Patent ID: 6086329
Filing Date: 2000-07-11
Classification: F01D

Abstract:
A rotating blade row for a gas turbine, comprising:a plurality of moving blades adapted to be adjacently arranged around a circumference disposed about a longitudinal axis of the gas turbine, each moving blade including a platform which has opposite sides that confront the corresponding platforms of adjacent moving blades, each platform including a forward flange portion and an aft flange portion, each flange portion defining two opposite corners spaced from corresponding corners of flange portions of adjacent moving blades;seal pins inserted between adjacent platforms of the moving blades to prevent cooling air from leaking from lower parts of the moving blades between the adjacent platforms, the seal pins including forward ends proximate forward edges of the platforms and aft ends proximate aft edges of the platforms;grooves formed at the four corners of the flange portions of each platform, each groove extending substantially longitudinally and circumferentially, the grooves at the forward edges of the platforms extending longitudinally such that the grooves overlap the forward ends of the seal pins, and the grooves at the aft edges of the platforms extending longitudinally such that the grooves overlap the aft ends of the seal pins; anda seal member inserted in each pair of adjacent grooves in the forward and aft flange portions of the moving blades so as to extend across gaps between the adjacent comers thereof to seal the gaps between the platforms, the seal members at the forward and aft edges of the platforms being disposed in the grooves so as to respectively overlap the forward and aft ends of the seal pins.