GAS TURBINE COOLED SHROUD ASSEMBLY WITH HOT GAS INGESTION SUPPRESSION

A cooled shroud assembly (19) includes an angled slot (25) and a plurality o f dilution jet openings (26). The shroud forward cavity is modified such that at least one recirculation zone (21) is produced. The angled slot (25) forces; an axial change in momentum of the hot gas flow (37) and increases...

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Bibliographische Detailangaben
Hauptverfasser:	HOWE, WILLIAM J, SCIACCA, JOHN F, ZURMEHLY, GEORGE E, TILTMAN, ALAN G, MORRIS, MARK C
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A cooled shroud assembly (19) includes an angled slot (25) and a plurality o f dilution jet openings (26). The shroud forward cavity is modified such that at least one recirculation zone (21) is produced. The angled slot (25) forces; an axial change in momentum of the hot gas flow (37) and increases radial and axial pressure variation attenuation. The cooled shroud assembly (19) isolat es the shroud structure and seals from the hot flow path and a cooling flow (42 ) from the dilution jet openings (26) dilutes the hot gas flow. A series of recirculation zones shields the shroud carrier (33) and high pressure seals from the hot gas flow.