Safran Aircarft Engines

Safran Aircraft Engines

Snecma

Laurent Christophe Francis Villaines

Vincent Paul Gabriel Perrot

Damien Joseph Cellier

Alicia Lise Julia Dufresne

Philippe Pierre Marcel Marie Pelletrau

Jean-Francois Antoine Christian Rios

Michel Dumas

Damien Cellier

Jean-François Antoine Christian Rios

A bladed disc for masking a moving disc of a jet engine, including blades, each blade including a pressure-side wall and a suction-side wall that meet at a leading-edge and at a trailing edge, and wherein each blade has a pressure-side wall and a suction-side wall each including a concave zone and a convex zone that are at a distance from the leading-edge and from the trailing edge and are spaced apart from one another, these concave zones and these convex zones each extending over the majority of the height of the blade, the concave zone of the pressure-side wall is opposite the convex zone of the suction-side wall, the concave zone of the suction-side wall is opposite the convex zone of the pressure-side wall.

Masking bladed disc for reducing the radar signature of a moving compressor moving disc of a jet engine

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

Vaux Le Penil, France

Laurent Christophe Francis Villaines