Patent ID: 8281486

Claim:
A method for machining a gas turbine rotor ( 10 ) having a cooling air slot ( 19 , 19 ′), which concentrically extends around an axis ( 18 ) of the gas turbine rotor ( 10 ) and is supplied with compressed cooling air via axial cooling air holes ( 14 ), which at a side of the gas turbine rotor lead into a slot base ( 16 ) of the cooling air slot ( 19 , 19 ′), and an opening of the cooling air slot is covered by bridges ( 36 ) which are arranged in a distributed manner over a circumference of the gas turbine rotor and spaced apart from each other by gaps ( 38 ), the method comprising: lowering a material-removing tool ( 22 , 25 ) in the gaps ( 38 ) between the bridges ( 36 ) one after the other into the cooling air slot ( 19 , 19 ′); machining the slot base ( 16 ) of the cooling air slot ( 19 , 19 ′) over the entire circumference of the gas turbine rotor, and widening, in width (b 1 , b 2 ), the slot base ( 16 ) of the cooling air slot ( 19 , 19 ′) as a result of the material removal in such a way that the slot base has a tear-shaped cross-sectional contour with a constriction ( 20 ) which lies at a level of the bridges ( 36 ).