Rim seal arrangement having pumping feature
Abstract
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:
- Research Org.:
- Siemens Energy, Inc. Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1353070
- Patent Number(s):
- 9,631,509
- Application Number:
- 14/946,893
- Assignee:
- Siemens Energy, Inc.
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2015 Nov 20
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Lee, Ching-Pang, and Myers, Caleb. Rim seal arrangement having pumping feature. United States: N. p., 2017.
Web.
Lee, Ching-Pang, & Myers, Caleb. Rim seal arrangement having pumping feature. United States.
Lee, Ching-Pang, and Myers, Caleb. Tue .
"Rim seal arrangement having pumping feature". United States. https://www.osti.gov/servlets/purl/1353070.
@article{osti_1353070,
title = {Rim seal arrangement having pumping feature},
author = {Lee, Ching-Pang and Myers, Caleb},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2017},
month = {4}
}
Works referenced in this record:
Air cooled turbine for a gas turbine engine
patent, September 1982
- Campbell, David; Morley, Frederick
- US Patent Document 4,348,157
Coverplate deflectors for redirecting a fluid flow
patent, March 2007
- Marini, Remo; Sreekanth, Sri
- US Patent Document 7,189,055
Outer rim seal assembly in a turbine engine
patent, January 2015
- Lee, Ching-Pang; Tham, Kok-Mun; Shivanand, Manjit
- US Patent Document 8,939,711
Aft outer rim seal arrangement
patent, April 2015
- Lee, Ching-Pang; Tham, Kok-Mun; Schroeder, Eric
- US Patent Document 9,017,014
Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
patent, May 2015
- Lee, Ching-Pang
- US Patent Document 9,039,357
Seal assembly including grooves in an inner shroud in a gas turbine engine
patent, June 2015
- Lee, Ching-Pang
- US Patent Document 9,068,513
Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
patent, November 2015
- Lee, Ching-Pang; Tham, Kok-Mun; Schroeder, Eric
- US Patent Document 9,181,816
Outer rim seal assembly in a turbine engine
patent, February 2016
- Lee, Ching-Pang; Tham, Kok-Mun; Shivanand, Manjit
- US Patent Document 9,260,979