초록 ▼

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 ra

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.

대표청구항 ▼

1. 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; anda swirl vane extending between the hub and the shroud in a radial direction relative to the axis, wherein

1. 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; anda swirl vane extending between the hub and the shroud in a radial direction relative to the axis, wherein the swirl vane comprises 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, wherein the plurality of fuel outlets is positioned at an axial distance of between 55 and 100 percent of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber, wherein the upstream edge extends radially away from the fuel inlet over a total radial distance, wherein at least half of the total radial distance of the upstream edge is oriented at an acute angle away from the radial direction between the hub and the shroud. 2. The system of claim 1, wherein the fuel flow path extends along the hub to the swirl vane. 3. The system of claim 1, wherein the fuel flow path extends along the shroud to the swirl vane. 4. The system of claim 1, wherein the upstream point is disposed adjacent the fuel inlet into the fuel chamber. 5. The system of claim 1, wherein the acute angle is between 5 and 60 degrees relative to the radial direction, and the total radial distance of the upstream edge is oriented at the acute angle away from the radial direction between the hub and the shroud. 6. The system of claim 1, wherein the acute angle of the upstream edge extends radially away from the fuel inlet gradually in a downstream direction of fuel flow from the fuel inlet. 7. The system of claim 6, wherein the upstream edge is a tapered edge that tapers linearly in the radial direction between the hub and the shroud. 8. The system of claim 6, wherein the upstream edge is a curved edge that curves in the radial direction between the hub and the shroud. 9. The system of claim 6, wherein the acute angle is at least approximately 30 degrees relative to the radial direction. 10. The system of claim 1, wherein the plurality of fuel outlets has a staggered arrangement in the radial direction. 11. The system of claim 1, wherein the plurality of fuel outlets progressively changes in size in the radial direction. 12. The system of claim 1, comprising a turbine combustor or a turbine engine having the turbine fuel nozzle. 13. The system of claim 1, wherein the plurality of fuel outlets is positioned at the axial distance of greater than or equal to approximately ⅔ of the axial length of the fuel chamber downstream from the upstream point along the upstream edge of the fuel chamber. 14. A system, comprising: a fuel nozzle, comprising: a hub having an axis;a shroud disposed about the hub;an air flow path between the hub and the shroud;a fuel flow path; anda vane disposed between the hub and the shroud, wherein the vane comprises a fuel inlet coupled to the fuel flow path, a fuel chamber coupled to the fuel inlet and extending between the hub and the shroud, and a plurality of fuel outlets coupled to the fuel chamber between the hub and the shroud, wherein an upstream edge of the fuel chamber extends radially away from the fuel inlet over a total radial distance, wherein at least half of the total radial distance of the upstream edge is oriented at an acute angle away from a radial direction between the hub and the shroud. 15. The system of claim 14, wherein all of the plurality of fuel outlets are offset by at least a minimum distance from a minimum pressure point of a recirculation zone in the fuel chamber, and the minimum distance is configured to increase uniformity of fuel flow through the plurality of fuel outlets. 16. The system of claim 14, wherein all of the plurality of fuel outlets are positioned at an axial distance of between 55 and 100 percent of an axial length of the fuel chamber downstream from an upstream point along the upstream edge of the fuel chamber. 17. The system of claim 14, wherein an axial length of the fuel chamber changes from a first axial length at the hub to a second axial length at the shroud, wherein the first and second axial lengths are different from one another, wherein a shorter one of the first and second axial lengths is less than 75 percent of a longer one of the first and second axial lengths. 18. The system of claim 14, wherein the acute angle of the upstream edge extends radially away from the fuel inlet gradually in a downstream direction of fuel flow from the fuel inlet. 19. The system of claim 14, wherein the upstream edge is a tapered edge that tapers linearly in the radial direction between the hub and the shroud. 20. The system of claim 14, wherein the upstream edge is a curved edge that curves in the radial direction between the hub and the shroud. 21. A system, comprising: a fuel nozzle swirl vane, comprising: an exterior extending about an axis from a leading edge to a trailing edge relative to an air flow path;an interior fuel chamber having an upstream edge facing the leading edge and a downstream edge facing the trailing edge;a fuel inlet into the interior fuel chamber adjacent the upstream edge; anda plurality of fuel outlets extending from the interior fuel chamber to the exterior, wherein the plurality of fuel outlets is positioned at a distance of between 55 and 100 percent of a length of the interior fuel chamber downstream from an upstream point along the upstream edge of the fuel chamber, wherein the upstream edge extends radially away from the fuel inlet over a total radial distance, wherein at least half of the total radial distance of the upstream edge is oriented at an acute angle away from a radial direction between opposite sides of the fuel nozzle swirl vane, the radial direction is relative to the axis along the fuel nozzle swirl vane, and the acute angle is oriented gradually in a downstream direction away from the fuel inlet. 22. The system of claim 21, wherein the upstream edge of the interior fuel chamber is acutely angled relative to the leading edge of the exterior in the radial direction between the opposite sides of the fuel nozzle swirl vane. 23. The system of claim 21, wherein all of the plurality of fuel outlets are offset by at least a minimum distance from a minimum pressure point of a recirculation zone in the interior fuel chamber, and the minimum distance is configured to increase uniformity of fuel flow through the plurality of fuel outlets.