Patent ID: 6672075
Filing Date: 2004-01-06
Classification: F01D,F02C,F05D,Y02T

Abstract:
A liquid cooling system in a gas turbine including a compressor section having a compressor drum and compressor blades, a combustion section fluidly coupled to said compressor section, a turbine rotor and a turbine stator, said turbine rotor having a rotor shaft, at least one rotor disk on said rotor shaft, and rotor blades arranged on said at least one rotor disk, comprising:a tank having an inlet and an outlet and containing a cooling liquid therein, a coolant pump coupled to said tank to extract said cooling liquid therefrom for forced circulation of said cooling liquid through said at least one rotor disk and said rotor blades, and a heat exchanger fluidly coupled by an inlet thereof to said at least one rotor disk and said rotor blades, and by an output thereof to said tank for cooling said liquid returning from said at least one rotor disk and said rotor blades and for supplying said cooled liquid to said tank, said tank, said coolant pump, and said heat exchanger being incorporated into said turbine rotor.