Patent ID: 7926289

Claim:
A gas turbine engine comprising: a fan, compressor, combustor, high pressure (HP) turbine and low pressure (LP) turbine in serial flow communication; said compressor including rows of compressor blades for pressurizing air sequentially in corresponding stages; said HP turbine including a single stage row of hollow rotor blades mounted in corresponding dovetail slots in the perimeter of a supporting rotor disk; said LP turbine including a row of hollow first stage LP vanes following said HP blades; a first interstage bleed circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in a first preultimate stage of said compressor to said HP blades inboard of said combustor; and a second interstage bleed circuit joined in flow communication between a second preultimate stage of said compressor and said HP blades outboard of said combustor and through said LP vanes.