In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately ⅔ of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber.