CUPPED CONTOUR FOR GAS TURBINE ENGINE BLADE ASSEMBLY

摘要

A method of forming an endwall (64) with a contour includes casting an endwall (64) with at least one cooling channel (84) having an opening from the endwall (84), and covering the opening with a cupped contour (80) formed on the endwall (64). A gas turbine engine blade assembly (60) includes an endwall (64) with a plurality of cooling channels (84), an airfoil (68) extending radially from the endwall (64) to a tip (76), and a cupped contour (80) formed on the endwall (64) to provide a cooling chamber (96) between the cupped contour (80) and a radially facing surface of the endwall (64).