Method and apparatus for combusting fuel within a gas turbine engine

A nozzle for channeling a fluid into a combustor assembly. The nozzle includes a body including a centerline, a first passageway extending through the body along the centerline, and a nozzle tip coupled to a downstream end of the first passageway. The nozzle tip has a radius extending from a center of the nozzle tip to an outer surface of the nozzle tip. The nozzle tip includes a downstream face, and a plurality of outlet passageways that each include an opening defined in the downstream face. Each opening includes respective X-, Y-, and Z-axes defined with respect to a tangent line, the radius, and the centerline. Each of the plurality of outlet passageways is at discharge angle of greater than 30° measured with respect to the respective Z-axis in a respective X-Z plane.