Abstract: A fuel injector assembly for a combustor of a gas turbine engine includes an annular body defining a hollow interior space, first and second openings to the interior space, and a chamber defining a fluid manifold. The first and second openings are respectively proximate opposite first and second ends of the annular body. The first end is upstream of the second end. The fuel injector assembly includes an annular fuel nozzle positioned in the interior space and spaced from the annular body. The annular fuel nozzle includes a plurality of fuel injection ports configured for injecting a fuel into the combustor. The fuel injector assembly also includes one or more fuel supply struts coupled to the annular fuel nozzle and the annular body. The fuel supply struts are coupled in fluid communication with the fluid manifold and the annular fuel nozzle for channeling a fuel therethrough.