Combustor for a gas turbine engine

A liner for a combustion chamber of a gas turbine engine, the combustion chamber defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the liner comprising:

• a forward liner segment and an aft liner segment disposed downstream from the forward liner segment:
• a dilution opening in the liner that directs an airflow therethrough into the combustion chamber;
• and
• a fence coupled to the aft liner segment downstream of the dilution opening, the fence directly coupled to an inner surface of the aft liner segment and including a flange that extends axially along the inner surface of the liner and a radially extending portion extending radially inward toward the longitudinal centerline from a radially outer end of the radially extending portion at the flange and axially positioned at the dilution opening such that the fence guides the airflow from the dilution opening into the combustion chamber, the fence being coupled to the aft liner segment at the flange.