Patent Number: 8,821,114

Title: Gas turbine engine sealing structure

Abstract: A turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct. A vane carrier located around the gas duct, and sealing elements extend radially between circumferentially extending grooves in the vane carrier and respective grooves in the flow path components. The sealing elements include radially inner and outer edges, and at least one axially facing side defining a chamfered portion extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.

Inventors: Afanasiev; Gennadiy (Windermere, FL), Strain; John N. (Tequesta, FL), Sunshine; Robert W. (Hobe Sound, FL), Barker; Robert D. (Hobe Sound, FL)

Assignee: Siemens Energy, Inc.

International Classification: F01D 11/00 (20060101)

Expiration Date: 9/02/12018