Patent ID: 7306435

Claim:
A rotor of a turbo machine, in particular a gas turbine rotor, having a rotor base body wherein the rotor base body has a plurality of axial grooves extending in an axial direction and/or in a direction of flow and having a plurality of rotor blades, each rotor blade being anchored in an axial groove of the rotor base body by a blade footing and the rotor blades being secured in an anchored position in the rotor base body to prevent displacement in the axial direction by means of locking plates, which are guided in ring grooves of the rotor base body and the rotor blades, wherein the locking plates have a diamond-like outline, in particular resembling a parallelogram or a rhombus, such that in an insertion position, the locking plates are insertable between the rotor base body and the rotor blades and in an installation position are rotated with respect to the insertion position, and wherein the locking plates are rotatable into the ring grooves of the rotor base body and the rotor blades.