Patent ID: 8438851

Claim:
A fuel nozzle assembly for use with a turbine engine, said fuel nozzle assembly comprising: a plurality of fuel nozzles positioned within an air plenum defined by a casing, each of said plurality of fuel nozzles coupled to a combustion liner defining a combustion chamber, each of said plurality of fuel nozzles comprises: a housing comprising a sidewall extending between a forward endwall and an opposite aft endwall, said sidewall comprising an inner surface that defines a cooling fluid plenum and a fuel plenum therein, said sidewall comprising at least one opening extending through said inner surface of said sidewall; and a plurality of mixing tubes extending through said housing, wherein each of said mixing tubes comprises an inner surface defining a flow channel extending between the air plenum and the combustion chamber, at least one mixing tube of said plurality of mixing tubes comprises at least one cooling fluid aperture for channeling a flow of cooling fluid from said cooling fluid plenum to said flow channel; and at least one cooling conduit coupled to said sidewall such that said at least one sidewall opening couples said cooling conduit in flow communication with said cooling fluid plenum for channeling a flow of cooling fluid to said cooling fluid plenum.