/passive coupled control method of wavy leading-edge and AC-DBD plasma actuator, a three-dimensional numerical model of blade static stall is established. NACA0012 straight blades are introduced for comparison, the lift-drag characteristics, the development of flow structure, and static stall coupling control mechanism of three-dimensional wavy leading-edge blades under different plasma excitation voltage parameters are numerically analyzed. Research has found that at a small attack angle of the wavy leading-edge blade, the induced jet will suppress vortex structure development, which is the dominant control stage of the jet. As the angle of attack increases, applying appropriate jets can help develop the flow direction vortex structure, which is the coupling control stage. When the amplitude of the excitation voltage increases, the jet velocity also increases, and the critical angle of attack of the jet dominant control stage increases, delaying the coupling control stage. At a large stall angle of attack (AOA=12°~20°), the stall angle of the wavy leading-edge blade under plasma excitation is significantly delayed, and it still maintains a high lift, exhibiting better controlled performance. Compared with an uncontrolled straight blade, the lift can be increased by up to 39.4% at attack angle of 15°.