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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.:
NETL (National Energy Technology Laboratory, Pittsburgh, PA, and 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) NETL
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. Tue . "Turbine seal assembly". United States. doi:. 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 = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Apr 16 00:00:00 EDT 2013},
month = {Tue Apr 16 00:00:00 EDT 2013}
}

Patent:

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