AIRFOIL PLATFORM COOLING CHANNELS

The present invention is related to an airfoil (100) for a gas turbine engine (20) including a body (120), a root (124) and a platform (122) disposed between the airfoil body (120) and the root (124). The platform (122) may have a first and a second mating surface (144, 146) and include a pocket (16...

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Bibliographische Detailangaben
Hauptverfasser:	LANA, Kyle C, LEWIS, Scott D
Format:	Patent
Sprache:	eng ; fre ; ger
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 present invention is related to an airfoil (100) for a gas turbine engine (20) including a body (120), a root (124) and a platform (122) disposed between the airfoil body (120) and the root (124). The platform (122) may have a first and a second mating surface (144, 146) and include a pocket (164) defined by an inner diameter surface (130) proximate the first mating surface (144). A channel (160) may be defined in the platform (122) with an outlet (162) defined in the second mating surface (146). The pocket (164) may capture a secondary cooling airflow (F) which flows around the root (124) and expel it via channel (160) and cooling holes (162) to impinge on a corresponding mating surface (144) of an adjacent airfoil (100). Thus, platform cooling properties are improved while discouraging ingestion of hot gas flow (C) into the gap (156) between adjacent blades (104).