Siemens Energy, Inc.

Joseph B Gilliam

George P Liang

Zhihong Gao

Brian J Wessell

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling region formed from endwall cooling channels having a higher density of cooling channels than other areas in order to cool the material forming the intersection between the trailing edge of the airfoil and the endwall to prevent premature cracking. The increased density of cooling channels in the endwall at the trailing edge forms a heat sink that draws heat from the airfoil, thereby lowering the temperature of the airfoil and increasing the useful life of the airfoil.

Turbine airfoil cooling system with high density section of endwall cooling channels

A vane assembly for a gas turbine engine including an endwall and an airfoil extending from the endwall. An inner rail extends radially inwardly of the endwall, and an overhang portion extends axially from a location of the inner rail to a downstream edge. A recess cavity is defined in the overhang portion between the inner rail and the downstream edge. The recess cavity extends radially into the overhang portion and defines a cavity surface. A plurality of grooves extend radially into the cavity surface and have an elongated dimension extending in a direction from the inner rail toward the downstream edge. A plurality of cooling passages extend axially through the overhang portion, and are located between the grooves.

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Deltona, FL, United States of America

Joseph B Gilliam