High shear swirler with recessed fuel filmer for a gas turbine engine
An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.
1. An assembly for a turbine engine, comprising:
a swirler configured with an outer wall, an inner wall, an outer passage and an inner passage;
the outer wall circumscribing the inner wall and extending axially along an axis to a distal outer wall end;
the inner wall extending axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end;
the outer passage formed by and radially between the inner wall and the outer wall;
the inner passage formed by and radially within the inner wall; and
a fuel nozzle projecting into the inner passage, the fuel nozzle configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis in an annular array, and the fuel nozzle configured with a central nozzle orifice arranged coaxial with the axis;
wherein the distal outer wall end is disposed a first distance along the axis from a tip of the fuel nozzle;
wherein the distal outer wall end is disposed a second distance along the axis from the distal inner wall end;
wherein the outer passage has a diameter at the distal outer wall end;
wherein a first value is equal to the first distance minus the second distance; and
wherein a quotient of the first value divided by the diameter is less than one.
2. The assembly of claim 1 , wherein the plurality of orifices include a first orifice that is configured to direct a jet of fuel to impinge against the inner wall.
3. The assembly of claim 1 , wherein the quotient is less than or equal to 0.8.
4. The assembly of claim 1 , wherein the quotient is greater than or equal to 0.25.
5. The assembly of claim 1 , wherein the quotient is between 0.35 and 0.68.
6. The assembly of claim 1 , wherein
the swirler includes a first set of vanes and a second set of vanes;
the first set of vanes are arranged with the outer passage; and
the second set of vanes are arranged with the inner passage.
7. The assembly of claim 1 , further comprising a nozzle guide plate mounting the fuel nozzle to the swirler.
8. An assembly for a turbine engine, comprising:
a swirler configured with an outer wall, an inner wall, an outer passage and an inner passage;
the outer wall circumscribing the inner wall and extending axially along an axis to a distal outer wall end;
the inner wall extending axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end;
the outer passage formed by and radially between the inner wall and the outer wall;
the inner passage formed by and radially within the inner wall; and
a fuel nozzle projecting into the inner passage, the fuel nozzle configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis in an annular array, and the fuel nozzle configured with a central nozzle orifice arranged coaxial with the axis;
wherein the distal outer wall end is disposed a distance along the axis from a tip of the fuel nozzle;
wherein the outer passage has a diameter at the distal outer wall end; and
wherein a quotient of the distance divided by the diameter is less than one.
9. The assembly of claim 8 , wherein the quotient is between 0.5 and 0.75.
10. An assembly for a turbine engine, comprising:
a swirler configured with an outer wall, an inner wall, an outer passage and an inner passage;
the outer wall circumscribing the inner wall and extending axially along an axis to a distal outer wall end;
the inner wall extending axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end;
the outer passage formed by and radially between the inner wall and the outer wall;
the inner passage formed by and radially within the inner wall; and
a fuel nozzle projecting into the inner passage, the fuel nozzle configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis in an annular array, and the fuel nozzle configured with a central nozzle orifice arranged coaxial with the axis;
wherein the distal outer wall end is disposed a first distance along the axis from a tip of the fuel nozzle;
wherein the distal outer wall end is disposed a second distance along the axis from the distal inner wall end;
wherein the outer passage has a diameter at the distal outer wall end; and
wherein a quotient of the second distance divided by the diameter is between 0.07 and 0.15.
11. An assembly for a turbine engine, comprising:
a swirler configured with an outer wall, an inner wall, an outer passage and an inner passage;
the outer wall circumscribing the inner wall and extending axially along an axis to a distal outer wall end;
the inner wall extending axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end;
the outer passage formed by and radially between the inner wall and the outer wall;
the inner passage formed by and radially within the inner wall; and
a fuel nozzle projecting into the inner passage, the fuel nozzle configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis in an annular array, and the fuel nozzle configured with a central nozzle orifice arranged coaxial with the axis;
wherein the swirler includes a first set of vanes and a second set of vanes;
wherein the first set of vanes are arranged with the outer passage;
wherein the second set of vanes are arranged with the inner passage;
wherein the swirler further includes a third set of vanes arranged with the inner passage; and
wherein the third set of vanes are axially offset from the second set of vanes.
12. A fuel injector assembly with an axis, comprising:
a swirler configured with an outer wall, an inner wall, an outer passage and an inner passage;
the outer wall extending circumferentially about the inner wall and extending axially along the axis to a distal outer wall end;
the inner wall extending axially along the axis to a distal inner wall end;
the outer passage radially between the inner wall and the outer wall;
the inner passage radially within the inner wall; and
a fuel nozzle projecting into the inner passage;
wherein the distal outer wall end is disposed a first distance along the axis from a tip of the fuel nozzle, the distal outer wall end is disposed a second distance along the axis from the distal inner wall end, and the outer passage has a diameter at the distal outer wall end;
wherein a first value is equal to the first distance minus the second distance;
wherein a quotient of the first value divided by the diameter is less than one; and
wherein the quotient is between 0.35 and 0.68.
13. The fuel injector assembly of claim 12 , wherein the fuel nozzle is configured with a plurality of orifices that are axially overlapped by the inner wall and arranged circumferentially about the axis.