Static seal for turbine engine
Abstract
A seal structure for a gas turbine engine, the seal structure including first and second components located adjacent to each other and forming a barrier between high and low pressure zones. A seal cavity is defined in the first and second components, the seal cavity extending to either side of an elongated gap extending generally in a first direction between the first and second components. A seal member is positioned within the seal cavity and spans across the elongated gap. The seal member includes first and second side edges extending into each of the components in a second direction transverse to the first direction, and opposing longitudinal edges extending between the side edges generally parallel to the first direction. The side edges include a groove formed therein for effecting a reduction of gas flow around the seal member at the side edges.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1129073
- Patent Number(s):
- 8684673
- Application Number:
- 12/791,968
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2010 Jun 02
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Salazar, Santiago, and Gisch, Andrew. Static seal for turbine engine. United States: N. p., 2014.
Web.
Salazar, Santiago, & Gisch, Andrew. Static seal for turbine engine. United States.
Salazar, Santiago, and Gisch, Andrew. Tue .
"Static seal for turbine engine". United States. https://www.osti.gov/servlets/purl/1129073.
@article{osti_1129073,
title = {Static seal for turbine engine},
author = {Salazar, Santiago and Gisch, Andrew},
abstractNote = {A seal structure for a gas turbine engine, the seal structure including first and second components located adjacent to each other and forming a barrier between high and low pressure zones. A seal cavity is defined in the first and second components, the seal cavity extending to either side of an elongated gap extending generally in a first direction between the first and second components. A seal member is positioned within the seal cavity and spans across the elongated gap. The seal member includes first and second side edges extending into each of the components in a second direction transverse to the first direction, and opposing longitudinal edges extending between the side edges generally parallel to the first direction. The side edges include a groove formed therein for effecting a reduction of gas flow around the seal member at the side edges.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Apr 01 00:00:00 EDT 2014},
month = {Tue Apr 01 00:00:00 EDT 2014}
}
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