Safran Aircraft Engines

Denis Gabriel Trahot

Arnaud Nicolas Negri

Elsa Maxime

Ba-Phuc Tang

Alexandre Gimel

Etienne Leon Francois

Josserand Jacques Andre Bassery

Maxime Paul Numa Givert

Josserand Jacques André Bassery

Slim Bensalah

Thomas Lardellier

Edouard Emmanuel Garreau

Thomas Tsassis

Lucas Geoffrey Desbois

Romain Bard

Christophe Damour

Arnaud Negri

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

Growing community of inventors

Moissy-Cramayel, France

Denis Gabriel Trahot