Interface ring for gas turbine fuel nozzle assemblies
Abstract
A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.
- Inventors:
- Issue Date:
- Research Org.:
- SIEMENS ENERGY, INC., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1243328
- Patent Number(s):
- 9291102
- Application Number:
- 13/226,529
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2011 Sep 07
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Fox, Timothy A., and Schilp, Reinhard. Interface ring for gas turbine fuel nozzle assemblies. United States: N. p., 2016.
Web.
Fox, Timothy A., & Schilp, Reinhard. Interface ring for gas turbine fuel nozzle assemblies. United States.
Fox, Timothy A., and Schilp, Reinhard. Tue .
"Interface ring for gas turbine fuel nozzle assemblies". United States. https://www.osti.gov/servlets/purl/1243328.
@article{osti_1243328,
title = {Interface ring for gas turbine fuel nozzle assemblies},
author = {Fox, Timothy A. and Schilp, Reinhard},
abstractNote = {A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {3}
}
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