Cooling system for a gas turbine airfoil

The cooling system for the airfoil (12) includes forward and aft cooling circuits (22, 24) supplied with a cooling medium. Both circuits include serpentine passages (36, 38, 46, 48, 50). A central rib (34) divides the forward and aft cooling circuits and includes an opening (70) adjacent the airfoil...

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Bibliographische Detailangaben
Hauptverfasser:	HIRT, PHILIP RICHARD, HONKOMP, MARK STEVEN, BUTKIEWICZ, JEFFREY JOHN
Format:	Patent
Sprache:	eng ; fre ; ger
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 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:	The cooling system for the airfoil (12) includes forward and aft cooling circuits (22, 24) supplied with a cooling medium. Both circuits include serpentine passages (36, 38, 46, 48, 50). A central rib (34) divides the forward and aft cooling circuits and includes an opening (70) adjacent the airfoil tip providing a jet of the cooling medium from the forward cooling circuit for impingement against the aft portion of the tip cap (60). The tip cap also includes a thermal barrier coating (62_ along an outside surface thereof as well as on the seat (58) for the tip cap, thereby lowering the tip cap metal temperature and thermally induced stress.