• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A fibrous preform (400) of turbomachine blade reinforcement made of composite material comprises a fibrous structure (200) woven in one piece by three-dimensional weaving or multilayer. The fibrous structure (200) includes a blade root portion (210) and a blade blade portion (220) extending in a longitudinal direction (D1) between the blade root portion (210) and a blade crown portion (221) and in a transverse direction (Dt) between a leading edge portion (222) and a trailing edge portion (223). The preform (400) further comprises at least one unidirectional fold (310) present on the blade blade portion (220) of the fibrous texture, the fibers (311) of each unidirectional fold extending in a direction determined by relative to the longitudinal (DI) and transverse (Dt) directions of the blade blade portion (220) of the fibrous structure (200).
    公开号:FR3040909A1
    申请号:FR1558680
    申请日:2015-09-16
    公开日:2017-03-17
    发明作者:Matthieu Arnaud Gimat；Jean-Noel Mahieu；Gilles Pierre-Marie Notarianni；Frederic Jean-Bernard Pouzadoux
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to the general field of turbomachine blades of composite material comprising a fiber reinforcement densified by a matrix.
    The targeted field is that of the blades to be mounted on gas turbine rotor discs for aircraft engines or industrial turbines.
    The composite materials make it possible to produce blades having a lower overall mass than these same parts when they are made of metallic material.
    The embodiment of blades of composite material for turbomachines has already been proposed. Reference is made in particular to US patent application 2011/0311368. This application describes the manufacture of a turbomachine blade of composite material comprising a fiber reinforcement densified by a matrix, the fiber blank intended to constitute the reinforcement is produced by three-dimensional weaving (3D) or multilayer between a plurality of warp yarns and a plurality of weft threads. The use of a fiber reinforcement obtained by 3D or multilayer weaving makes it possible to obtain a blade made of composite material having very good mechanical properties, especially in terms of fatigue strength and toughness. It is generally possible with this material to act on the weaving parameters and the definition of the preform to give the piece the desired mechanical properties in the relevant areas. However, in some very particular cases, it may be difficult to act completely freely on the mechanical properties of a given area without negatively impacting a wider area, bound by weaving (same warp or weft columns).
    In the case of certain stresses causing significant local deformations, as may occur for example during a bird ingestion or hail, or a loss of dawn (FBO for "Fan Blade Out"), a control in particular the level and the orientation of the stiffness in the area or areas of the blade concerned would improve the mechanical strength of the blade vis-à-vis this type of solicitations. The definition of a stiffness ratio between the radial direction corresponding to the warp direction and the rope direction corresponding to the weft direction in the blade reinforcement is possible. However, this definition remains limited in its possibilities because of the 3D or multilayer weave which does not completely freely change the orientation and the local fiber content in the fibrous reinforcement without negatively impacting a wider area, bound by weaving. (same string or field columns).
    In addition to a need for specific stiffness in certain areas of the dawn, there are other parts of the dawn in which, on the contrary, it is interesting to be able to locally increase the elongation capacity of the material to support local deformations that may impose the material of the blade forces greater than the limit of elongation of this material.
    Object and summary of the invention
    It is therefore desirable to have fiber reinforcements for blades of composite material whose mechanical characteristics can be adapted more freely locally relative to the rest of the fibrous reinforcement. For this purpose, according to the present invention, it is proposed a fibrous preform of turbomachine blade reinforcement composite material, said preform comprising a fibrous structure woven in one piece by three-dimensional weaving or multilayer between a first plurality of layers of son and a second plurality of wire layers, the fiber structure comprising a blade root portion and a blade blade portion extending in a longitudinal direction between the blade root portion and a peak portion of blade and in a transverse direction between a leading edge portion and a trailing edge portion, characterized in that said preform further comprises at least one unidirectional fold or a two-dimensional fabric layer present on the blade portion of dawn of the fibrous texture, the fibers of each unidirectional fold extending in a determined direction with respect to the longitudinal and transverse directions e of the blade blade portion of the fibrous structure or the yarns of each two-dimensional fabric layer extending in two determined directions with respect to the longitudinal and transverse directions of the blade blade portion of the fibrous structure.
    Thus, by adding one or more unidirectional folds and / or two-dimensional fabric layers on a fibrous structure obtained by three-dimensional or multi-layer weaving, it is possible to locally increase the level of fibers in one or more determined directions, which makes it possible to define a specific mechanical behavior of the reinforcement and, consequently, of the resulting composite material blade, in the zone or regions of the blade covered by the added unidirectional ply (s) and / or by the layer (s) of two-dimensional fabric added.
    According to one embodiment of the fiber preform of the invention, the fibers of each unidirectional fold and the threads of each two-dimensional fabric layer are of the same nature as the fibers of the fibrous structure. In this case, the stiffness of the preform and, consequently, the stiffness of the resulting composite material blade reinforcement is increased in the area of the fibrous texture covered by the unidirectional ply (s) and / or the ply layer (s). two-dimensional fabric and in the direction of the fibers of this or these folds and / or the directions of the son of this or these two-dimensional fabric layers. The tenacity of the 3D or multilayer woven fibrous structure is thus combined with an increase in localized stiffness and oriented in one or more determined directions. The resulting blade has, therefore, improved mechanical strength.
    According to a particular characteristic of the preform of the invention, one or more unidirectional folds and / or one or more layers of two-dimensional fabric are present on the crown portion of the blade portion of the fibrous structure, the fibers of the ply or folds. unidirectional directions extending in a direction parallel to the transverse direction of the blade blade part of the fibrous structure while the wires of the bidirectional tissue layer (s) extend in two directions respectively parallel to the longitudinal direction and the transverse direction of the blade blade portion of the fibrous structure. Thus, by adding at the blade crown portion of the blade portion of the fibrous structure one or more unidirectional folds and / or one or more layers of two-dimensional fabric including fibers or yarns. are oriented in the transverse direction and / or the longitudinal direction of the blade portion, the rate of fibers in these directions is locally increased, which makes it possible to have at the blade tip a specific mechanical behavior in terms of stiffness with respect to the rest of the dawn.
    According to another embodiment of the preform of the invention, the fibers of each unidirectional fold and the threads of each two-dimensional fabric layer have a higher elongation rate than the fibers of the fibrous structure. Thus, the rate of elongation and, consequently, the ability of the resulting blade to deform without cracking in the area covered by the unidirectional fold (s) and / or the two-dimensional fabric layer (s) is increased locally. The resulting blade has, therefore, improved mechanical strength.
    According to a particular characteristic of the preform of the invention, one or more unidirectional folds and / or one or more layers of two-dimensional fabric are present on the trailing edge portion of the blade portion of the fibrous structure, the fibers of the unidirectional folds extending in a direction parallel to the longitudinal direction of the blade blade portion of the fibrous structure while the wires of the bi-directional tissue layer (s) extend in two directions respectively parallel to the longitudinal direction and in the transverse direction of the blade blade portion of the fibrous structure. Thus, by adding at the trailing edge portion of the blade portion of the fibrous structure one or more unidirectional pleats and / or one or more two-dimensional fabric layers whose fibers or yarns exhibit a higher elongation rate at break than that of the fibers of the fibrous structure, the rate of elongation is increased locally and, consequently, the capacity of the resulting blade to deform without cracking in the zone covered by the the unidirectional folds and / or the two-dimensional fabric layer (s). The fibers of the unidirectional ply or plies are oriented in the longitudinal direction of the blade portion, in which direction the resulting blade will present on the area covered by the ply or creases a deformation capacity without increased cracking. With the two-dimensional fabric layer (s), the resulting blade will exhibit deformation capacity without increased cracking in both the longitudinal direction and the blade section cross direction.
    According to yet another embodiment of the preform of the invention, the same preform comprises, on the one hand, one or more unidirectional folds or one or more layers of two-dimensional fabric having fibers or threads of the same nature as the fibers. of the fibrous structure present in one or more areas of the blade blade part of the fibrous texture and, on the other hand, one or more unidirectional folds or one or more two-dimensional fabric layers whose fibers or yarns have a greater elongation at break than that of the fibers of the fibrous structure in one or more other areas of the blade portion of the fibrous texture. The invention also relates to a turbomachine blade comprising a fiber reinforcement densified by a matrix characterized in that the fiber reinforcement consists of a fiber preform according to the invention. The invention also relates to a process for manufacturing a fiber reinforcement of turbomachine blade of composite material, said method comprising the production of a fibrous structure woven in one piece by three-dimensional weaving or multilayer between a first plurality of layers of yarns and a second plurality of yarn layers, the fibrous structure comprising a blade root portion and a blade blade portion extending in a longitudinal direction between the blade root portion and an apex portion blade and in a transverse direction between a leading edge portion and a trailing edge portion, characterized in that said method further comprises placing at least one unidirectional fold or a two-dimensional fabric layer over the portion blade blade of the fibrous texture, the fibers of each unidirectional fold extending in a direction determined with respect to the longitudinal and transv directions ersal of the blade blade portion of the fibrous structure and the yarns of each two-dimensional fabric layer extending in two directions determined with respect to the longitudinal and transverse directions of the blade blade portion of the fibrous structure.
    According to one embodiment of the method of the invention, the fibers of each unidirectional fold and the threads of each layer of two-dimensional fabric are of the same nature as the fibers of the fibrous structure.
    According to a particular characteristic of the method of the invention, one or more unidirectional folds and / or one or more layers of two-dimensional fabric are placed on the crown portion of the blade portion of the fibrous structure, the fibers of the unidirectional fold or folds. extending in a direction parallel to the transverse direction of the vane blade portion of the fibrous structure while the yarns of the bi-directional tissue layer (s) extend in two directions respectively parallel to the longitudinal direction and the transverse direction of the blade blade part of the fibrous structure.
    According to another embodiment of the method of the invention, the fibers of each unidirectional fold and the threads of each two-dimensional fabric layer have a tensile elongation rate greater than that of the fibers of the fibrous structure.
    According to a particular characteristic of the method of the invention, one or more unidirectional folds and / or one or more layers of two-dimensional fabric are placed on the trailing edge portion of the blade portion of the fibrous structure, the fibers of the unidirectional folds extending in a direction parallel to the longitudinal direction of the blade blade part of the fibrous structure while the wires of the two-dimensional fabric layer (s) extend in two directions respectively parallel to the longitudinal direction and in the transverse direction of the blade blade part of the fibrous structure.
    According to yet another embodiment of the preform of the invention, one or more unidirectional folds or one or more two-dimensional fabric layers having fibers or yarns of the same nature as the fibers of the fibrous structure are placed on one or more zones. of the blade blade part of the fibrous texture while one or more unidirectional folds or one or more layers of two-dimensional fabric whose fibers or yarns have a higher elongation-to-break ratio than the fibers of the fibrous structure are placed on one or more other areas of the blade portion of the fibrous texture. The invention finally relates to a method of manufacturing a turbomachine blade comprising the manufacture of a fibrous reinforcement according to the invention and the densification of said fibrous reinforcement by a matrix. The invention further relates to a turbomachine equipped with a plurality of blades according to the invention or manufactured according to the method as defined above.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood from the description given below, by way of indication but without limitation, with reference to the accompanying drawings in which: FIG. 1 very schematically illustrates a three-dimensional woven fiber blank intended for the producing a fiber preform according to an embodiment of the invention; - Figures 2 and 4 show the realization of a fiber preform according to one embodiment of the invention; FIG. 3 very schematically illustrates a unidirectional fold used for producing a fiber preform according to the invention; FIG. 5 illustrates a turbomachine blade of composite material obtained from the preform of FIG. 4; - Figures 6 and 7 show the embodiment of a fiber preform according to another embodiment of the invention.
    DETAILED DESCRIPTION OF EMBODIMENTS The invention generally applies to the production of fiber preforms capable of constituting fibrous reinforcements for turbomachine blades of composite material, in particular fan blades or gas turbine compressor blades. aeronautical engines. The blades are obtained by densification of the fibrous preforms by a matrix. The matrix is typically a resin, in the case of composite materials used at relatively low temperature, typically up to 300 ° C, or a refractory material such as carbon or ceramic in the case of thermostructural composites.
    FIG. 1 shows very schematically a fibrous blank 100 intended to form a fibrous texture from which a fibrous preform according to the invention is constituted by adding one or more unidirectional folds or one or more two-dimensional fabric layers as explained below. The preform thus obtained is intended to form the fibrous reinforcement of an aeronautical engine blade. The fibrous blank 100 is obtained by three-dimensional weaving or multilayer weaving made in known manner by means of a jacquard loom on which a bundle of warp threads or strands 101 has been arranged in a plurality of layers, the threads of chain being linked by weft threads 102 also arranged in a plurality of layers. A detailed example of embodiment of a fiber preform intended to form the fibrous reinforcement of a blade for an aeronautical engine is described in detail in documents US 7 101 154, US 7 241 112 and WO 2010/061140.
    By "three-dimensional weaving" or "3D weaving" or "multilayer weaving" is meant here a weaving mode whereby at least some of the weft yarns bind warp yarns on several layers of warp yarns or conversely following a weave corresponding to a weave weave which can be chosen in particular from one of the following armor: interlock, multi-fabric, multi-satin and multi-twill.
    By "weave or interlock fabric" is meant here a 3D weave armor, each layer of warp threads binding several layers of weft threads with all the threads of the same warp column having the same movement in the plane of the weave. armor. By "armor or multi-fabric fabric" is meant here a 3D weave with several layers of weft threads whose basic armor of each layer is equivalent to a conventional canvas type armor but with some points of the armor that bind the layers of weft threads together. By "multi-satin weave or fabric" is meant here a 3D weave with several layers of weft yarns whose basic weave of each layer is equivalent to a classic satin-like weave but with certain points of the weave which bind the layers of weft threads together. By "weave or multi-twill fabric" is meant here a 3D weave with several layers of weft threads whose basic armor of each layer is equivalent to a classic twill type armor but with some points of the armor that bind the layers of weft threads together. The fibrous texture can also be achieved by combining a plurality of weave weaves, for example interlock weave at heart and multi-satin skin weave.
    The yarns used to weave the fibrous blank intended to form the fibrous reinforcement of the composite material part may in particular be formed of fibers consisting of one of the following materials: carbon, silicon carbide, alumina. The fibrous blank 100 is woven in the form of a strip extending generally in a direction X corresponding to the longitudinal direction of the blade to be produced. The fibrous blank has a variable thickness determined according to the longitudinal thickness and profile of the blade of the blade to be produced. In its part intended to form a foot preform, the fibrous blank 100 has an extra thickness 103 determined as a function of the thickness of the root of the blade to be produced and which can be made using for example larger title threads. or an insert. The fibrous blank 100 is extended by a portion of decreasing thickness 104 intended to form the stilt of the blade and then by a portion 105 intended to form the blade of the blade. The portion 105 has in a direction perpendicular to the direction X a variable thickness profile between its edge 105a intended to form the leading edge of the blade and its edge 105b intended to form the trailing edge of the blade to be realized . The fibrous blank 100 is woven in one piece and must have, after cutting nonwoven son, the shape and the almost final dimensions of the dawn ("net shape"). For this purpose, in the thickness variation portions of the fibrous blank, as in the decreasing thickness portion 104, the preform thickness decrease is achieved by progressively removing layers of warp and weft yarns. during weaving. Once the weaving of the fibrous blank 100 has been completed, the non-woven yarns are cut, in particular those that have been extracted from the texture at the thickness variation portions. A fibrous structure 200 illustrated in FIG. 2 is then obtained and woven in one piece.
    The fibrous structure 200 comprises a blade root portion 210 and a blade blade portion 220 extending in a longitudinal direction Di between the blade root portion 210 and a blade crown portion 221 and following. a transverse direction Dt between a leading edge portion 222 and a trailing edge portion 223.
    According to one embodiment of the invention, one or more unidirectional folds are placed on the blade blade portion of the fibrous texture, the fibers of each unidirectional fold extending in a determined direction relative to the longitudinal and transverse directions. the blade blade part of the fibrous structure.
    By "unidirectional folds" is meant here fibrous strata consisting of continuous long fibers which are parallel to each other. Figure 3 illustrates a unidirectional fold 30 consisting of a plurality of continuous long fiber strands 311 all extending in the same direction Dp. Each fold may consist of a single row of aligned fibers next to one another or of several superimposed rows as shown in FIG. 3. The fibers are held in place by a connecting means which may be in particular an adhesive agent or a sewing thread, possibly of a fleeting nature.
    In the example described here, two unidirectional folds 310 and 320 are placed on the blade crown edge portion 221 of the blade portion 220 of the fibrous structure 200. The fold 310 is placed on a first face of the portion blade blade 220 while the fold 320 is placed on the other face of the blade blade portion 220. The fibers 311 and 321 respectively unidirectional folds 310 and 320 extend in directions D310 and D320 which are parallel to the transverse direction Dt of the blade blade portion 220 of the fibrous structure 220. According to an alternative embodiment, only one of the two unidirectional folds 310 and 320 may be placed on one of the faces of the blade portion 220. The unidirectional plies may be pre-impregnated, for example with a resin, which allows the ply to adhere directly to the blade portion 220 of the fibrous structure 200. In the case of so-called "dry" non-impregnated plies, a glue in spray or "tackifia nt "can be used to adhere the plies on the blade portion 220 of the fibrous structure 200, the glue evaporating during subsequent heat treatments.
    A fibrous preform 400 consisting of the texture 200 and unidirectional folds 310 and 320 is thus obtained as illustrated in FIG. 4.
    In this embodiment, the fibers 311 and 321 respectively unidirectional folds 310 and 320 are of the same nature as those of the fibrous structure 200. The fibers of the plies 310, 320 and the fibers of the structure 200 are for example carbon, glass, silicon carbide or alumina.
    Thus, thanks to the addition at the blade crown portion 221 of the blade portion 220 of the fibrous structure of unidirectional folds 310 and 320 whose fibers are oriented in the blade section transverse direction Dt 220, the fiber content is increased locally in this direction, which makes it possible to define a specific mechanical behavior of the blade reinforcement in the direction of the fibers of the folds. The tenacity of the 3D or multilayer woven fibrous structure 200 is thus combined with an increase in localized stiffness and oriented in a determined direction, the area concerned here corresponding to the blade tip where the unidirectional folds 310 and 320 have been placed and the direction determined corresponding here to the transverse direction of the blade blade. The resulting blade has, therefore, improved mechanical strength.
    Of course, the fibers of the unidirectional fold or folds added to the fibrous structure can be oriented in any direction with respect to the longitudinal and transverse directions of the blade portion as needed.
    According to another embodiment of the invention, one or more two-dimensional fabric layers may also be used in addition to or in place of the unidirectional folds 310 and 320, which makes it possible to define a specific mechanical behavior of the reinforcement of the dawn in the directions of the threads of the layers of cloth. The yarns of the bidirectional fabric layer (s) may extend in two directions respectively parallel to the longitudinal direction and the transverse direction of the blade blade part of the fibrous structure or in any other directions as required. The increase in stiffness in a determined direction with the addition of one or more unidirectional folds or in two determined directions with the addition of one or more layers of two-dimensional fabric can also be achieved using fibers or wires having a stiffness greater than that of the fibers or threads of the fibrous structure 200.
    The fiber preform 400 is then densified in order to form a blade 10 made of a composite material illustrated in FIG. 5. The densification of the fibrous preform intended to form the fibrous reinforcement of the part to be manufactured consists in filling the porosity of the preform, in all or part of the volume thereof, by the material constituting the matrix. This densification can be carried out in a manner known per se according to the liquid method (CVL) or the gaseous process (CVI), or alternatively in a sequence of these two processes.
    The liquid process consists of impregnating the preform with a liquid composition containing a precursor of the matrix material. The precursor is usually in the form of a polymer, such as a high performance epoxy resin, optionally diluted in a solvent. The preform is placed in a mold that can be sealed with a housing having the shape of the molded final blade. Then, the mold is closed and the liquid matrix precursor (for example a resin) is injected throughout the housing to impregnate the entire fibrous portion of the preform.
    The conversion of the precursor into a matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after removal of the optional solvent and crosslinking of the polymer, the preform being always maintained in the mold having a shape corresponding to that of the piece to realize.
    In the case of the formation of a carbon or ceramic matrix, the heat treatment consists in pyrolyzing the precursor to transform the matrix into a carbon or ceramic matrix according to the precursor used and the pyrolysis conditions. By way of example, liquid precursors of ceramics, in particular of SiC, may be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type resins, whereas liquid carbon precursors may be rate resins. relatively high coke, such as phenolic resins. Several consecutive cycles, from impregnation to heat treatment, can be performed to achieve the desired degree of densification.
    According to one aspect of the invention, in the case in particular of the formation of an organic matrix, the densification of the fiber preform can be carried out by the well-known method of transfer molding known as RTM ("Resin Transfer Molding"). According to the RTM method, the fiber preform is placed in a mold having the external shape of the part to be produced. A thermosetting resin is injected into the inner space of the mold which comprises the fibrous preform. A pressure gradient is generally established in this internal space between the place where the resin is injected and the evacuation ports of the latter in order to control and optimize the impregnation of the preform with the resin.
    The densification of the fiber preform may also be carried out, in a known manner, by gaseous method by chemical vapor infiltration of the matrix (CVI). The fibrous preform corresponding to the fibrous reinforcement of the blade to be produced is placed in an oven in which a gaseous reaction phase is admitted. The pressure and the temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the matrix by deposition, at the heart of the material on contact. fibers, of a solid material resulting from a decomposition of a constituent of the gas phase or a reaction between several constituents, unlike the pressure conditions and temperatures specific to the CVD ("Chemical Vapor Deposition") processes which lead to exclusively to a deposit on the surface of the material.
    The formation of an SiC matrix can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of the MTS while a carbon matrix can be obtained with hydrocarbon gases such as methane and / or propane giving the carbon by cracking.
    A densification combining liquid route and gaseous route can also be used to facilitate implementation, limit costs and production cycles while obtaining satisfactory characteristics for the intended use.
    After densification, a blade 10 of composite material is obtained, which, as illustrated in FIG. 5, comprises in its lower part a root 13 formed by the root portion 210 of the fibrous structure 200 and a blade 15 formed by the part of the blade blade 220 of the fibrous structure. The local increase in stiffness can also be defined in parts of the preform intended to be assembled with a piece having a stiffness greater than that of the resulting blade, as is the case for example when gluing a piece of metal protection on the leading edge of a dawn. In this case, the difference in stiffness between the piece of metallic material and the composite material of the blade can lead to damage or breakage of the assembly. By increasing the stiffness of the composite dawn material by adding one or more unidirectional pleats and / or one or more layers of two-dimensional fabric to the area of the fibrous reinforcement to be joined with the metallic material part it reduces the risk of damage or breakage.
    Figure 6 shows very schematically a fibrous structure 500 from which a fibrous preform according to another embodiment of the invention is formed by adding one or more two-dimensional fabric layers as explained below. The preform obtained is intended to form the fibrous reinforcement of an aeronautical engine blade.
    As already explained above, the fibrous structure 500 is obtained by three-dimensional or multi-layer weaving of a fibrous blank. The fibrous blank from which the fibrous structure 500 is obtained is produced in the same way as the fiber blank 100 already described and will not be described again for the sake of simplification. All the weaving and production variants described in relation to the blank 100 also apply to the fiber blank used to produce the fibrous structure 500.
    The one-piece 3D or multi-layer woven fiber structure 500 comprises a blade root portion 510 and a blade blade portion 520 extending in a longitudinal direction Di between the blade root portion 510 and a portion blade aperture 521 and in a transverse direction Dt between a leading edge portion 522 and a trailing edge portion 523.
    According to the invention, one or more layers of two-dimensional fabric are placed on the blade blade portion of the fibrous texture, the threads of each two-dimensional fabric layer extending in two directions determined with respect to the longitudinal and transverse directions. the blade blade part of the fibrous structure. By "two-dimensional fabric layer" is meant here any fibrous texture woven according to a two-dimensional weave with a first series of son forming an angle, for example 45 ° or 90 °, with a second series of son.
    In the example described here, a two-dimensional fabric layer 610 is placed on the trailing edge portion 523 of the blade portion 520 of the fibrous structure 500. The two-dimensional fabric layer 610 is placed on both the first and second second faces of the blade blade portion 520. The two-dimensional fabric layer comprises first wires 611 which extend in a direction D6ii parallel to the longitudinal direction Di of the blade blade portion 520 of the fiber structure 500 and second wires 612 which extend in a direction D612 parallel to the transverse direction Dt of the blade blade portion 520 of the fibrous structure 500. According to an alternative embodiment, the two-dimensional tissue layer 610 may be placed on only one of the faces of the blade blade portion 520.
    The two-dimensional fabric layer may be pre-impregnated, for example with a resin, which allows the ply to adhere directly to the blade portion 520 of the fibrous structure 500. In the case of a non-impregnated fabric layer known as "dry" "A spray adhesive or" tackifier "may be used to adhere the layer on the blade portion 520 of the fibrous structure 500, the adhesive evaporating during subsequent heat treatments.
    A fibrous preform 700 consisting of the fibrous texture 500 and the two-dimensional fabric layer 610 (FIG. 7) is then obtained. In this embodiment, the wires 611 and 612 of the two-dimensional fabric layer have an elongation rate at break greater than that of the fibers of the fiber structure. In the case for example of a fan blade made of organic matrix composite material (CMO), the fiber preform of the blade can be made from a fibrous texture obtained by weaving HexTow® IM7 carbon fibers on which one or more two-dimensional HexForce® fabric layers are added, the HexForce® fabric comprising carbon fibers having a greater elongation at break than HexTow® IM7 carbon fibers.
    Thus, by adding at the trailing edge portion 523 of the blade portion 520 of the fibrous structure 500 a two-dimensional fabric layer 610 whose yarns have a higher elongation rate at break than that of the fibers of the fibrous structure, the rate of elongation and, consequently, the capacity of the resulting blade to deform without cracking in the area covered by the unidirectional fold is locally increased. The threads 611 and 612 of the two-dimensional fabric layer 610 are respectively oriented in the longitudinal direction Di and the blade section 520 transverse direction Dt, directions in which the resulting blade will present on the area covered by the two-dimensional fabric layer 610 a deformation capacity without increased crack. The resulting blade has, therefore, improved mechanical strength.
    Of course, the yarns of the two-dimensional fabric layer (s) added to the fibrous structure can be oriented in any direction with respect to the longitudinal and transverse directions of the blade portion as needed.
    One or more unidirectional folds may also be used in addition to or in place of the two-dimensional fabric layer 610, which makes it possible to define a specific mechanical behavior of the blade reinforcement, here a greater capacity of deformation without cracking, in the fiber direction of the unidirectional fold or folds.
    The fiber preform 600 is then densified to form a blade made of composite material. The densification of the fibrous preform intended to form the fibrous reinforcement of the part to be manufactured consists in filling the porosity of the preform, in all or part of the volume thereof, with the material constituting the matrix. This densification can be carried out in a manner known per se according to the liquid method (CVL) or the gaseous process (CVI), or alternatively in a sequence of these two processes. For the details of these different densification channels, reference will be made to the densification of the preform 400 already described.
    Of course, the invention can be implemented to confer on the same blade both an increased stiffness in one or more determined zones and a deformation capacity without cracks in one or more other determined zones of the blade. For this purpose, one or more unidirectional plies and / or one or more layers of two-dimensional fabric having fibers or yarns of the same nature or of a stiffness higher than that of the fibers are added to the fibrous texture. fibers of the fibrous texture and, on the other hand, one or more unidirectional folds and / or one or more two-dimensional fabric layers having fibers or yarns having a higher elongation-to-break ratio than the fibers of the structure fibrous.
    权利要求:
    Claims (17)
    [1" id="c-fr-0001]
    A fibrous preform (400) for a turbomachine blade reinforcement made of a composite material, said preform comprising a fibrous structure (200) woven in one piece by three-dimensional or multi-layer weaving between a first plurality of layers of threads (101) and a second plurality of wire layers (102), the fibrous structure (200) including a blade root portion (210) and a blade blade portion (220) extending in a longitudinal direction (Di) between the a blade root portion (210) and a blade crown portion (221) and in a transverse direction (Dt) between a leading edge portion (222) and a trailing edge portion (223), characterized in that said preform (400) further comprises at least one unidirectional pi (310) or a two-dimensional fabric layer (610) present on the blade blade portion (220) of the fibrous texture, the fibers (311) ) of each unidirectional fold extending in a determined direction (D3ii) pa r to the longitudinal (Di) and transverse (Dt) directions of the blade blade portion (220) of the fibrous structure (200) or the yarns (611, 612) of each two-dimensional fabric layer (610); extending in two determined directions (D6ii, D612) with respect to the longitudinal (Di) and transverse (Dt) directions of the blade blade portion (220) of the fibrous structure (200).
    [2" id="c-fr-0002]
    2. Preform according to claim 1, characterized in that the fibers (311) of each unidirectional fold (310) and the son of each layer of two-dimensional fabric (610) are of the same nature as the fibers of the fibrous structure (200) .
    [3" id="c-fr-0003]
    3. Preform according to claim 2, characterized in that one or more unidirectional folds (310, 320) are present on the crown portion (221) of the blade portion (220) of the fibrous structure (200) and the fibers (311, 321) of the unidirectional ply or folds (210, 320) extend in a direction (D3ii, D321) parallel to the transverse direction (Dt) of the blade blade portion (220) of the fibrous structure.
    [4" id="c-fr-0004]
    4. Preform according to claim 2 or 3, characterized in that one or more bidirectional fabric layer are present on the crown portion (221) of the blade portion (220) of the fibrous structure (200) and in that the yarns (611, 621) of the bidirectional fabric layer (s) extend in two directions (D6ii, D612) respectively parallel to the longitudinal direction (Di) and the transverse direction (Dt) of the blade portion dawn (220) of the fibrous structure.
    [5" id="c-fr-0005]
    5. Preform according to claim 1, characterized in that the fibers of each unidirectional fold and the son (611, 612) of each layer of two-dimensional fabric (610) have an elongation rate at break greater than that of the fibers of the fibrous structure (500).
    [6" id="c-fr-0006]
    6. Preform according to claim 5, characterized in that one or more unidirectional folds are present on the trailing edge portion (223) of the blade portion (220) of the fibrous structure (200) and in that the fibers or unidirectional folds extend in a direction parallel to the longitudinal direction (Di) of the blade blade portion (220) of the fibrous structure.
    [7" id="c-fr-0007]
    The preform according to claim 5, characterized in that one or more two-dimensional fabric layer (610) is present on the trailing edge portion (223) of the blade portion (220) of the fibrous structure (200). and in that the yarns (611, 612) of the two-dimensional fabric layer (s) extend in two directions respectively parallel to the longitudinal direction (Di) and to the transverse direction (Dt) of the blade blade portion. (220) of the fibrous structure.
    [8" id="c-fr-0008]
    8. A turbomachine blade comprising a fiber reinforcement densified by a matrix characterized in that the fibrous reinforcement consists of a fibrous preform (400; 700) according to any one of claims 1 to 7.
    [9" id="c-fr-0009]
    9. A turbomachine characterized in that it comprises a plurality of blades according to claim 8.
    [10" id="c-fr-0010]
    10. A method of manufacturing a fiber reinforcement turbomachine blade composite material, said method comprising the production of a fibrous structure (200) woven in one piece by three-dimensional weaving or multilayer between a first plurality of layers of son (101) and a second plurality of wire layers (102), the fibrous structure (200) comprising a blade root portion (210) and a blade blade portion (220) extending in a longitudinal direction (Di) between the blade root portion (210) and a blade crown portion (221) and in a transverse direction (Dt) between a leading edge portion (222) and a leading edge portion leak (223), characterized in that said method further comprises placing at least one unidirectional fold (310) or a two-dimensional fabric layer (610) on the blade blade portion (220) of the fibrous texture (200), the fibers (311) of each unidirectional fold (310) extending from in a given direction (D3ii) with respect to the longitudinal (Di) and transverse (Dt) directions of the blade blade part (220) of the fibrous structure and the wires (611, 612) of each two-dimensional fabric layer ( 610) extending in two determined directions (D6ii, D612) relative to the longitudinal (Di) and transverse (Dt) directions of the blade blade portion (220) of the fibrous structure (200).
    [11" id="c-fr-0011]
    11. The method of claim 10, characterized in that the fibers (311) of each unidirectional fold (310) and the son of each layer of two-dimensional fabric (610) are of the same nature as the fibers of the fibrous structure (200) .
    [12" id="c-fr-0012]
    Method according to claim 11, characterized in that one or more unidirectional pleats (310, 320) are placed on the crown portion (221) of the blade portion (220) of the fibrous structure (200) and the fibers (311, 321) of the unidirectional ply (s) extend in a direction parallel to the transverse direction (Dt) of the blade blade portion (220) of the fibrous structure.
    [13" id="c-fr-0013]
    Method according to claim 11 or 12, characterized in that one or more bidirectional fabric layers are placed on the crown portion (221) of the blade portion (220) of the fibrous structure (200) and in that the yarns (611, 621) of the bidirectional fabric layer (s) extend in two directions (D6ii, D612) respectively parallel to the longitudinal direction (Di) and the transverse direction (Dt) of the blade portion dawn (220) of the fibrous structure.
    [14" id="c-fr-0014]
    14. The method of claim 10, characterized in that the fibers of each unidirectional fold and the son (611, 612) of each layer of two-dimensional fabric (610) have an elongation rate at break greater than that of the fibers of the fibrous structure (500).
    [15" id="c-fr-0015]
    The method of claim 14, characterized in that one or more unidirectional pleats (610) are placed on the trailing edge portion (223) of the blade portion (220) of the fibrous structure (200) and the fibers (611) of the unidirectional ply (s) (610) extend in a direction parallel to the longitudinal direction (Di) of the blade blade portion (220) of the fibrous structure.
    [16" id="c-fr-0016]
    The method of claim 14, characterized in that one or more two-dimensional fabric layers (610) are placed on the trailing edge portion (223) of the blade portion (220) of the fibrous structure (200). and in that the yarns (611, 612) of the two-dimensional fabric layer (s) extend in two directions respectively parallel to the longitudinal direction (DI) and the transverse direction (Dt) of the blade blade portion. (220) of the fibrous structure.
    [17" id="c-fr-0017]
    17. A method of manufacturing a turbomachine blade comprising the manufacture of a fibrous reinforcement according to the method as defined in any one of claims 10 to 16 and the densification of said fibrous reinforcement with a matrix.
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    同族专利:
    公开号 | 公开日
    FR3040909B1|2018-03-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4118147A|1976-12-22|1978-10-03|General Electric Company|Composite reinforcement of metallic airfoils|
    EP2458153A2|2010-11-29|2012-05-30|United Technologies Corporation|Impact tolerant composite airfoil for a turbine engine|
    WO2013088038A2|2011-12-14|2013-06-20|Snecma|Fiber structure intended to reinforce composite material parts and including a portion having a reduced thickness|
    EP2843193A1|2013-08-28|2015-03-04|Techspace Aero S.A.|Composite blade made by additive manufacturing|
    FR3011253A1|2013-10-01|2015-04-03|Snecma|FIBROUS STRUCTURE WITH FLEET COMBINATION|FR3087701A1|2018-10-30|2020-05-01|Safran Aircraft Engines|HYBRIDIZATION OF THE FIBROUS REINFORCEMENT FIBERS OF A BLOWER BLADE|
    WO2021038173A1|2019-08-28|2021-03-04|Safran Aircraft Engines|Hybridization of the fibers of the fibrous reinforcement of a fan blade|
    FR3100471A1|2019-09-10|2021-03-12|Safran Aircraft Engines|Composite blade preform|
    FR3108143A1|2020-03-13|2021-09-17|Safran Aircraft Engines|Turbomachine blade comprising a part made of a composite material comprising 3D woven fibers|
    WO2021191531A1|2020-03-27|2021-09-30|Safran Aircraft Engines|Fibrous texture for turbine engine blade made of composite material|
    WO2021255378A1|2020-06-18|2021-12-23|Safran Aircraft Engines|Turbomachine blade having a metallic leading edge|
    法律状态:
    2016-09-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-17| PLSC| Search report ready|Effective date: 20170317 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1558680|2015-09-16|
    FR1558680A|FR3040909B1|2015-09-16|2015-09-16|FIBROUS PREFORMS FOR TURBOMACHINE DRAWINGS OF COMPOSITE MATERIAL AND METHOD FOR MANUFACTURING SUCH A PREFORM|FR1558680A| FR3040909B1|2015-09-16|2015-09-16|FIBROUS PREFORMS FOR TURBOMACHINE DRAWINGS OF COMPOSITE MATERIAL AND METHOD FOR MANUFACTURING SUCH A PREFORM|
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