Ceramic blade with tip seal
Abstract
The present gas turbine engine includes a disc assembly defining a disc having a plurality of blades attached thereto. The disc has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc. A shroud assembly is attached to the gas turbine engine and is spaced from the plurality of blades a preestablished distance forming an interface there between. Positioned in the interface is a seal having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades. 4 figs.
- Inventors:
- Issue Date:
- Research Org.:
- Solar Turbines Inc
- Sponsoring Org.:
- USDOE, Washington, DC (United States)
- OSTI Identifier:
- 516915
- Patent Number(s):
- 5653579
- Application Number:
- PAN: 8-555,686
- Assignee:
- Solar Turbines Inc., San Diego, CA (United States)
- DOE Contract Number:
- AC21-93MC30246
- Resource Type:
- Patent
- Resource Relation:
- Other Information: PBD: 5 Aug 1997
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 03 NATURAL GAS; 33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; TURBINE BLADES; SEALS; CERAMICS; THERMAL EXPANSION; EQUIPMENT INTERFACES
Citation Formats
Glezer, B, Bhardwaj, N K, and Jones, R B. Ceramic blade with tip seal. United States: N. p., 1997.
Web.
Glezer, B, Bhardwaj, N K, & Jones, R B. Ceramic blade with tip seal. United States.
Glezer, B, Bhardwaj, N K, and Jones, R B. Tue .
"Ceramic blade with tip seal". United States.
@article{osti_516915,
title = {Ceramic blade with tip seal},
author = {Glezer, B and Bhardwaj, N K and Jones, R B},
abstractNote = {The present gas turbine engine includes a disc assembly defining a disc having a plurality of blades attached thereto. The disc has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc. A shroud assembly is attached to the gas turbine engine and is spaced from the plurality of blades a preestablished distance forming an interface there between. Positioned in the interface is a seal having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades. 4 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Aug 05 00:00:00 EDT 1997},
month = {Tue Aug 05 00:00:00 EDT 1997}
}
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