Stationary blade in gas turbine and gas turbine comprising the same

A stationary blade provided in a gas turbine which comprises moving blades arranged in a plurality of rows and moving-blade disks to which main bodies of the moving blades are attached, wherein:

• the stationary blade comprises an outer shroud, a main body, and an inner shroud and is positioned adjacent to at least one of the moving-blade disks in an axial direction of the gas turbine;
• the stationary blade introduces a combustion gas into the main body of the moving blade of the next row;
• a concave portion is provided in the inner shroud in a manner such that:
• the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks;
• and
• a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud;
• wherein the concave portion has side walls which are continuously formed through the inner-peripheral face in a manner such that the side walls are substantially parallel to a plane of rotation of the moving-blade disks;
• and
• wherein a plurality of fins for radiating heat are arranged on a bottom face of the concave portion, which protrude towards the rotation shaft of the moving-blade disks.