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:
- Publication Date:
- Research Org.:
- Solar Turbines Inc
- OSTI Identifier:
- 119040
- Patent Number(s):
- US 5,459,995/A/
- 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. 1995.
"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 = {},
url = {https://www.osti.gov/biblio/119040},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Oct 24 00:00:00 EDT 1995},
month = {Tue Oct 24 00:00:00 EDT 1995}
}