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Title: Turbine nozzle positioning system

A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine. 9 figs.
Authors:
;
Publication Date:
OSTI Identifier:
187061
Report Number(s):
US 5,487,642/A/
PAN: US patent application 8-262,179
DOE Contract Number:
AC02-92CE40960
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 30 Jan 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; POSITIONING; SUPPORTS; SHAFT GUIDES; DESIGN; ALIGNMENT; COMBUSTION CHAMBERS