Combustion section for a turbine engine

A combustion section for a turbine engine, the combustion section comprising:

• a wall at least partially forming a combustion chamber;
• and
• a fuel nozzle that opens to the combustion chamber through the wall, the fuel nozzle configured to deliver hydrogen fuel to the combustion chamber and comprising:
• a fuel nozzle body defining a central channel exhausting into the combustion chamber at a fuel nozzle outlet;
• and
• a swirler provided within the central channel, the swirler having a body centerline and a helical vane extending from the body centerline, the helical vane wrapped circumferentially about the body centerline greater than or equal to π/2 radians between a first end and a second end, axially opposing the first end, of the helical vane, wherein the swirler is a first swirler included in a set of swirlers, the first swirler including the helical vane, the helical vane being a first helical vane wrapped in a first circumferential direction, with respect to the body centerline, the body centerline being a first body centerline of the first swirler;
• and
• a second swirler, separate from the first swirler, includes a second helical vane wrapped in a second circumferential direction, opposite the first circumferential direction, with respect to a second body centerline of the second swirler, wherein the fuel nozzle includes an interior wall extending through the central channel and splitting the central channel into a first swirler channel and a second swirler channel, the first swirler being provided within the first swirler channel and the second swirler being provided within the second swirler channel.