Interface ring for gas turbine fuel nozzle assemblies
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United States of America Patent
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Mar 22, 2016
Grant Date -
Mar 7, 2013
app pub date -
Sep 7, 2011
filing date -
Sep 7, 2011
priority date (Note) -
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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.
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