Safran Aircarft Engines

Snecma

Safran Aircraft Engines

Alicia Lise Julia Dufresne

Vincent Paul Gabriel Perrot

Damien Joseph Cellier

Laurent Christophe Francis Villaines

Philippe Pierre Marcel Marie Pelletrau

Jean-Francois Antoine Christian Rios

Jean-François Antoine Christian Rios

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 rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle &#x3bb; and its dihedral angle &#x3bd;, wherein the sweep angle &#x3bb; varies as a function of height H in such a manner that the sweep angle &#x3bb; reaches a maximum at a height H&#x3bb;M, the value H&#x3bb;M lying in the range 5% to 40%, and the sweep angle &#x3bb; increases from 0% to H&#x3bb;M, and wherein the dihedral angle &#x3bd; varies as a function of H, the dihedral angle &#x3bd; being a decreasing function of height H for heights H lying in the range 0% to H&#x3bd;, H&#x3bd;lying in the range 10% to 40%.

Turbine engine rotor blade

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

Paris, France

Alicia Lise Julia Dufresne