A cooled shroud assembly for a turbine engine comprising: a turbine stator outer wall; a stator retainer disposed radially outward from the turbine stator outer wall; a shroud segment spaced axially apart from the turbine stator outer wall and the stator retainer; a shroud carrier disposed radially outwardly from the shroud segment; a recirculation cavity formed between the turbine stator outer wall and the shroud segment, the recirculation cavity configured to recirculate a flow therein, said recirculation cavity positioned radially outward from a hot gas flow path through said turbine engine; at least one dilution jet opening formed in the shroud segment and in flow communication with said recirculation cavity; and an angled slot positioned radially inward from said recirculation cavity and formed between said turbine stator outer wall and a leading edge of the shroud segment, said angled slot in flow communication with said recirculation cavity and said hot gas flow path, characterized by: said recirculation cavity being further formed between said turbine stator outer wall and said shroud carrier, said recirculation cavity including a hot ingestion gas zone cavity positioned radially outward from said hot gas flow path and directing at least a portion of gas from the hot gas flow path therein, a cool upper zone cavity in flow communication with said hot ingestion gas zone cavity, and at least one warm middle zone cavity positioned between and in flow communication with said hot ingestion gas zone cavity and said cool upper zone cavity. a turbine stator outer wall; a stator retainer disposed radially outward from the turbine stator outer wall; a shroud segment spaced axially apart from the turbine stator outer wall and the stator retainer; a shroud carrier disposed radially outwardly from the shroud segment; a recirculation cavity formed between the turbine stator outer wall and the shroud segment, the recirculation cavity configured to recirculate a flow therein, said recirculation cavity positioned radially outward from a hot gas flow path through said turbine engine; at least one dilution jet opening formed in the shroud segment and in flow communication with said recirculation cavity; and an angled slot positioned radially inward from said recirculation cavity and formed between said turbine stator outer wall and a leading edge of the shroud segment, said angled slot in flow communication with said recirculation cavity and said hot gas flow path, characterized by: said recirculation cavity being further formed between said turbine stator outer wall and said shroud carrier, said recirculation cavity including a hot ingestion gas zone cavity positioned radially outward from said hot gas flow path and directing at least a portion of gas from the hot gas flow path therein, a cool upper zone cavity in flow communication with said hot ingestion gas zone cavity, and at least one warm middle zone cavity positioned between and in flow communication with said hot ingestion gas zone cavity and said cool upper zone cavity. said recirculation cavity being further formed between said turbine stator outer wall and said shroud carrier, said recirculation cavity including a hot ingestion gas zone cavity positioned radially outward from said hot gas flow path and directing at least a portion of gas from the hot gas flow path therein, a cool upper zone cavity in flow communication with said hot ingestion gas zone cavity, and at least one warm middle zone cavity positioned between and in flow communication with said hot ingestion gas zone cavity and said cool upper zone cavity.