TURBINE BLADE HAVING COMPOSITE SPECIALLY-SHAPED SLOTTED GAS FILM COOLING STRUCTURE AND MANUFACTURING METHOD THEREOF

A turbine blade (100) having a gas film cooling structure with a composite irregular groove. The turbine blade (100) has a hollow structure, and an outer wall (101) thereof has multiple recessed first grooves (105). A bottom portion (500) of each first groove is provided with multiple discrete holes A (400) extending to an inner wall (102) of the turbine blade. The first groove (105) is a specially-shaped slot, and comprises at least two portions in a depth direction. The portion having a depth of H1 and starting from the bottom portion (500) of the first groove is a first portion (302), and the remainder is a second portion (301). At least one side surface of the second portion (301) is formed by lateral extension of the same side surface of the first portion (302). Gas ejected from the discrete holes A (400) fully expands in the first portion (302) of the first groove, forms a continuous and uniform gas with positive pressure, and is conveyed, via the second portion (301), to a side of an open end close to the outer wall (101) of the turbine blade and flows out, so as to form a continuous and uniformly adhering gas film on the outer wall (101) of the turbine blade. Also disclosed is a manufacturing method for the turbine blade.