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Title: Ceramic turbine nozzle

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:
OSTI Identifier:
415724
Assignee:
Solar Turbines Inc., San Diego, CA (United States) CHO; SCA: 421000; PA: EDB-97:016040; SN: 97001714606
Patent Number(s):
US 5,584,652/A/
Application Number:
PAN: 8-369,245
Contract Number:
AC02-92CE40960
Resource Relation:
Other Information: PBD: 17 Dec 1996
Research Org:
Solar Turbines Inc
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

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