United Technologies Corporation

David Michael Kontrovitz

Edward F Pietraszkiewicz

Dominic J Mongillo, Jr

James Preston Downs

Frank J Cunha

Bret M Teller

Jeffrey R Levine

Young H Chon

Takao Fukuda

Norman F Roeloffs

An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air onto a suction wall. The supplemental film cooling channel air is generally directed to a location on the suction wall that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.

Airfoil with supplemental cooling channel adjacent leading edge

A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.

Turbine blade trailing edge construction

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Manchester, CT, United States of America

David Michael Kontrovitz