TURBOMACHINE VANE AND METHOD OF COOLING THE SAME

PROBLEM TO BE SOLVED: To provide a turbomachine having a means for cooling a turbomachine vane.SOLUTION: The turbomachine includes at least one turbine vane arranged within a casing. The turbine vane includes a platform portion 42 operatively connected to the airfoil portion 40. A cooling cavity 60...

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Bibliographische Detailangaben
Hauptverfasser:	COIGN ROBERT W, BRITTINGHAM ROBERT ALAN
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:	PROBLEM TO BE SOLVED: To provide a turbomachine having a means for cooling a turbomachine vane.SOLUTION: The turbomachine includes at least one turbine vane arranged within a casing. The turbine vane includes a platform portion 42 operatively connected to the airfoil portion 40. A cooling cavity 60 is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged facing the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned facing the third wall. An impingement cooling plate 104 extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate includes at least one impingement cooling passage 120, 123 that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.