Ceramic turbine nozzle
Abstract
A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components have a preestablished rate of thermal expansion greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment, each of the first and second vane segments having a vertical portion, and each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component. 4 figs.
- Inventors:
- Issue Date:
- Research Org.:
- Solar Turbines Inc
- OSTI Identifier:
- 415724
- Patent Number(s):
- 5584652
- Application Number:
- PAN: 8-369,245
- Assignee:
- Solar Turbines Inc., San Diego, CA (United States)
- DOE Contract Number:
- AC02-92CE40960
- Resource Type:
- Patent
- Resource Relation:
- Other Information: PBD: 17 Dec 1996
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; GAS TURBINE ENGINES; NOZZLES; JACKETS; DESIGN; BAFFLES; THERMAL EXPANSION; CERAMICS
Citation Formats
Shaffer, J E, and Norton, P F. Ceramic turbine nozzle. United States: N. p., 1996.
Web.
Shaffer, J E, & Norton, P F. Ceramic turbine nozzle. United States.
Shaffer, J E, and Norton, P F. Tue .
"Ceramic turbine nozzle". United States.
@article{osti_415724,
title = {Ceramic turbine nozzle},
author = {Shaffer, J E and Norton, P F},
abstractNote = {A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components have a preestablished rate of thermal expansion greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment, each of the first and second vane segments having a vertical portion, and each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component. 4 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1996},
month = {12}
}