Turbine vane cooling

Details Turbine vane cooling Turbine vane cooling

F - Mech Eng,Light,Heat,Weapons

02

C

170/70

F02C 7/18 (2006.01) F01D 5/08 (2006.01)

Patent

CA 1045040

TURBINE VANE COOLING ABSTRACT OF THE INVENTION A method and apparatus for providing high pressure cooling air to the turbine vanes of a gas turbine engine is disclosed. A centrifugal compressor stage is interposed in the flow path of cooling air to the turbine vanes. The centrifugal compres- sor stage raises the pressure of the cooling air to a value substantially greater than the pressure of the combustion gases entering the turbine. The availability of high pressure cooling air allows the incorporation of improved cooling systems in the turbine vanes. Increasingly effective cooling systems are necessary to the continued development of low pressure drop combustion chambers which discharge high temper- ature gases to the inlet of the turbine. -1-

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