Patent ID: 8517676

Claim:
A coolable gas turbine compressor rotor ( 1 ) comprising a multiplicity of welded-together rotor disks ( 3 a , 3 b , 4 , 5 ), wherein each rotor disk ( 3 a , 3 b , 4 , 5 ) extends over at least three blade stages and of which at least two rotor disks ( 3 a , 3 b ) are arranged axially next to each other and at a last and second from last point of the rotor ( 1 ) in a flow direction, the rotor disks ( 3 a , 3 b ) have a central region ( 9 ) which encompasses the rotational axis ( 2 ) of the rotor ( 1 ) and extends radially outward from the rotational axis ( 2 ), and the rotor disks ( 3 a , 3 b ) have a radially outer region ( 9 ′) which encompasses the radially outer surface of the rotor and extends radially inward, and for discharging heat from a central region ( 9 ) of the last two rotor disks ( 3 a , 3 b ) in the flow direction, the last two rotor disks ( 3 a , 3 b ) in the flow direction are abutment-joined together in their central region ( 9 ) and are welded together in a radially outer region ( 9 ′) of the rotor disks ( 3 a , 3 b ) and an annulus (H″) extends between the central region ( 9 ) and the radially outer region ( 9 ′) of the last two rotor disks ( 3 a , 3 b ) in the flow direction, and the last of the two abutment-joined rotor disks ( 3 a , 3 b ) in the flow direction has on a radially outer surface a recess ( 7 ) which can be cooled by means of an externally supplied cooling medium and which extends over a periphery of the rotor disk.