TURBINE BLADE FOR A GAS TURBINE ENGINE AND GAS TURBINE ENGINE

A turbine blade (130) for a gas turbine engine (10), has: an airfoil (33) extending along a span (S) from a base (33a) to a tip (33b) and along a chord (C) from a leading edge (33c) to a trailing edge (33d), the airfoil (33) having a pressure side (33e) and a suction side (33f), a tip pocket (134) a...

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Bibliographische Detailangaben
Hauptverfasser:	LECUYER, Daniel, LEGHZAOUNI, Othmane
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 turbine blade (130) for a gas turbine engine (10), has: an airfoil (33) extending along a span (S) from a base (33a) to a tip (33b) and along a chord (C) from a leading edge (33c) to a trailing edge (33d), the airfoil (33) having a pressure side (33e) and a suction side (33f), a tip pocket (134) at the tip (33b) of the airfoil (33), the tip pocket (134) at least partially surrounded by a peripheral tip wall (135) defining a portion of the pressure and suction sides (33e, 33f); at least one internal cooling passage (37) in the airfoil (33), the at least one internal cooling passage (37) having at least one outlet (137a) communicating with the tip pocket (134); and a reinforcing bump (140) located on the pressure side (33e) of the airfoil (33) and protruding from a baseline surface (B) of the peripheral tip wall (135) to a bump end (140b) located into the tip pocket (134), the reinforcing bump (140) overlapping a location (L1) where a curvature of a concave portion of the pressure side (33e) of the airfoil (33) is maximal.