Turbine blade internal cooling configuration

US8172533B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Sandra S. Pinero · Middletown, US
• Edward F. Pietraszkiewicz · Southington, US
• Bryan P. Dube · Wallingford, US
• Stephen J. Yee · Manchester, US
• Ryan Shepard Levy · Middletown, US
• Mohamed Hassan · Berlin, DE
• Domenico Valerio · Waterbury, US
• Scott D. Hartmann · Tolland, US

Key dates

• Filing date: May 14, 2008
• Grant date: May 8, 2012
• Expiry date: Mar 9, 2031

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

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.