GAS TURBINE NOZZLES WITH COOLING HOLES AND TURBINE

The nozzle segment for a gas turbine comprises an inner platform (23) and an outer platform (25) as well as a plurality of airfoils (27, 29) arranged between the inner platform (23) and the outer platform (25). A set of platform film cooling holes (37) are provided, including at least one inner plat...

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Bibliographische Detailangaben
Hauptverfasser:	CUBEDA, Simone, CRESCI, Irene, TRIPOLI, Girolamo, PAONE, Fabrizio, ANDREI, Luca
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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:	The nozzle segment for a gas turbine comprises an inner platform (23) and an outer platform (25) as well as a plurality of airfoils (27, 29) arranged between the inner platform (23) and the outer platform (25). A set of platform film cooling holes (37) are provided, including at least one inner platform film cooling hole on a surface of the inner platform or on a surface of the outer platform facing said hot gas flow passage (31). A ratio between a distance (Δγhole) in tangential direction of the platform film cooling hole (37) from the pressure side of the respective airfoil (29) and a width (Δγ) of the hot gas flow passage (31) in tangential direction at the platform film cooling hole (37) is comprised between 0 and 0.5.