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Title: Method and system to facilitate sealing in gas turbines

Abstract

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:
; ;
Publication Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1390171
Patent Number(s):
9,759,081
Application Number:
14/049,020
Assignee:
General Electric Company NETL
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Oct 08
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Morgan, Victor John, Foster, Gregory Thomas, and Sarawate, Neelesh Nandkumar. Method and system to facilitate sealing in gas turbines. United States: N. p., 2017. Web.
Morgan, Victor John, Foster, Gregory Thomas, & Sarawate, Neelesh Nandkumar. Method and system to facilitate sealing in gas turbines. United States.
Morgan, Victor John, Foster, Gregory Thomas, and Sarawate, Neelesh Nandkumar. 2017. "Method and system to facilitate sealing in gas turbines". United States. doi:. https://www.osti.gov/servlets/purl/1390171.
@article{osti_1390171,
title = {Method and system to facilitate sealing in gas turbines},
author = {Morgan, Victor John and Foster, Gregory Thomas and Sarawate, Neelesh Nandkumar},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = 2017,
month = 9
}

Patent:

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