Cooling system for a gas turbine engine

Details Cooling system for a gas turbine engine Cooling system for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

02

C

170/67

F02C 7/12 (2006.01) F01D 5/08 (2006.01) F01D 11/00 (2006.01)

Patent

CA 1062619

AN IMPROVED COOLING SYSTEM FOR A GAS TURBINE ENGINE ABSTRACT OF THE DISCLOSURE A gas turbine engine having cooled rotor blades is shown wherein the coolant is delivered to a stationary chamber adjacent the blades. A portion of the coolant is directed to seals between the stationary structure and the rotor and another portion is directed between adjacent rotor discs for entry through the downstream disc into the blades supported therein. The portion flowing through the seals is prevented from flowing into the fluid directed to the discs. Also, the coolant to the discs is given a velocity vector substantially equal to the velocity vector of the openings through the disc to the blade root to minimize pumping losses and temperature increases in the coolant during its delivery to the blade.

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