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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 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}
}

Works referenced in this record:

Gas-path leakage seal for a gas turbine
patent, August 1997


Gas-path leakage seal for a turbine
patent, August 1999


Interstage van seal apparatus
patent, June 2000


Removable inner turbine shell with bucket tip clearance control
patent, July 2000


Seal apparatus for rotary machines
patent, November 2001


Supplemental seal for the chordal hinge seal in a gas turbine
patent, August 2003


Supplemental seal for the chordal hinge seal in a gas turbine
patent, October 2003


Seal assembly
patent, March 2011


Gas turbine having a sealing structure
patent-application, October 2006


Gas turbine and sealing means for a gas turbine
patent-application, February 2007


Reducing Inter-Seal Gap In Gas Turbine
patent-application, September 2010


Transition Piece Sealing Assembly
patent-application, May 2012


Cloth Seal For Turbo-Machinery
patent-application, May 2012


Assembly And Method For Preventing Fluid Flow
patent-application, July 2012


Assembly For Preventing Fluid Flow
patent-application, July 2012


Sealing Device And Method For Providing A Seal In A Turbine System
patent-application, August 2012