High shear swirler for gas turbine engine

A fuel injector assembly for a gas turbine engine, comprising:

• a swirler configured with an outer wall having a swirler outer wall (SOW) inner wall surface, and an inner wall having a swirler inner wall (SIW) inner wall surface and a SIW outer wall surface, an outer passage defined at least in part by the SIW outer wall surface and the SOW inner wall surface, and an inner passage defined in part by the SIW inner wall surface;
• wherein the outer wall and the inner wall having a center axis;
• wherein the SIW inner wall surface includes a first section and a second section, and the first section extends between a first airflow inlet and the second section, and the second section extends between the first section and a distal end wall of the inner wall, wherein the first section tapers radially inward toward the center axis in a conical configuration at a first angle relative to the center axis, and the second section tapers radially away from the center axis;
• wherein the outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall of the inner wall is axially recessed within the swirler from the distal outer wall end;
• and
• a fuel nozzle projecting into the inner passage;
• and
• wherein the second section is disposed at an angle beta relative to the center axis, wherein the angle beta is in the range of greater than zero degrees and an angle at which a line contiguous with the second section is tangential to an inner edge of the distal outer wall end.