Combustion section for a turbine engine
A combustion section for a turbine engine. The combustion section has a wall and a fuel nozzle. The wall at least partially forms a combustion chamber. The fuel nozzle opens to the combustion chamber through the wall. The fuel nozzle has a fuel nozzle body and a swirler. The fuel nozzle body defines a central channel. The swirler is provided within the central channel.
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.