Film cooling effect and heat transfer performance on the winglet-squealer tip of a turbine stage were investigated using the conjugate heat transfer method. The effects of conjugate heat transfer on heat transfer coefficient, net heat flux reduction, and film cooling effectiveness distributions on two types of squealer tip (i.e. conventional squealer tip and pressure-side winglet squealer tip) and rotor blade surfaces were analyzed. Compared to the single-fluid-domain computations, the area-averaged heat transfer coefficient on the conventional squealer tip is decreased by 6.26% and the area-averaged heat transfer coefficient on the pressure side winglet squealer tip is increased by 1.67% if the conjugate heat transfer in blade solid is considered. The area-averaged heat transfer coefficient on the pressure side surface of rotor blade with pressure-side winglet squealer tip is increased by 23.73%, and area-averaged heat transfer coefficient on the suction side surface of rotor blade with pressure-side winglet squealer tip is increased by 2.18% if the conjugate heat transfer in blade solid is considered. However, the tip geometry has slight influence on the blade surface film cooling and heat transfer performance.