Safran Aircraft Engines

Charles-Henri Claude Jacky Sullet

Thomas Alain De Gaillard

Guillaume Pascal Jean-Charles Gondre

Alexandre Bernard Marie Boisson

Gilles Pierre-Marie Notarianni

Clément Pierre Postec

Olivier Bazot

Stéphane Roger Mahias

Guillaume Claude Robert Belmon

A blade () of a fan (), made of composite material, of a turbomachine. On a portion () of the blade () which extends from a lower limit () located at a predetermined distance (d) from the shank () of the blade equal to at least 80% of the predetermined height (h) to the top () of the blade (), a dihedral angle (D) measured at least one predefined point on the chord of the blade (), located on the chord of the blade () at the upstream end () of the nose () of the shield (), is greater than or equal to −3° and less than or equal to 0°.

Fan blade with zero tip dihedral at the head

A blade comprising a blade body made of fiber-reinforced organic-matrix composite material and a leading edge shield made of a material having a better resistance to point impacts than the composite material of the blade body, the leading edge shield being assembled on the blade body and including a pressure side fin and a suction side fin connected by a thicker central part, the blade including an aerodynamic airfoil height and a chord length, the suction side fin having a first length projected onto the chord between 10 and 18% of the chord length, the first length being disposed between 70 and 80% of the aerodynamic airfoil height, a second length projected onto the chord between 18 and 26% of the chord length, the second length being disposed between 85 and 95% of the aerodynamic airfoil height.

Blade made of composite material comprising a leading edge shield, turbine engine comprising the blade

A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.

Blade body and a blade made of composite material having fiber reinforcement made up both of three-dimensional weaving and also of short fibers, and method of fabrication

A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.

Growing community of inventors

Moissy-Cramayel, France

Charles-Henri Claude Jacky Sullet