Patent ID: 8657577

Claim:
A turbine rotor for a gas turbine, comprising: a turbine disk comprising an axially extending rotor blade retaining slot; a plurality of coolable rotor blades which are assembled in each case to form rotor blade rows, each of the plurality of coolable rotor blades being arranged on the turbine disk and comprising: a respective blade root arranged in the axially extending rotor blade retaining slot of the turbine disk, the respective blade root comprising two grooves which extend substantially azimuthally with regard to a turbine axis, and a locking plate arranged between the respective blade root and a base of the rotor blade retaining slot, for securing rotor blades against displacement along the rotor blade retaining slot, the locking plate being fixed on the turbine disk by folds and comprising: a plurality of cooling air holes, and two tongues which are arranged for sealing in such a manner that the two tongues are connected to the two grooves of the respective blade root in a form-fitting manner; and a cooling air feed passage leading to the base of the rotor blade retaining slot for feed of a cooling medium, wherein the cooling air holes of the locking plate provide a passage for the cooling medium.