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Title: Static seal for turbine engine

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:
OSTI Identifier:
1129073
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
Patent Number(s):
8,684,673
Application Number:
12/791,968
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2010 Jun 02
Research Org:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Works referenced in this record: