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Title: Vertically oriented seal system for gas turbine vanes

Abstract

A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.

Inventors:
;
Publication Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1735259
Patent Number(s):
10,774,665
Application Number:
16/050,008
Assignee:
General Electric Company (Schenectady, NY)
DOE Contract Number:  
FE0024006
Resource Type:
Patent
Resource Relation:
Patent File Date: 07/31/2018
Country of Publication:
United States
Language:
English

Citation Formats

Greene, John Ellington, and Sarawate, Neelesh Nandkumar. Vertically oriented seal system for gas turbine vanes. United States: N. p., 2020. Web.
Greene, John Ellington, & Sarawate, Neelesh Nandkumar. Vertically oriented seal system for gas turbine vanes. United States.
Greene, John Ellington, and Sarawate, Neelesh Nandkumar. 2020. "Vertically oriented seal system for gas turbine vanes". United States. https://www.osti.gov/servlets/purl/1735259.
@article{osti_1735259,
title = {Vertically oriented seal system for gas turbine vanes},
author = {Greene, John Ellington and Sarawate, Neelesh Nandkumar},
abstractNote = {A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.},
doi = {},
url = {https://www.osti.gov/biblio/1735259}, journal = {},
number = ,
volume = ,
place = {United States},
year = {2020},
month = {9}
}

Works referenced in this record:

Turbine vane assembly including a low ductility vane
patent, October 2002


Turbine nozzle assembly
patent, June 2013


Turbine vane collar seal
patent, May 2006


Ceramic matrix composite vane seals
patent, October 2009


Ceramic matrix composite turbine engine vane
patent, June 2012


Multi-ply seal ring
patent, November 2019


CMC vane assembly apparatus and method
patent, October 2012