Patent ID: 7743613
Filing Date: 2010-06-29
Classification: F01D,F02C,Y02T

Abstract:
1. A gas turbine engine comprising: a fan, compressor, combustor, high pressure turbine, and low pressure turbine disposed in serial flow communication; said compressor including rows of compressor blades for pressurizing air sequentially in corresponding stages; said HP turbine including a row of hollow nozzle vanes having forward and aft internal cooling channels followed by a row of hollow rotor blades having forward and aft internal cooling channels; and first, second, third, and fourth bleed circuits joined in flow communication with different stages of said compressor for bleeding pressurized air therefrom at different pressures to provide first and second coolants to said vane forward and aft channels from correspondingly different stages of said compressor, and third and fourth coolants to said blade forward and aft channels, respectively.