Methods and apparatus for injecting fluids into a turbine engine

A nozzle tip for a turbine engine fuel nozzle, said nozzle tip comprising:

• an annular body having a centerline extending therethrough, said annular body comprising:
• at least one pilot fuel outlet configured to discharge only pilot fuel from said nozzle tip;
• a plurality of steam outlets configured to discharge steam from said nozzle tip, said plurality of steam outlets spaced circumferentially about said at least one pilot fuel outlet;
• and
• a plurality of primary fuel outlets configured to discharge primary fuel from said nozzle tip, said plurality of primary fuel outlets circumferentially aligned with said plurality of steam outlets, said plurality of primary fuel outlets configured to discharge primary fuel at a first oblique angle with respect to the centerline to facilitate mixing the primary fuel with the steam.

A gas turbine engine comprising:

• a combustor;
• and
• a fuel nozzle for injecting fluids into said combustor, said nozzle comprising:
• a nozzle tip comprising an annular body having a centerline, said nozzle tip in flow communication with said combustor, said nozzle tip further comprising:
• at least one pilot fuel outlet configured to discharge only pilot fuel from said nozzle tip;
• a plurality of steam outlets configured to discharge steam from said nozzle tip, said plurality of steam outlets spaced circumferentially about said at least one pilot fuel outlet;
• and
• a plurality of primary fuel outlets configured to discharge primary fuel from said nozzle tip, said plurality of primary fuel outlets circumferentially aligned with said plurality of steam outlets, said plurality of primary fuel outlets configured to discharge primary fuel at a first oblique angle with respect to the centerline to facilitate mixing the primary fuel with the steam.