United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gerald M Mace

Tania Bhatia Kashyap

Jeffrey R Levine

Ky H Vu

Eleanor D Kaufman

Lisa P O'Neill

Jeffrey Leon

Richard N Allen

Takao Fukuda

Andrew P Boursy

Gregory Anselmi

Daniel C Nadeau

Christina E Botnick

Andy Turko

Lynn M Boy

John David Forbes

A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

Turbine vane assembly

An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Gas turbine engine airfoil platform edge geometry

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Wallingford, CT, United States of America

Gerald M Mace