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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 being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being 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 therebetween. 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.

Inventors:
 [1];  [2];  [2]
  1. Del Mar, CA
  2. San Diego, CA
Issue Date:
Research Org.:
Solar Turbines Inc
OSTI Identifier:
870312
Patent Number(s):
5494402
Assignee:
Solar Turbines Incorporated (San Diego, CA)
DOE Contract Number:  
AC02-92CE40960
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
thermal; stress; ceramic; turbine; nozzle; vane; assembly; preestablished; rate; expansion; positioned; gas; engine; attached; conventional; metallic; components; outer; shroud; inner; plurality; vanes; therebetween; device; heating; cooling; portion; furthermore; bosses; thereto; cylindrical; grooves; formed; therein; corresponding; ones; provides; economical; reliable; effective; component; nozzle vane; attached thereto; turbine nozzle; outer shroud; assembly provides; metallic components; ceramic component; thermal stress; formed therein; preestablished rate; turbine engine; thermal expansion; gas turbine; vane assembly; inner shroud; metallic component; conventional metallic; ceramic turbine; grooves formed; corresponding ones; conventional metal; /415/

Citation Formats

Glezer, Boris, Bagheri, Hamid, and Fierstein, Aaron R. Low thermal stress ceramic turbine nozzle. United States: N. p., 1996. Web.
Glezer, Boris, Bagheri, Hamid, & Fierstein, Aaron R. Low thermal stress ceramic turbine nozzle. United States.
Glezer, Boris, Bagheri, Hamid, and Fierstein, Aaron R. Mon . "Low thermal stress ceramic turbine nozzle". United States. https://www.osti.gov/servlets/purl/870312.
@article{osti_870312,
title = {Low thermal stress ceramic turbine nozzle},
author = {Glezer, Boris and Bagheri, Hamid and Fierstein, Aaron R},
abstractNote = {A turbine nozzle vane 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 having a preestablished rate of thermal expansion being 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 therebetween. 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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1996},
month = {1}
}

Patent:

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