United Technologies Corporation

Raytheon Technologies Corporation

Dipanjan Saha

Thomas N Slavens

Brooks E Snyder

A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

Cupped contour for gas turbine engine blade assembly

An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.

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New Milford, CT, United States of America

Dipanjan Saha