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Title: Method and system to facilitate sealing in gas turbines

A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
Inventors:
; ;
Issue Date:
OSTI Identifier:
1390171
Assignee:
General Electric Company NETL
Patent Number(s):
9,759,081
Application Number:
14/049,020
Contract Number:
FC26-05NT42643
Resource Relation:
Patent File Date: 2013 Oct 08
Research Org:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

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