Patent ID: 6227801
Filing Date: 2001-05-08
Classification: F01D,F02C,Y02T,Y10T

Abstract:
A turbine engine comprising:a compressor section to compress intake air into high pressure air and intermediate pressure air, said intermediate pressure air having a lower pressure and temperature than said high pressure air and formed upstream of said high pressure air in said compressor;a combustion section in flow communication with said compressor section, to combust fuel with compressed air;a turbine section in flow communication with combustion gases from said combustion section, said turbine section comprising a rotating turbine blade wherein static pressure at said turbine blade is lower than the pressure of said intermediate pressure air; anda conduit having an inlet in flow communication with said intermediate pressure air and an outlet in flow communication with said turbine blade, thereby guiding said intermediate pressure air to said turbine blade to cool said turbine blade.