Turbine blade with step gap cooling structure on pressure surface

The invention discloses a novel gas air film cooling structure for an aircraft engine and a turbine guide blade of a gas turbine. The cooling structure comprises a blade basal body, an air film gap, a connecting rib and a step surface, and is characterized in that a step-shaped gap air film flow outlet structure is formed by an inner blade and an outer blade on the blade pressure surface basal body and the connecting rib, so that cooling air flows out in the tangential direction of the blade surface. The cooling flow outlet structure of a novel blade can form a uniform and consistent cooling air film on the blade surface; the air outlet air film is higher in stability; the vortex effect of cold air flowing out is weakened; the cooling air film is large in covering area and high in cooling efficiency; and meanwhile, the cooling air in the tangential direction is mixed with a high-temperature main flow, so that the pneumatic loss of the blade is reduced, and the blade has both high cooling efficiency and high-efficiency pneumatic performance. The structure also can enable the blade to be produced by a piece connecting structure, and can simplify the blade processing and maintenance process.