Patent ID: 9488052
Filing Date: 2016-11-08
CPC Classification: B23P,F01D,F05D,Y10T

Claim Text:
1. A method for reconditioning a blade of a gas turbine, the blade comprising a blade airfoil, with a pressure-side and a suction-side, which extends in a blade longitudinal direction between a platform and a blade tip, the blade having a leading edge and a trailing edge, and is outwardly delimited by a pressure-side wall and a suction-side suction-side wall which converge at the trailing edge of the blade airfoil, and ribs arranged between the pressure-side wall and the suction-side wall forming discharge openings for cooling air which are arranged in a distributed manner along the trailing edge between the walls, the method comprising: removing a portion of the pressure-side wall and a portion of the ribs by introducing a cutout into the pressure-side wall along the trailing edge, and starting from said trailing edge, in such a way that the trailing-side edge of the pressure-side wall is cut back compared with the trailing-side edge of the suction-side wall, and a terminal portion of the ribs proximate the trailing-side edge are cut back,