Symmetric fuel injection for turbine combustor
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United States of America Patent
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Jun 23, 2015
Grant Date -
Jul 11, 2013
app pub date -
Jan 9, 2012
filing date -
Jan 9, 2012
priority date (Note) -
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Abstract
A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.
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