Interstage cooled turbine engine

Details Interstage cooled turbine engine Interstage cooled turbine engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/16 (2006.01) F01D 5/08 (2006.01) F01D 25/12 (2006.01) F02C 9/18 (2006.01)

Patent

CA 2607654

A gas turbine engine (10) includes a compressor (18), combustor (20), and high pressure (HP) turbine (22) operatively joined together. An interstage cooling circuit (48) is joined in flow communication from an intermediate stage (3,5) of the compressor (18) to a forward face (50) of an HP disk (46) supporting a row of turbine blades (44) for channeling interstage bleed cooling air thereto.

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