Patent ID: 7096674
Filing Date: 2006-08-29
Classification: F02C,F05D,F23R,Y02T

Abstract:
1. A gas turbine engine having a longitudinal centerline axis therethrough, comprising: (a) a fan section at a forward end of said gas turbine engine including at least a first fan blade row connected to a first drive shaft; (b) a booster compressor positioned downstream of and in at least partial flow communication with said fan section including a plurality of stages, each said stage including a stationary compressor blade row and a rotating compressor blade row connected to said first drive shaft and interdigitated with said stationary compressor blade row; (c) a core system positioned downstream of said booster compressor, said core system further comprising: (d) a low pressure turbine positioned downstream of and in flow communication with said core system, said low pressure turbine being utilized to power said first drive shaft; wherein a first source of compressed air having a predetermined pressure is provided to said combustion system inlet and a second source of compressed air having a pressure greater than said first source of compressed air is provided to cool said combustion system.