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Title: Rim seal arrangement having pumping feature

A rim seal arrangement for a gas turbine engine includes a first seal face on a rotor component, and a second seal face on a stationary annular rim centered about a rotation axis of the rotor component. The second seal face is spaced from the first seal face along an axial direction to define a seal gap. The seal gap is located between a radially outer hot gas path and a radially inner rotor cavity. The first seal face has a plurality of circumferentially spaced depressions, each having a depth in an axial direction and extending along a radial extent of the first seal face. The depressions influence flow in the seal gap such that during rotation of the rotor component, fluid in the seal gap is pumped in a radially outward direction to prevent ingestion of a gas path fluid from the hot gas path into the rotor cavity.
Inventors:
;
Issue Date:
OSTI Identifier:
1353070
Assignee:
Siemens Energy, Inc. NETL
Patent Number(s):
9,631,509
Application Number:
14/946,893
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2015 Nov 20
Research Org:
Siemens Energy, Inc. Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Other works cited in this record:

Air cooled turbine for a gas turbine engine
patent, September 1982

Coverplate deflectors for redirecting a fluid flow
patent, March 2007

Outer rim seal assembly in a turbine engine
patent, January 2015

Aft outer rim seal arrangement
patent, April 2015

Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
patent, May 2015

Seal assembly including grooves in an inner shroud in a gas turbine engine
patent, June 2015

Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
patent, November 2015

Outer rim seal assembly in a turbine engine
patent, February 2016

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