AIRFOIL WITH DIRT SEPARATOR FOR A FILM COOLING HOLE

A gas turbine engine internally cooled component airfoil (400) having a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, including a cooling system having at least one or more passages including a first passage...

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Bibliographische Detailangaben
Hauptverfasser:	WAGNER, Joel H, PROPHETER-HINCKLEY, Tracy A
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:	A gas turbine engine internally cooled component airfoil (400) having a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, including a cooling system having at least one or more passages including a first passage pressure side surface that includes an interior protrusion (412), the geometry of which providing a dirt filtering system. The interior protrusion includes a first sloped surface (414) extending to a peak of the interior protrusion and a second sloped surface (418) extending from the peak substantially in the direction of the pressure side surface with a slope that is greater than the slope of the first sloped surface. A first cooling hole (404) extends from the second sloped surface through the interior protrusion to vent the first of the one or more passages to the pressure side surface.