High shear swirler with recessed fuel filmer for a gas turbine engine

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.

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.

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.

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.