Low thermal stress ceramic turbine nozzle
Abstract
A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and is attached to conventional metallic components, the metallic components having 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 an outer shroud and an inner shroud having a plurality of vanes there between. Each of the plurality of vanes have a device for heating and cooling a portion of each of the plurality of vanes. Furthermore, the inner shroud has a plurality of bosses attached thereto. A cylindrical member has a plurality of grooves formed therein and each of the plurality of bosses are positioned in corresponding ones of the plurality of grooves. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component. 4 figs.
- Inventors:
- Issue Date:
- Research Org.:
- Solar Turbines Inc
- OSTI Identifier:
- 201506
- Patent Number(s):
- 5494402
- Application Number:
- PAN: 8-242,792
- Assignee:
- Solar Turbines Inc., San Diego, CA (United States)
- DOE Contract Number:
- AC02-92CE40960
- Resource Type:
- Patent
- Resource Relation:
- Other Information: PBD: 27 Feb 1996
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; NOZZLES; DESIGN; CERAMICS; METALS; JOINTS; THERMAL EXPANSION; HEAT TRANSFER
Citation Formats
Glezer, B, Bagheri, H, and Fierstein, A R. Low thermal stress ceramic turbine nozzle. United States: N. p., 1996.
Web.
Glezer, B, Bagheri, H, & Fierstein, A R. Low thermal stress ceramic turbine nozzle. United States.
Glezer, B, Bagheri, H, and Fierstein, A R. Tue .
"Low thermal stress ceramic turbine nozzle". United States.
@article{osti_201506,
title = {Low thermal stress ceramic turbine nozzle},
author = {Glezer, B and Bagheri, H and Fierstein, A R},
abstractNote = {A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and is attached to conventional metallic components, the metallic components having 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 an outer shroud and an inner shroud having a plurality of vanes there between. Each of the plurality of vanes have a device for heating and cooling a portion of each of the plurality of vanes. Furthermore, the inner shroud has a plurality of bosses attached thereto. A cylindrical member has a plurality of grooves formed therein and each of the plurality of bosses are positioned in corresponding ones of the plurality of grooves. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component. 4 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1996},
month = {2}
}