System and method for improved engine cooling

Details System and method for improved engine cooling System and method for improved engine cooling

F - Mech Eng,Light,Heat,Weapons

01

P

F01P 1/00 (2006.01) F01D 5/08 (2006.01)

Patent

CA 2076120

13DV-10766 THE ABSTRACT OF THE DISCLOSURE A method and system for cooling a gas turbine engine. The gas turbine engine has a multi-stage compressor which discharges compressor discharge air for expansion by a combustor. A cavity which is aerodynamically linked to a turbine stage on its downstream end is forced by a metal structure the upstream end of which is connected to a seal which prevents compressor discharge air from entering the cavity. A conduit links an intermediate stage of the multi-stage compressor to the cavity for purposes of cooling the cavity and the turbine stage components located downstream of the cavity.

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