Safran Aircraft Engines

Elsa Maxime

Denis Gabriel Trahot

Ba-Phuc Tang

Alexandre Gimel

Etienne Leon Francois

Josserand Jacques Andre Bassery

Maxime Paul Numa Givert

Josserand Jacques André Bassery

Edouard Emmanuel Garreau

Thomas Tsassis

Lucas Geoffrey Desbois

Christophe Damour

A turbine engine has a blade with lower and upper surfaces. The blade has a root at a radially external end and includes a transverse head section in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first center of gravity. The root has a second center of gravity defined in a plane parallel to the transverse head section and transversely offset from the first center of gravity. The second center of gravity is defined in a predetermined zone at least partly demarcated by a V that is open towards the lower surface and includes a peak, the orthogonal projection of which on the transverse head section is located on the first center of gravity.

Vane for a turbine engine with optimized heel and method for optimizing a vane profile

To increase the inertia of a sealing lip of a blade for an aircraft turbine engine, and thus improve the service life of such a sealing lip, the sealing lip is conformed so as to have a trough in the outer surface thereof and a corresponding boss in the inner surface thereof, the trough and the boss being defined based on a connection cross section of the sealing lip to a blade body, and being formed at a distance from a free axial end of the sealing lip.

Blade for a rotating bladed disk for an aircraft turbine engine comprising a sealing lip having an optimized non-constant cross section

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Moissy-Cramayel, France

Elsa Maxime