Turbine Blade And Gas Turbine Including Same

A gas turbine comprising:

• a compressor configured to compress incoming air;
• a combustor configured to mix the compressed air with fuel and combust an air-fuel mixture;
• and
• a turbine configured to generate power with the combustion gases supplied from the combustor, the turbine comprising a turbine vane guiding the combustion gases along a path through which the combustion gases flows, and a turbine blade rotating with the combustion gases flowing through the path, wherein the turbine blade comprises:
• an airfoil having an internal cooling channel, wherein the airfoil comprises:
• a suction side forming a convex curved surface protruding outwardly;
• a pressure side forming a concave curved surface recessed toward the suction side;
• a leading edge formed at a leading end to connect the suction side and the pressure side;
• a trailing edge formed at a trailing end to connect the suction side and the pressure side;
• a first cooling channel through which a first cooling fluid introduced from a lower side of the leading edge is discharged toward a rear side of the trailing edge through a first serpentine flow path formed on the pressure side;
• a second cooling channel through which a second cooling fluid introduced from a lower side of the suction side is discharged toward the rear side of the trailing edge through a second serpentine flow path formed on the suction side;
• and
• a plurality of cooling fins formed to extend from cooling channel surfaces of the first cooling channel and the second cooling channel to surfaces of the pressure side and the suction side in a direction perpendicular to the surfaces of the pressure side and the suction side.