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...

Full description

Saved in:
Bibliographic Details
Main Authors LECUYER, Daniel, LEGHZAOUNI, Othmane
Format Patent
LanguageEnglish
French
German
Published 01.06.2022
Subjects
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 AccessGet full text

Cover

More Information
Summary: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.
Bibliography:Application Number: EP20210210883