Slotted air film cooling structure for guide blades of turbines

The invention discloses a novel slotted air film cooling structure for guide blades of turbines of gas turbine engines. The novel slotted air film cooling structure comprises a blade base, air film slots, connecting ribs and stepped planes, and is characterized in that the air film slots are oblique slots which are forwardly oblique along a mainstream direction, are communicated with a tail cooling air cavity and are equidistantly arrayed along the blade height direction, outlets of the air film slots are separated from a blade tail edge, and the connecting ribs and the air film slots are alternately distributed. The novel slotted air film cooling structure has the advantages that uniform and consistent cooling air films can be transversely formed by the novel blade structure, and outflow air films are high in stability; an eddy flow effect of outflow cooling air can be weakened, the cooling air films are large in coverage area, and accordingly the novel slotted air film cooling structure is high in cooling efficiency and simple in machining.