Safran Aircraft Engines

Safran

Snecma Propulsion Solide

Safran Ceramics

Herakles

Albany International Corporation

Snecma

François Charleux

Dominique Coupe

Eric Bouillon

Eric Philippe

Dominique Marie Christian Coupe

Mattéo Minervino

Marie Lefebvre

Hervé Grelin

Caroline Louchet-Pouillerie

Matthieu Arnaud Gimat

Jérémy Guivarc'h

Clément Pierre Postec

Brock Gilbertson

Pierre Jean Faivre D'arcier

Rémi Bouvier

Bernard Delperier

Bruno Dambrine

Didier Fromonteil

Steven Gérard Joseph Bienvenu

Arnaud Fillion

Marc-Antoine Colot

Julie-Anne Bouchet

Jean Noel Mahieu

Jean-Philippe Richard

Sébastien Marin

Sébastien Jimenez

Jean-Marie Parenteau

Pierre-Antoine Bossan

Stéphanie Fouquet

Gwenael Marion

Vincent Lionel René Maison

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

Propeller blade or vane having a hollow composite root

A strip-shaped fibrous texture has a three-dimensional or multi-layered weaving between a plurality of layers of warp yarns or strands and a plurality of layers of weft yarns or strands extending in the lateral direction. The fibrous texture includes a first section extending along the longitudinal direction from a proximal portion of the texture and in which one or more layers of the plurality of layers of weft yarns or strands consist of a plurality of groups of yarns or strands each including at least one carbon fiber yarn or strand and one glass fiber yarn or strand. The carbon fiber yarn or strand and the glass fiber yarn or strand of each group of yarns being woven together according to the same weaving pattern or weave. The fibrous texture further includes a second section present between the first section and a distal portion of the fibrous texture.

Fiber texture for a casing made of composite material with improved impact resistance

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including along a longitudinal direction a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile parts being connected to one another by three-dimensional weaving. The root preform part includes two woven skins wound around an insertion element.

Propeller blade or airfoil with wound composite root

A blade made of a composite material, the blade including a fibrous reinforcement densified by an organic matrix and being provided, in an attachment zone, with a metal element, wherein the reinforcement includes, in at least one region of the attachment zone, a surface textile orientation adapted to the direction of mechanical stresses by having first skin threads that extend in a main mechanical stress direction and that are bonded to second skin threads transverse to the first threads, the first skin threads making up most of the surface area of the region of the attachment zone.

Hybrid metal/composite blade with textile orientation adapted to mechanical stresses

A method for manufacturing a fibrous preform for a blade or propeller part of a turbomachine, includes at least one fixing base extended by a mounting portion of an aerodynamic profile, the method including the winding of a fibrous texture, obtained by contour weaving, on a substrate of changing section having at least a first region of extra thickness in the shape of the fixing base and a second region in the shape of the mounting portion of the aerodynamic profile.

Method for producing a preform for part of a blade or propeller by winding a weave obtained by weaving to shape

A weaving installation includes a loom that receives a series of strands, and at least one device for measuring the diameter of a strand having a defined number of filaments. The device includes a diaphragm having an external ring forming a support on which a series of strips forming an iris are fixed. The strips are movable and allow a substantially circular space with variable dimensions to be defined at the center of the iris. The diaphragm is configured to adjust the dimensions of the space so as to allow a strand of the loom to pass through it, and to encircle the profile of the strand so as to allow the number of filaments in the strand to be determined.

Weaving installation allowing the number of filaments in a strand to be determined

A composite platform for an aircraft turbine engine fan includes a wall of elongate shape that is configured to extend between two fan blades. The wall has an aerodynamic external face and an internal face on which is disposed a fixing tab configured to be fixed to a fan disc. A method for manufacturing the composite platform includes the steps of: a) producing a preform by three-dimensionally weaving of fibers, b) unbinding some of the fibers of the preform to detach at least one longitudinal layer of fibers from the rest of the preform, c) inserting a metal reinforcement between this layer and the rest of the preform, and d) injecting a resin into the preform so as to form said wall and secure the reinforcement to this wall.

Method for manufacturing a composite platform for an aircraft turbine engine fan

A method of fabricating a fiber structure by multilayer three-dimensional weaving between a plurality of weft yarns and of warp yarns, the fiber structure having at least first and second portions that are adjacent in the warp direction, the first portion presenting, in a direction perpendicular to the warp and weft directions, a thickness greater than the thickness of the second portion, includes making the first portion using a step of three-dimensionally weaving warp and weft layers in which a fiber fabric is formed in the form of a Mock-Leno weave grid in a core of the first portion together with skins at a surface of the first portion, a weave of the skins being modified locally so as to deflect certain warp yarns from said skins and weave them with the fiber fabric in the form of the Mock-Leno weave grid.

Fiber structure and a composite material part incorporating such a structure

A fibrous texture in the form of a web includes a first portion extending in a longitudinal direction between a proximal part and an intermediate part. One or more layers of warp threads or strands present on the side of an inner face of the fibrous texture include threads or strands of glass fibers, the threads or strands of the other layers of warp threads or strands including threads or strands of carbon fibers. The fibrous texture further includes a second portion extending in the longitudinal direction between the intermediate part and a distal part of the fibrous texture. One or more of the plurality of layers of warp threads or strands present on the side of an outer face of the fibrous texture include threads or strands of glass fibers. The warp threads or strands are continuous over the entire length of the fibrous texture.

Fiber texture for a casing made of composite material with improved shear resistance

A fiber structure includes a plurality of weft layers and a plurality of warp layers interlinked with three-dimensional or multilayer weaving, the fiber structure including at least first and second portions that are adjacent in the warp direction, the first portion presenting thickness in a direction perpendicular to the warp and weft directions that is greater than the thickness of the second portion. The weft layers situated in the core of the first portion of the fiber structure include braids. The weft layers extending on either side of the weft layers including the braids and going as far as the skin of the first portion include yarns or strands, the braids presenting a section greater than the section of the yarns or strands.

Reinforcing fiber structure for composite material parts with great variation of thickness

A fiber structure includes a plurality of weft layers and of warp layers interlinked by multilayer three-dimensional weaving, the fiber structure having at least first and second portions that are adjacent in the warp direction, the first portion presenting, in a direction perpendicular to the warp and weft directions, a thickness that is greater than the thickness of the second portion, wherein the first portion has at its core at least one fiber fabric obtained by three-dimensional weaving of warp yarns and weft yarns in the form of a Mock Leno weave grid, the at least one fabric being present between two skins present at the surface of the first portion and being linked to the skins by warp yarns belonging to the skins that are locally deflected into the fabric.

A composite material guide vane for a gas turbine engine, the composite material including fiber reinforcement densified by a matrix, the fiber reinforcement being formed as a single piece by three-dimensional weaving and including an airfoil and at least two fastener flanges extending from a radial end of the vane towards opposite side faces of the airfoil, the fastener flanges being axially offset from each other.

Guide vane made from composite material, comprising staggered attachment flanges for a gas turbine engine

A method of fabricating a curved cellular structure includes making an expandable fiber structure by multilayer weaving between layers of warp yarns and layers of weft yarns, the structure having zones of non-interlinking extending in the thickness of the structure, the non-interlinking zones spaced apart from one another by portions of interlinking between layers of weft yarns, the portions of interlinking offset by one or more weft yarns in a direction parallel to the direction of the layers of weft yarns between each series of these planes; impregnating the fiber structure with a resin; expanding the fiber structure on support tooling to form a cell in the fiber structure at each zone of non-interlinking, the tooling also presenting a curved shape corresponding to the shape of the cellular structure that is to be fabricated; and polymerizing the resin of the fiber structure to form a curved cellular structure.

Method for producing a curved honeycomb structure made from composite material

A method of fabricating a composite material part comprises fiber reinforcement densified by a matrix. The method comprises the following steps: making a fiber fabric by weaving yarns having an initial mean fiber percentage; and densifying the fiber fabric with a matrix. The fiber fabric is subjected, prior to densification, to one or more jets of water under pressure so as to reduce the mean fiber percentage in the fabric to a value lying in the range 20% to 45%.

Method of fabricating a composite material part with improved intra-yarn densification

A thermostructural composite material part including carbon or ceramic fiber reinforcement densified by a matrix having at least one thin portion in which: the thickness of the part is less than 2 mm, or indeed less than 1 mm; the fiber reinforcement is made as a single thickness of multilayer fabric made of spread yarns having a weight of not less than 200 tex; the fiber volume ratio lies in the range 25% to 45%; and the ratio between the number of layers of the multilayer fabric and the thickness in millimeters of the part is not less than four.

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Bordeaux, France

François Charleux