Fuel nozzle for a combustor of a gas turbine engine
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United States of America Patent
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Mar 22, 2016
Grant Date -
Jun 5, 2014
app pub date -
Dec 5, 2012
filing date -
Dec 5, 2012
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Abstract
A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
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