Patent ID: 8113001

Claim:
A secondary fuel nozzle for a gas turbine comprising: a fuel manifold coupled with a plurality of annular fuel passages; and a tubular fuel injector in fluid communication with the fuel manifold and disposed surrounding the plurality of annular fuel passages, the tubular fuel injector comprising a plurality of axially oriented air slots and a plurality of fuel injection holes disposed between the plurality of air slots, wherein the plurality of fuel injection holes are oriented such that fuel from the fuel manifold is injected in at least a radial direction to mix with air flowing through the plurality of air slots, wherein at least one of the plurality of fuel injection holes is oriented axially such that fuel from the fuel manifold is injected in an axial direction to mix with the air flowing through the plurality of air slots, wherein the tubular fuel injector comprises an end surface at a distal axial end, and wherein the at least one axially oriented fuel injection hole is disposed in the end surface.