United Technologies Corporation

Raytheon Technologies Corporation

Thomas Allwood

Steven Bruce Gautschi

Nicholas M LoRicco

Christopher Whitfield

Shawn M McMahon

Richard M Salzillo

Justin M Aniello

Vincent E Simms

Jeffery Scott Hembree, Sr

Sr Jeffery Scott Hembree

A coolable airfoil for a gas turbine engine includes a suction side wall that extends from a leading edge to a trailing edge. A pressure side wall is joined to the suction side wall at the leading edge and the trailing edge and spaced from the suction side wall to form a cavity therein that includes a cooling circuit with a plurality of serpentine cooling passages. A cooling air inlet passage receives cooling air from a plenum formed between an outer platform and an engine case and routes the received cooling air from the plenum to the cooling circuit. The coolable airfoil may also include a cooling air feed elbow that includes a metering input orifice that receives compressor first discharge air that provides the received compressor first discharge air to a feed elbow cavity and is redirected via a feed elbow outlet passage to the cooling circuit.

Vane airfoil cooling air communication

A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Turbine vane cooling arrangement

A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

Doublet vane assembly for a gas turbine engine

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Manchester, CT, United States of America

Thomas Allwood