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Title: Turbine seal assembly

Abstract

A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members.

Inventors:
Publication Date:
Research Org.:
National Energy Technology Laboratory (NETL), Pittsburgh, PA, Morgantown, WV (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1083775
Patent Number(s):
8,419,356
Application Number:
12/416,423
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Little, David A. Turbine seal assembly. United States: N. p., 2013. Web.
Little, David A. Turbine seal assembly. United States.
Little, David A. 2013. "Turbine seal assembly". United States. https://www.osti.gov/servlets/purl/1083775.
@article{osti_1083775,
title = {Turbine seal assembly},
author = {Little, David A.},
abstractNote = {A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members.},
doi = {},
url = {https://www.osti.gov/biblio/1083775}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Apr 16 00:00:00 EDT 2013},
month = {Tue Apr 16 00:00:00 EDT 2013}
}

Works referenced in this record:

Device for sealing gas turbine stator blades
patent, April 2001


Rim seal for turbine wheel
patent, April 1996


Gas turbine shroud and platform seal system
patent, October 1999


Gap control system for turbine engines
patent, June 2007


Air sealing for turbomachines
patent, January 1984


Gas turbine seal apparatus
patent, February 2001


Turbine nozzle backflow inhibitor
patent, October 1994


Sealing apparatus for gas turbine
patent, November 2000