Patent ID: 9234463
Filing Date: 2016-01-12
CPC Classification: F01D,F02C,F04D

Claim Text:
1. A thermal management system for a gas turbine engine comprising: means for delivering a first stream of cooling air to at least one forward cavity for controlling disk temperature and shaft temperature; means for allowing said first stream of cooling air to exit said at least one forward cavity; means for delivering a second stream of cooling air to at least one aft cavity for providing disk web cooling; and means for mixing said first stream of cooling air exiting said at least one forward cavity with an intershaft flow of cooling air, wherein said at least one forward cavity comprises a plurality of forward cavities formed by a plurality of disks, hubs and an outer diameter of a shaft and said at least one aft cavity comprises a plurality of aft cavities formed by a plurality of disks and the outer diameter of said shaft.