United Technologies Corporation

Stephen J Yee

Brandon W Spangler

Edward F Pietraszkiewicz

Bryan P Dube

Russell J Bergman

Mohamed Hassan

Joseph W Bridges, Jr

Leonard A Bach

Ryan Shepard Levy

Sandra S Pinero

Lawrence J Willey

Scott D Hartmann

Domenico Valerio

A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.

Turbine blade internal cooling configuration

Growing community of inventors

Manchester, CT, United States of America

Stephen J Yee