Patent ID: 7870743

Claim:
A gas turbine engine comprising: a fan, compressor, combustor, high pressure (HP) turbine, and low pressure turbine in serial flow communication; said compressor including rows of compressor blades for pressurizing air sequentially in corresponding stages; said HP turbine including a nozzle having a row of stator vanes followed by a row of rotor blades; each of said vanes having circumferentially opposite pressure and suction sides extending in span radially and in chord axially between opposite leading and trailing edges, and being hollow with an imperforate septum bridging said opposite sides to define forward and aft cooling channels feeding corresponding first cooling holes along said leading edge and second cooling holes along said trailing edge; a first bleed circuit joined in flow communication between a last stage of said compressor and said vane forward channels to provide thereto pressurized primary air at a first pressure; and a second bleed circuit joined in flow communication between an intermediate stage of said compressor and said vane aft channels to provide thereto pressurized secondary air at a second pressure less than said first pressure.