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 Co., 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
- 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. 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 = {},
url = {https://www.osti.gov/biblio/1390171},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Sep 12 00:00:00 EDT 2017},
month = {Tue Sep 12 00:00:00 EDT 2017}
}
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