Patent ID: 7334993
Filing Date: 2008-02-26
Classification: F01D

Abstract:
1. A gas turbine rotor blade including a blade section provided with a shroud cover at an outer peripheral end thereof, and a platform, a shank and a dovetail which are formed in an integral structure to successively continue from said blade section, said gas turbine rotor blade having an inner cooling hole formed to penetrate through said gas turbine rotor blade from said dovetail to said shroud cover, wherein said shroud cover has a cooling through hole formed to open in an outer surface of said shroud cover and extend in communication with said inner cooling hole for cooling a target area in which significant creep damage of the shroud cover is predicted, in the vicinity of a root portion of the shroud cover projecting, in the form of a cantilevered beam, said cooling through hole being formed to open at a position away from said target area, with the distance from the center of the cooling through hole from said target area exceeding 1.8 times the radius of said cooling through hole.