Cooling passage with structural rib and film cooling slot

A component for a gas turbine engine, includes a component outer surface exposed to flowpath gases of the gas turbine engine, a cooling channel located in the component, and at least one channel rib located in the cooling channel extending across the cooling channel from a channel inner surface to a...

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Bibliographische Detailangaben
1. Verfasser:	LoRicco, Nicholas M
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:	A component for a gas turbine engine, includes a component outer surface exposed to flowpath gases of the gas turbine engine, a cooling channel located in the component, and at least one channel rib located in the cooling channel extending across the cooling channel from a channel inner surface to a channel outer surface. A cooling slot extends from the cooling channel to a slot outlet at the component outer surface. The slot outlet has a radial width greater than an axial length.