F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
170/71
F01D 5/08 (2006.01)
Patent
CA 1113009
GAS TURBINE ENGINE AND MEANS FOR COOLING SAME Abstract The turbine blades of a gas turbine engine are individually cooled through the internal circulation of a fluid coolant by the thermosiphon principle. Each turbine blade has associated therewith a closed-loop coolant passageway which is rotatable with the turbine rotor disk and which, in one embodiment, passes through a heat exchanger borne by, and rotatable with, a rotatable lubrication duct. The blade internal coolant is placed in heat exchange relationship with engine lubrication oil within the heat exchanger. The heated lubrication oil is then placed in heat exchange relationship with the engine fuel and the fuel thus heated is burned in the combustor, thereby returning at least a portion of the heat removed from the turbine blades to the engine power cycle. The cooling system is designed for simplified blade removal and replacement and the entire turbine can be removed from the engine as a sealed unit. A secondary cooling system is provided as a backup in the unlikely event that cooling effectiveness of one or more of the blade coolant loop passageways is lost.
310429
Corsmeier Robert J.
Rauf James P.
Company General Electric
Eckersley Raymond A.
LandOfFree
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