A system, comprising: a turbine fuel nozzle, comprising: a hub having an axis; a shroud surrounding the hub along the axis; an air flow path between the hub and the shroud; a fuel flow path; and a swirl vane (32, 160, 380) extending between the hub and the shroud in a radial direction relative to the axis, wherein the swirl vane (32, 160, 380) comprises a fuel inlet (72, 170, 396) coupled to the fuel flow path, a fuel chamber (34, 162, 342, 394) extending from the fuel inlet (72, 170, 396), and a plurality of fuel outlets extending from the fuel chamber (34, 162, 342, 394) to the air flow path, wherein the plurality of fuel outlets is positioned at an axial distance (86, 184, 402) of between 55 and 100 percent of an axial length (88, 404) of the fuel chamber (34, 162, 342, 394) downstream from an upstream point (94, 186, 226, 268, 406) along an upstream edge (74, 172, 344, 398) of the fuel chamber (34, 162, 342, 394), characterized in that the upstream edge (74, 172, 344, 398) extends away from the fuel inlet (72, 170, 396) at an angle in a downstream direction of fuel flow from the fuel inlet (72, 170, 396). a turbine fuel nozzle, comprising: a hub having an axis; a shroud surrounding the hub along the axis; an air flow path between the hub and the shroud; a fuel flow path; and a swirl vane (32, 160, 380) extending between the hub and the shroud in a radial direction relative to the axis, wherein the swirl vane (32, 160, 380) comprises a fuel inlet (72, 170, 396) coupled to the fuel flow path, a fuel chamber (34, 162, 342, 394) extending from the fuel inlet (72, 170, 396), and a plurality of fuel outlets extending from the fuel chamber (34, 162, 342, 394) to the air flow path, wherein the plurality of fuel outlets is positioned at an axial distance (86, 184, 402) of between 55 and 100 percent of an axial length (88, 404) of the fuel chamber (34, 162, 342, 394) downstream from an upstream point (94, 186, 226, 268, 406) along an upstream edge (74, 172, 344, 398) of the fuel chamber (34, 162, 342, 394), characterized in that the upstream edge (74, 172, 344, 398) extends away from the fuel inlet (72, 170, 396) at an angle in a downstream direction of fuel flow from the fuel inlet (72, 170, 396). a hub having an axis; a shroud surrounding the hub along the axis; an air flow path between the hub and the shroud; a fuel flow path; and a swirl vane (32, 160, 380) extending between the hub and the shroud in a radial direction relative to the axis, wherein the swirl vane (32, 160, 380) comprises a fuel inlet (72, 170, 396) coupled to the fuel flow path, a fuel chamber (34, 162, 342, 394) extending from the fuel inlet (72, 170, 396), and a plurality of fuel outlets extending from the fuel chamber (34, 162, 342, 394) to the air flow path, wherein the plurality of fuel outlets is positioned at an axial distance (86, 184, 402) of between 55 and 100 percent of an axial length (88, 404) of the fuel chamber (34, 162, 342, 394) downstream from an upstream point (94, 186, 226, 268, 406) along an upstream edge (74, 172, 344, 398) of the fuel chamber (34, 162, 342, 394), characterized in that the upstream edge (74, 172, 344, 398) extends away from the fuel inlet (72, 170, 396) at an angle in a downstream direction of fuel flow from the fuel inlet (72, 170, 396).