Safran Aircraft Engines

Loïc Fabien François Villard

Baptiste Marie Aubin Pierre Jouy

Bertrand Guillaume Robin Pellaton

Laurent Cédric Zamai

Mathieu Charles Jean Verdiere

Laurent Claude Descamps

Josselin Luc Florent Sicard

Benoit Guilhem Bruno Jeannin

A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.

Device for sealing between a rotor and a stator of a turbine engine

A rotor disc for a turbomachine, the disc extending circumferentially around an axis and including a plurality of cells configured to receive blade roots and each cell including an upstream radial wall configured to axially block the blade root in the cell, each cell being connected to an upstream surface of the disc by a ventilation channel of the cell, the ventilation channel including an inlet orifice which opens onto the upstream surface of the disc and an outlet orifice which opens into the cell. An assembly of such a disc, of a plurality of blades and of a downstream retaining ring and a turbomachine including such an assembly.

Rotor disc with axial stop of the blades, assembly of a disc and a ring and  turbomachine

A device for controlling the clearance between a rotor and a stator surrounding same, which is carried out by modifying the delivery flow carried in a rotor recess in order to provide a bleed flow that prevents the gases from the flow section from penetrating into the recess. A valve can partially close the delivery circuit, thus reducing the cooling of the rotor structure and allowing the expansion thereof and the reduction of the clearance with the stator, for certain operating speeds including cruise operating speeds. In addition, the delivery air is heated more at a lower flow rate, especially if it is made to follow a bypass provided with meanders in the hottest portions of the circuit.

Method and device for adjusting the clearance between a rotor and a concentric stator of an aircraft turbine engine

Growing community of inventors

Moissy-Cramayel, France

Loïc Fabien François Villard