DUAL INTERSTAGE COOLED ENGINE

摘要

A gas turbine engine (10) includes a compressor (18), combustor (20), and high pressure turbine (22) operatively joined together. A first interstage bleed circuit (56) is joined in flow communication between a first preultimate stage (5) of the compressor (18) and hollow blades (44) in the turbine (22) to provide thereto pressurized primary air. A second interstage bleed circuit (58) is joined in flow communication between a second preultimate stage (3) of the compressor (18) and the turbine blades (44) to provide thereto pressurized secondary air at a lower pressure than the primary air.