Gas turbine cooled shroud assembly with hot gas ingestion suppression

An apparatus for a turbine engine comprising:

• a hot ingestion gas zone cavity positioned radially outward from a hot gas flow path through said turbine engine;
• at least one warm middle zone cavity positioned radially outward from and in flow communication with said hot ingestion gas zone cavity;
• a cool upper zone cavity positioned radially outward from and in flow communication with said at least one warm middle zone cavity;
• an angled slot positioned radially inward from said hot ingestion gas zone cavity, said angled slot in flow communication with said hot ingestion gas zone cavity and said hot gas flow path;
• and
• a plurality of dilution jet openings positioned radially outward from said angled slot and in flow communication with said at least one warm middle zone cavity.

An assembly for a turbine engine comprising:

• a recirculation cavity having a hot ingestion gas zone cavity, a warm middle zone cavity, and a cool upper zone cavity, said recirculation cavity positioned radially outward from a hot gas flow path through said turbine engine;
• a plurality of dilution jet openings positioned aft of and in flow communication with said recirculation cavity;
• and
• an angled slot in flow communication with said recirculation cavity and said hot gas flow path, said angled slot positioned radially inward from said recirculation cavity.

A turbine shroud assembly for a turbine engine having a plurality of airfoils comprising:

• a hot ingestion gas zone cavity positioned radially outward from a hot gas flow path through said turbine engine;
• a warm middle zone cavity positioned radially outward from and in flow communication with said hot ingestion gas zone cavity;
• a cool upper zone cavity positioned radially outward from and in flow communication with said warm middle zone cavity;
• an angled slot positioned radially inward from said hot ingestion gas zone cavity, said angled slot in flow communication with said hot ingestion gas zone cavity and said hot gas flow path, said angled slot having a slot angle between about 200 and about 60°;
• and
• a plurality of dilution jet openings positioned radially outward from said angled slot and in flow communication with said warm middle zone cavity, at least one said dilution jet opening positioned circumferentially in line with a trailing edge wake of each said airfoil, and wherein a distance between a flow exit end of each said dilution jet opening and said hot ingestion gas zone cavity is at least about 0.2 inches.

A method of shielding a turbine engine from a hot gas flow path there through comprising the steps of:

• providing a hot ingestion gas zone cavity radially outward from said hot gas flow path;
• positioning at least one dilution jet opening in flow communication with a shroud cooling cavity of said turbine engine and said hot ingestion gas zone cavity, such that flow recirculation is induced within said hot ingestion gas zone cavity during operation of said turbine engine;
• and
• positioning an angled slot between and in flow communication with said hot ingestion gas zone cavity and said hot gas flow path.