Safran Aircraft Engines

Safran

Jérémy Jacques Attilio Fanelli

Ba-Phuc Tang

Romain Pierre Cariou

Vianney Simon

A turbine engine blade includes an airfoil with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge and downstream by a trailing edge. A cooling circuit has an internal cavity extending inside the airfoil and a plurality of outlet openings, each oriented substantially along a longitudinal axis X. Each outlet opening communicates with the cavity and is arranged in the vicinity of the trailing edge. A calibration device is arranged in the cavity and provided with calibration conduits arranged substantially opposite the outlet openings. The calibration conduits each include an oblong transverse section which is substantially perpendicular to the longitudinal axis.

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Moissy-Cramayel, France

Jérémy Jacques Attilio Fanelli