Combustor for a gas turbine engine

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 forward liner segment;
• an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber;
• one or more dilution slots extending in the radial direction and defined between the forward liner segment and the aft liner segment;
• and
• a moveable interface configured to couple the forward liner segment and the aft liner segment, the moveable interface comprising one or more windows located radially outward, with respect to the longitudinal centerline, of the forward liner segment and the aft liner segment, wherein the one or more windows are configured to communicate cooling medium from radially outward of the combustor, through the one or more dilution slots, and into to the combustion chamber.