Fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine

A fuel nozzle for a gas turbine comprising:

• a nozzle body defining a longitudinal axis, a central conduit developing in a direction along the longitudinal axis and an annular conduit developing around the central conduit;
• a radial swirler configured to swirl a first flow of a first oxidant-fuel mixture that flows through the central conduit;
• an axial swirler arranged to swirl a second flow of a second oxidant-fuel mixture that flows through the annular conduit;
• a first shroud defining a downstream end of the central conduit and encompassing the first flow from the radial swirler;
• and
• a second shroud defining a downstream end of the annular conduit and encompassing the second flow from the axial swirler,
• wherein the central conduit and the annular conduit keep the first flow and the second flow separate until both exit at an outlet, and
• wherein the first shroud and the second shroud both terminate at a plane perpendicular to the longitudinal axis.