United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Vincent E Simms

Steven Bruce Gautschi

Nicholas M LoRicco

Shawn M McMahon

Christopher Whitfield

Richard M Salzillo

Justin M Aniello

Thomas Allwood

Jeffery Scott Hembree, Sr

Mark A Boeke

Mosheshe Camara-Khary Blake

Kevin Rajchel

Sr Jeffery Scott Hembree

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

An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Chordal seal

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Bloomfield, CT, United States of America

Vincent E Simms