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Fuel nozzle for a combustor of a gas turbine engine

United States Patent

March 22, 2016
View the Complete Patent at the US Patent & Trademark Office
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.
Belsom; Keith Cletus (Laurens, SC), McMahan; Kevin Weston (Greer, SC), Thomas; Larry Lou (Flat Rock, NC)
13/ 705,443
December 5, 2012
FEDERAL RESEARCH STATEMENT This invention was made with Government support under Contract No. DE-FC26-05NT42643, awarded by the Department of Energy. The Government has certain rights in the invention.