skip to main content
DOE Patents title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Turbine nozzle attachment system

Abstract

A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and is attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine. 3 figs.

Inventors:
;
Issue Date:
Research Org.:
Solar Turbines Inc
OSTI Identifier:
119040
Patent Number(s):
5,459,995
Application Number:
PAN: 8-265,863
Assignee:
Solar Turbines Inc., San Diego, CA (United States)
DOE Contract Number:  
AC02-92CE40960
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 24 Oct 1995
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; NOZZLES; FASTENING; FASTENERS; SUPPORTS; ALIGNMENT

Citation Formats

Norton, P F, and Shaffer, J E. Turbine nozzle attachment system. United States: N. p., 1995. Web.
Norton, P F, & Shaffer, J E. Turbine nozzle attachment system. United States.
Norton, P F, and Shaffer, J E. Tue . "Turbine nozzle attachment system". United States.
@article{osti_119040,
title = {Turbine nozzle attachment 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 is attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine. 3 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1995},
month = {10}
}