Safran Aircraft Engines

Safran

Alexandre Branco

Clément Bourolleau

Vincent Pascal Fiore

Serge Domingues

Anwer Siraj

Thierry Georges Paul Papin

Thomas Dupays

Azath Mohamed

Clémentine Arnold

Baptiste Leblon

Virginie Martine Collin

Michael Isemene

A fan casing for an aircraft turbomachine includes an annular body extending around an axis and equipped with an annular attachment flange at each of its axial ends. The casing further includes an annular coating made from abradable material, wherein the body is made from a composite material, and further includes an annular stiffener that is arranged inside the body and that carries the coating. The stiffener includes an annular ring, a radially outer face of which is separated radially from the body and a radially inner face of which receives the coating. The stiffener further includes annular attachment tabs configured to the wall to the body.

Fan casing for an aircraft turbomachine

Discharge valve of an aircraft turbomachine, including a discharge gate intended to be mounted pivotably about an axis between a position for closing an air passage orifice and an open position of said orifice, the orifice being formed in an intermediate casing of the turbomachine, the discharge valve including a sealing device having a seal configured to be movably mounted on the intermediate casing and a movement system configured to move the seal between a first position in which the seal is intended to bear against the discharge gate when the gate is in a closure position, and a second position in which the seal is retracted with respect to the air passage orifice when the discharge gate is in an open position.

Sealing device for a discharge valve of a turbomachine

A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N, N) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.

Method for detecting a roughness in an abradable layer in a fan casing

A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

Casing made of composite material with local variation of thickness

The invention relates to a blade (), in particular a fan blade, for resurfacing an abradable coating () on an internal surface of a turbine engine case () intended to surround the blade. The comprises a root () and an airfoil () having a tip opposite the root, said root comprising a housing () for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.

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Moissy-Cramayel, France

Alexandre Branco