Patent ID: 7555892

Claim:
A cooling system for a gas turbine, comprising: an annular duct extending axially along a compressor portion of a rotor; at least one ring of a plurality of compressor guide blades fastened fixedly in terms of rotation, the compressor guide blades comprising: a securable blade root on which a blade profile and, following the latter, a blade head are formed; at least one cooling-air extraction point, arranged on the rotor, for diverting a cooling-air stream into a cooling-duct system arranged in the rotor and with a turbine unit; and at least one ring of moving blades fastened to a rotor disk of the rotor are provided, where each ring of moving blades is associated with one ring of compressor guide blades in each case, wherein when the gas turbine is in operation, components subjected to thermal stress by a hot gas cooled are by the divertible cooling-air stream, and also with a feed line for feeding a liquid into the cooling-air stream, the feed line having at least one orifice for the outlet of the liquid such that the feed line extends with a subduct through at least one of the compressor guide blades of the ring, and the orifice for the outlet of the liquid is connected in the region of the cooling-air extraction point, wherein the rotor has at least two directly adjacent rotor disks, between which is provided a radially outwardly open disk interspace, into which the blade heads of the compressor guide blades of the ring project.