Refrigerated gas turbine cover assembly with suppression of hot gas ingestion

摘要

A refrigerated cover assembly (19) for a turbine engine comprising: an outer wall of turbine stator; a stator retainer (30) radially disposed outwardly from the outer wall of the turbine stator; a cover segment (28) axially separated from the outer wall of the turbine stator and the stator retainer (30); a cover carrier (33) radially disposed outwardly from the cover segment (28); a recirculation cavity (21) formed between the outer wall of the turbine stator and the cover segment (28), the recirculation cavity (21) being configured to recirculate a flow therein, said recirculation cavity (21) being positioned radially outward from a hot gas flow path (38) through said turbine engine; at least one dilution jet opening (26) formed in the cover segment (28) and in flow communication with said recirculation cavity (21); and an inclined groove (25) positioned radially inwardly from said recirculation cavity (21) and formed between said outer turbine stator wall and an anterior edge (39) of the cover segment (28), said groove (25) being inclined in flow communication with said recirculation cavity (21) and said hot gas flow path (38), characterized in that said recirculation cavity (21) formed between said outer turbine stator wall and said carrier ( 33) of cover, said recirculating cavity (21) including a cavity (22) of hot gas ingestion zone positioned radially outward from said hot gas flow path (38) and directing at least a part of the gas from the hot gas flow path (38) therein, a cold upper zone cavity (24) in flow communication with said hot gas ingestion zone (22), and at least one intermediate zone cavity (23) AC It is positioned between and in flow communication with said cavity (22) of hot gas ingestion zone and said cavity (24) of upper cold zone.