Turbine blade having a gas film cooling structure with a composite irregular groove and its manufacturing method

摘要

A turbine blade (100) having a gas film cooling structure with a composite irregular groove, the turbine blade (100) having a hollow structure, and an outer wall (101) thereof having a plurality of concave first grooves (105). A plurality of discrete holes A (400) penetrating to the inner wall (102) of the turbine blade are installed in each first groove body bottom portion (500). The first groove body (105) is a composite irregular groove, and is composed of at least two parts along the depth direction, and the part having a depth of H1 from the bottom of the first groove body (500) is the first part (302). The remaining portion is the second portion (301), and at least one side wall of the second portion (301) is formed so as to extend laterally from the same side wall of the first portion (302). After the gas is ejected from the discrete hole A (400), it develops well in the first portion (302) of the first groove to form a continuous, uniform positive pressure gas, and then the second portion. It is transmitted to the open end via (301) and flows out unevenly toward the outer wall (101) side of the turbine blade, and forms a continuous and uniformly attached gas film on the outer wall (101) of the turbine blade. A method for manufacturing the turbine blade is further disclosed.