Combustor for a gas turbine engine

A liner for a combustor of a gas turbine engine, the gas turbine engine 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:

• an annular body comprising a forward liner segment and an aft liner segment configured to at least partially define a combustion chamber of the combustor, wherein the annular body comprises a dilution slot extending to the combustion chamber;
• one or more guides integral with the annular body, wherein at least one guide of the one or more guides defines a scooped surface extending radially outward from an axially forwardmost end of the aft liner segment, the scooped surface formed to redirect cooling medium into the dilution slot;
• and
• a fence extending radially inward from the axially forwardmost end of the aft liner segment into the combustion chamber through the dilution slot,
• wherein the fence and the scooped surface are axially spaced from an axially aftmost end of the forward liner segment by the dilution slot.

A combustor for a gas turbine engine, the gas turbine engine 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 combustor comprising:

• a liner comprising a forward liner segment and an aft liner segment at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber;
• a scooped interface integral with the liner and configured to redirect cooling medium into the dilution slot, the scooped interface defining a scooped surface extending radially outward from an axially forwardmost end of the aft liner segment, the scooped surface configured to form a film of airflow into the combustor through the dilution slot;
• and
• a fence extending radially inward from the axially forwardmost end of the aft liner segment into the combustion chamber through the dilution slot, wherein the fence and the scooped surface are axially spaced from an axially aftmost end of the forward liner segment by the dilution slot.