Active clearance control

Claim 1

An active clearance control system for a twin spool gas turbine power plant operating over an engine operating envelope including a cruise mode having a plurality of stages of axial flow compressors defining the high pressure compressor spool and the low pressure compressor spool powering aircraft, each compresor stage having a stator including circumferentially spaced vanes, a disc supporting a plurality of compressor blades and an outer air seal, said compressor stages rotatably supported in an engine case to a shaft supported by bearings, said bearings being in proximity to the entrance of the high pressure spool of said compressor stages, means for selectively bleeding air from separate compressor stages in the high pressure compressor spool, and means including an external conduit and tube means for leading said bled air into the bore of said high pressure spool, through an opening in the engine's casing, a hollow stator vane in the low pressure compressor spool, through said bearing and said high pressure spool shaft and means responsive to engine operating parameters for controlling said selective bleeding means so as to introduce air into said bore from the hottest stage of said bleeding stages during the cruise mode of said power plant.