Safran Aircraft Engines

Safran

Clément Bourolleau

Serge Domingues

Vincent Pascal Fiore

Anwer Siraj

Alexandre Branco

Florent Louis André Rognin

Thomas Dupays

Clémentine Arnold

Jean-Hilaire Lexilus

Baptiste Leblon

Coline Poulenc

A fibrous texture having a three-dimensional weave between a plurality of layers of warp strands and a plurality of layers of weft strands. The fibrous texture includes first to fifth portions. The first and fifth portions extend in the lateral direction from the first and second lateral edges, respectively. The first and fifth portions each include warp strands composed of a first type of fiber corresponding to carbon fibers having a Young's modulus greater than 290 GPA and an elongation at break comprised between 1.2% and 2% and warp strands composed of a second type of fiber having a Young's modulus between 150 GPA and 250 GPA and an elongation at break between 4% and 6%.

Fibrous texture for a casing made of composite material with reinforced flanges

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

A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two tools between the flanges, each of the tools being located in a circumferential area outside the body so as to exert bearing forces in opposite axial directions on the flanges.

Method for manufacturing a housing for a turbine engine and tools for the implementation thereof

A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

Fibrous texture for a casing made of composite material with hybrid warp strands

The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing () comprising: —an annular shell () with axis A; —an annular element () attached to the inside of the shell (), the annular element comprising a body () made of NIDA-type cellular material and comprising a downstream portion () covered with an abradable material (), and an upstream portion () without abradable material, the body () extending in a continuous manner from the upstream portion () to the downstream portion (), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (), —attaching the segments to the shell, and —depositing the abradable material () onto the inside surface () of the downstream portion ().

Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine

A method for manufacturing a composite-material casing for a gas turbine, includes producing by three-dimensional weaving a fiber texture in the form of a strip, winding of the fiber texture around several superimposed turns on a mandrel with a profile corresponding to that of the casing to be manufactured in order to obtain a fiber preform of a shape corresponding to that of the casing to be manufactured, and densifying the fiber preform by a matrix. During the winding of the last turn of the fiber texture on the mandrel, at least one stiffening element is interposed between the before-last turn and the last turn of the fiber texture. The stiffening element projects over the outer surface of the before-last turn of the fiber texture. The stiffening element has an axial section of omega-type shape.

Composite-material casing having an integrated stiffener

A ring assembly has a housing made of woven composite material carrying on its radially inner face an acoustic panel with a cellular structure covered with a composite material. The housing includes at least one radial recess in which is engaged at least one radially outwardly projecting part of the radially outer face of the acoustic panel.

Turbomachine fan

A fan casing for an aircraft turbomachine, the casing including a one-piece annular body, the one piece annular body including a radially internal annular surface, a first annular portion of which is made of an abradable material, wherein a second annular portion of the internal surface comprises blind holes conferring acoustic properties to the second portion.

Fan casing for an aircraft turbomachine directly incorporating abradable portions and having acoustic properties

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.

Growing community of inventors

Moissy-Cramayel, France

Clément Bourolleau