COMBUSTOR FOR A GAS TURBINE ENGINE OF AN AIRCRAFT WITH A SPALL PLATE AND METHOD FOR PRODUCING A COMBUSTOR FOR A GAS TURBINE ENGINE OF AN AIRCRAFT

A combustor (140) may comprise an outer wall (164) defining, at least, a portion of a combustion chamber (142). A dilution chute (180) may extend from an interior surface (182) of the outer wall (164). A support structure (190) may extend between the dilution chute and the interior surface of the outer wall. A spall plate (200) may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet (162) of the combustion chamber.