COOLING ARRANGEMENT FOR GAS TURBINE ENGINE COMPONENT

An airfoil (162) for a gas turbine engine (20) includes an airfoil section (162A) extending in a radial direction (R) from a root section (162B) to a tip portion (162T). The airfoil section (162A) has an external wall (166) and an internal wall (168). The airfoil section (162A) establishes an intern...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	SURACE, Raymond, DeGRAY, Jeffrey J, JENNINGS, Timothy J, PETERS, Christopher J, MONGILLO, Dominic J, PLACE, Emma J, FREDETTE, Jeremy B
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	An airfoil (162) for a gas turbine engine (20) includes an airfoil section (162A) extending in a radial direction (R) from a root section (162B) to a tip portion (162T). The airfoil section (162A) has an external wall (166) and an internal wall (168). The airfoil section (162A) establishes an internal cooling arrangement (164) including a first cooling passage (170) having a first section (170A) and a tip flag section (170B). The tip flag section (170B) extends in the chordwise direction (X) along the tip portion (162T) from the first section (170A). The first section (170A) includes a plurality of branched paths (171) established by at least one turning vane (174).