Liquid cooling system for gas turbines
AssigneeUniversity of Maryland
InventorsConstantin Sandu, Dan Brasoveanu
Life of this patent
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Abstract
Cooling systems with liquid for gas turbine engines use the relative motion of the engine stator with respect to the rotor for actuating the coolant pump. The cooling system is completely encapsulated within the engine rotor. The cooling system includes a tank containing the cooling liquid, a coolant pump coupled to the tank to extract the cooling liquid from the tank, a system of ducts and channels extending in the rotor shaft, and rotor disks and rotor blades, where the heat exchanger is positioned either in the compressor drum, or in the end of compressor section.
Claims15
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.
Dependencies are inferred from the claim text.