Gas-path leakage seal for a gas turbine
Abstract
A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a gas turbine (such as combustor casing segments). The seal includes a generally imperforate foil-layer assemblage which is generally impervious to gas and is located in the leakage-gap. The seal also includes a cloth-layer assemblage generally enclosingly contacting the foil-layer assemblage. In one seal, the first edge of the foil-layer assemblage is left exposed, and the foil-layer assemblage resiliently contacts the first member near the first edge to reduce leakage in the "plane" of the cloth-layer assemblage under conditions which include differential thermal growth of the two members. In another seal, such leakage is reduced by having a first weld-bead which permeates the cloth-layer assemblage, is attached to the metal-foil-layer assemblage near the first edge, and unattachedly contacts the first member.
- Inventors:
-
- Schenectady, NY
- Troy, NY
- New Lebanon, NY
- Issue Date:
- Research Org.:
- General Electric Co., Boston, MA (United States)
- OSTI Identifier:
- 870382
- Patent Number(s):
- 5509669
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02K - JET-PROPULSION PLANTS
- DOE Contract Number:
- AC21-93MC30244
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- gas-path; leakage; seal; gas; turbine; sealing; leakage-gap; spaced-apart; combustor; casing; segments; imperforate; foil-layer; assemblage; impervious; located; cloth-layer; enclosingly; contacting; edge; left; exposed; resiliently; contacts; near; reduce; plane; conditions; differential; thermal; growth; reduced; weld-bead; permeates; attached; metal-foil-layer; unattachedly; thermal growth; differential thermal; gas turbine; gas-path leakage; combustor casing; leakage seal; gas-path leakage-gap; casing segments; /277/415/
Citation Formats
Wolfe, Christopher E, Dinc, Osman S, Bagepalli, Bharat S, Correia, Victor H, and Aksit, Mahmut F. Gas-path leakage seal for a gas turbine. United States: N. p., 1996.
Web.
Wolfe, Christopher E, Dinc, Osman S, Bagepalli, Bharat S, Correia, Victor H, & Aksit, Mahmut F. Gas-path leakage seal for a gas turbine. United States.
Wolfe, Christopher E, Dinc, Osman S, Bagepalli, Bharat S, Correia, Victor H, and Aksit, Mahmut F. Mon .
"Gas-path leakage seal for a gas turbine". United States. https://www.osti.gov/servlets/purl/870382.
@article{osti_870382,
title = {Gas-path leakage seal for a gas turbine},
author = {Wolfe, Christopher E and Dinc, Osman S and Bagepalli, Bharat S and Correia, Victor H and Aksit, Mahmut F},
abstractNote = {A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a gas turbine (such as combustor casing segments). The seal includes a generally imperforate foil-layer assemblage which is generally impervious to gas and is located in the leakage-gap. The seal also includes a cloth-layer assemblage generally enclosingly contacting the foil-layer assemblage. In one seal, the first edge of the foil-layer assemblage is left exposed, and the foil-layer assemblage resiliently contacts the first member near the first edge to reduce leakage in the "plane" of the cloth-layer assemblage under conditions which include differential thermal growth of the two members. In another seal, such leakage is reduced by having a first weld-bead which permeates the cloth-layer assemblage, is attached to the metal-foil-layer assemblage near the first edge, and unattachedly contacts the first member.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1996},
month = {1}
}