Film-cooled turbine blade for a turbomachine

A turbine blade for a turbomachine has an outer wall which delimits an inner cavity. Cooling fluid flows in the inner cavity. A through duct is arranged in the outer wall through which the cooling fluid flows from the inner cavity to an outside of the turbine blade. The through duct is inclined with...

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Bibliographische Detailangaben
1. Verfasser:	HESELHAUS ANDREAS
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL 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 WEAPONS
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Beschreibung
Zusammenfassung:	A turbine blade for a turbomachine has an outer wall which delimits an inner cavity. Cooling fluid flows in the inner cavity. A through duct is arranged in the outer wall through which the cooling fluid flows from the inner cavity to an outside of the turbine blade. The through duct is inclined with respect to a trailing edge of the turbine blade, wherein a marginal portion of an entrance of the through duct is designed on an upstream side to be sharp-edged in relation to other marginal portions of the entrance such that a separation zone of a cooling fluid flow is formed in the through duct. A pair of swirls builds up in the through duct, wherein velocity vectors of the cooling fluid flow between the swirl centers point toward a downstream side of the through duct.