Patent ID: 6887039
Filing Date: 2005-05-03
Classification: F01D,F02C

Abstract:
1. 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; and 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 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.