Turbine blade internal cooling configuration

Turbine blade internal cooling configuration

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 co...

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Hauptverfasser: Pinero, Sandra S, Pietraszkiewicz, Edward F, Dube, Bryan P, Yee, Stephen J, Levy, Ryan Shepard, Hassan, Mohamed, Valerio, Domenico, Hartmann, Scott D
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Sprache:eng
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creator Pinero, Sandra S
Pietraszkiewicz, Edward F
Dube, Bryan P
Yee, Stephen J
Levy, Ryan Shepard
Hassan, Mohamed
Valerio, Domenico
Hartmann, Scott D
description 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.
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title Turbine blade internal cooling configuration
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