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}
}
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