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Title: Low thermal stress ceramic turbine nozzle

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:
OSTI Identifier:
201506
Assignee:
Solar Turbines Inc., San Diego, CA (United States) CHO; SCA: 330103; PA: EDB-96:053381; SN: 96001551771
Patent Number(s):
US 5,494,402/A/
Application Number:
PAN: 8-242,792
Contract Number:
AC02-92CE40960
Resource Relation:
Other Information: PBD: 27 Feb 1996
Research Org:
Solar Turbines Inc
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; NOZZLES; DESIGN; CERAMICS; METALS; JOINTS; THERMAL EXPANSION; HEAT TRANSFER