Cooling system for a gas turbine and method for cooling a gas turbine.

摘要

Cooling system (42) for a gas turbine (1), with a ring of a compressor (5) extending axially along a rotor (3) channel, which are at least provided a crown (15 ) of guide blades of the compressor (14, 28, 33) fixed integrally in rotation and at least one ring (17) rotor-blade (16) attached to a rotor disk (19) of the rotor (3), wherein guidelines compressor (14, 28, 33) blades have in each case one blade root (32) which can be fixed, on which are formed one airfoil (30) and then the same head blade (26) with at least one extraction point cooling air (34) disposed on the rotor (3) for disengaging a stream of cooling air in a system of cooling channels in the rotor (3), and with a drive turbine (8) wherein during operation of the gas turbine (1) components, which applies thermally gas hot (20) can be cooled by an air stream detachably cooling and with a supply conduit (46) for feeding a liquid (45) in the stream of cooling air, having at least one opening (48, 49 ) to let the liquid, wherein the conduit (46) extends with a partial channel (44) through at least one of the driving blades compressor (28, 33) of the crown (15), and the opening (48, 49) to release the liquid (45) is arranged in the region of the removal of cooling air (34).