Fuel nozzle for gas turbine
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United States of America Patent
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Apr 26, 2016
Grant Date -
Jun 12, 2014
app pub date -
Dec 6, 2012
filing date -
Dec 6, 2012
priority date (Note) -
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Abstract
A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining a first fuel passage, a second fluid conduit defining a second fuel passage, and a third fluid conduit defining an oxidant passage. A first plurality of orifices is disposed along the first fluid conduit and is configured to fluidly couple the first fuel passage to the oxidant passage. A second plurality of orifices is disposed on the third fluid conduit and is configured to fluidly couple the second fuel passage to the oxidant passage. A first diameter of the first plurality of orifices is less than a second diameter of the second plurality of orifices.
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