Interface ring for gas turbine fuel nozzle assemblies

Fox, Timothy A.; Schilp, Reinhard

Title: Interface ring for gas turbine fuel nozzle assemblies

Patent · Tue Mar 22 00:00:00 EDT 2016

OSTI ID:1243328

Fox, Timothy A.; Schilp, Reinhard

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.

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Research Organization:: SIEMENS ENERGY, INC., Orlando, FL (United States)

Sponsoring Organization:: USDOE

DOE Contract Number:: FC26-05NT42644

Assignee:: SIEMENS ENERGY, INC. (Orlando, FL)

Patent Number(s):: 9,291,102

Application Number:: 13/226,529

OSTI ID:: 1243328

Resource Relation:: Patent File Date: 2011 Sep 07

Country of Publication:: United States

Language:: English

References (17)

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