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Title: Turbine nozzle positioning system

Abstract

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.

Inventors:
;
Issue Date:
Research Org.:
Solar Turbines Inc
OSTI Identifier:
187061
Patent Number(s):
5,487,642
Application Number:
PAN: 8-262,179
Assignee:
Solar Turbines Inc., San Diego, CA (United States)
DOE Contract Number:  
AC02-92CE40960
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 30 Jan 1996
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

Citation Formats

Norton, P F, and Shaffer, J E. Turbine nozzle positioning system. United States: N. p., 1996. Web.
Norton, P F, & Shaffer, J E. Turbine nozzle positioning system. United States.
Norton, P F, and Shaffer, J E. Tue . "Turbine nozzle positioning system". United States.
@article{osti_187061,
title = {Turbine nozzle positioning system},
author = {Norton, P F and Shaffer, J E},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1996},
month = {1}
}