Combustion section for a turbine engine

1 . 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 fuel nozzle includes a fuel channel extending through a portion of the swirler, the fuel channel including a fuel orifice opening into the central channel and being provided along the swirler,

wherein the helical vane includes at least two helical vanes and the fuel orifice includes a set of fuel orifices, with each second end of the at least two helical vanes having at least one fuel orifice of the set of fuel orifices.

2 . The combustion section of claim 1 , wherein the at least two helical vanes form at least a double helix.

3 . The combustion section of claim 2 , wherein the second end of a first vane of the at least two helical vanes is axially spaced an axial distance, with respect to the body centerline, from the second end of a second vane of the at least two helical vanes.

4 . The combustion section of claim 2 , wherein the first end and the second end of a first helical vane of the at least two helical vanes axially corresponds to the first end and the second end of a second helical vane of the at least two helical vanes.

5 . The combustion section of claim 1 , wherein the at least one fuel orifice of the set of fuel orifices is provided along the second end of the at least two helical vanes.

6 . The combustion section of claim 1 , wherein the set of fuel orifices includes a fuel orifice provided along a portion of the helical vane axially between the first end and the second end.

7 . The combustion section of claim 1 , wherein the set of fuel orifices includes a fuel orifice provided along the body centerline.

8 . The combustion section of claim 1 , wherein:

the swirler is a first swirler included in a set of swirlers, the first swirler including the helical vane, the at least two helical vanes 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.

9 . The combustion section of claim 8 , wherein the first swirler is provided downstream the second swirler.

10 . The combustion section of claim 8 , wherein the first swirler is provided radially adjacent to the second swirler, with respect to the first body centerline of the first swirler.

11 . The combustion section of claim 1 , wherein the swirler includes a vortex generator provided along one of the at least two helical vanes.

12 . The combustion section of claim 1 , wherein the swirler converges radially inward, with respect to the body centerline, from an upstream portion and to a downstream portion of the swirler.

13 . The combustion section of claim 1 , wherein the fuel nozzle body includes a nozzle centerline, and the swirler is axially offset from or coincides with the fuel nozzle outlet.

14 . The combustion section of claim 1 , wherein the swirler terminates at the fuel nozzle outlet.

15 . The combustion section of claim 1 , wherein the swirler is moveable.

16 . 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.

17 . The combustion section of claim 16 , wherein the interior wall extends into the central channel to the fuel nozzle outlet.

18 . The combustion section of claim 16 , wherein the first swirler is configured to direct a flow of compressed air in a first circumferential direction, and wherein the second swirler is configured to direct a flow of compressed air in a second circumferential direction, opposite the first circumferential direction.