Snecma

Safran Aircarft Engines

Jean-Francois Antoine Christian Rios

Vincent Paul Gabriel Perrot

Damien Joseph Cellier

Laurent Christophe Francis Villaines

Alicia Lise Julia Dufresne

Philippe Pierre Marcel Marie Pelletrau

Damien Cellier

A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.

Turbomachine centre blade comprising a curved portion

A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

Turbine engine blade, in particular for a one-piece bladed disk

Growing community of inventors

Nandy, France

Jean-Francois Antoine Christian Rios