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Title: 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):
5,494,402
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}
}