The invention discloses an air film and water transpiration combined blade cooling method. An aircraft engine carries water in certain weight (such as 120kg), and the 120kg of water is only used in 120s from an aircraft accelerating moment to a take-off moment. Cooling water is sprayed between a heat insulation front cover plate and a rotor through a nozzle under the pressure of an aircraft enginecompressor and conveyed to water cooling passages of blades under the action of centrifugal layering. Surfaces of the blades are provided with cooling air holes including air film air holes and watertranspiration composite cooling air holes, and water is heated in the blades to evaporate and is dispersed to the surfaces of the blades through the holes to form a cold air protection layer (thermalprotection) along with air film cooled gas so as to reduce heat exchange with main flow. By adoption of the method, problems of power insufficiency of a military aircraft engine in takeoff boosting and short fatigue life are solved.