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Title: 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):
9,291,102
Application Number:
13/226,529
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL)
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}
}

Patent:

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