United Technologies Corporation

Annette M Pighetti

John W Magowan

Richard J Pawlaczyk

Lawrence A Seidel

Richard A Schwarz, Jr

An airfoil for a gas turbine engine, having an airfoil portion with a leading and a trailing edge, includes dual pressure source cooling. The trailing edge of the airfoil includes an internal trailing edge passage and the leading edge includes an internal leading edge passage. Compressor bleed air at higher pressure is channeled through the leading edge passage whereas compressor bleed air at lower pressure is channeled through the trailing edge passage. The higher internal pressure in the leading edge ensures that the inward flow of products of combustion does not occur.

Airfoil with dual source cooling

A turbine vane for a gas turbine engine core adaptable to be operated in a variety of thrust regimes is disclosed. Various construction details are developed which provide cooling to an inner platform of the turbine vane. In one particular embodiment, a turbine vane includes a hollow core permitting cooling fluid to pass through the vane and an inner platform having a pocket disposed therein, the pocket being in fluid communication with the core. Heat is exchanged between the platform and the cooling fluid within the pocket. Cooling holes extend between the pocket and a flow surface of a platform to provide cooling of the flow surface.

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Andover, CT, United States of America

Annette M Pighetti