AIRFOIL TIP ARRANGEMENT FOR GAS TURBINE ENGINE

An airfoil (162) for a gas turbine engine includes a platform section (162B) and an airfoil section (162A) extending in a spanwise direction from the platform section (162B) to a tip portion (162TP) establishing a tip (162T). The airfoil section (162A) has an external wall (166) defining pressure an...

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Bibliographische Detailangaben
Hauptverfasser:	MONGILLO Jr., 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
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Beschreibung
Zusammenfassung:	An airfoil (162) for a gas turbine engine includes a platform section (162B) and an airfoil section (162A) extending in a spanwise direction from the platform section (162B) to a tip portion (162TP) establishing a tip (162T). The airfoil section (162A) has an external wall (166) defining pressure and suction sides (162P, 162S) extending in a chordwise direction (X) between a leading edge (162LE) and a trailing edge (162TE), and the pressure and suction sides (162P, 162S) are spaced apart in a thickness direction (T) between the leading edge (162LE) and the trailing edge (162TE). The tip portion (162TP) includes a tip pocket (174) and a tip shelf (176) extending inwardly from the tip (162T). The tip pocket (174) and tip shelf (176) are on opposite sides of a shelf wall (178), and the shelf wall (178) has a serpentine profile.