• 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 composite material blade body (400) comprises a matrix densified fibrous reinforcement, the blade body extending in a longitudinal direction (DL) between a foot portion or lower portion (403) and an apex vane or an upper portion (406) and, in a transverse direction (DT), between a leading edge (405a) and a trailing edge (405b). The fiber reinforcement of the blade body comprises a first portion (401) consisting of a plurality of layers of yarn interconnected by three-dimensional weaving or multilayer weave and a second portion (410) forming all or part of at least one edge of attack (405a) or a vanishing trailing edge (405b). The second portion (410) comprises a plurality of randomly oriented short fibers, the yarns of the plurality of yarn layers of the first portion (401) and the short staple fibers of the second portion (410) being embedded in the die.
    公开号:FR3081370A1
    申请号:FR1854234
    申请日:2018-05-22
    公开日:2019-11-29
    发明作者:Thomas Alain DE GAILLARD；Clement Pierre Postec；Charles-Henri Claude Jacky Sullet
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Invention background
    The present invention relates to the general field of the manufacture of blades of composite material comprising a fibrous reinforcement densified by a matrix, the matrix being obtained by injection of a liquid composition containing a precursor of the matrix in a fibrous preform.
    One area targeted is that of gas turbine blades for aeronautical engines or industrial turbines and, more particularly but not exclusively, fan blades for aeronautical engines.
    The manufacture of a composite material blade comprises the following steps:
    a) production of a fibrous structure by three-dimensional or multilayer weaving,
    b) compacting and shaping of the fibrous structure,
    c) placing the fibrous preform thus obtained in an injection molding tool (RTM),
    d) injection of a liquid precursor composition of a matrix material such as a resin into the fibrous preform,
    e) transformation of the liquid composition into a matrix so as to obtain a profiled element of composite material comprising a fibrous reinforcement densified by a matrix.
    The production of a composite material blade obtained from a fibrous reinforcement produced by three-dimensional weaving and densified by a matrix is described in particular in document US 2005/0084377.
    The three-dimensional (3D) or multi-layer weaving makes it possible to give the resulting composite material blade very good mechanical strength. However, the good mechanical strength conferred by three-dimensional or multi-layer weaving is more difficult to obtain in parts of the blade having small thicknesses, of the order of 1 mm to 2 mm as is the case at the edge d attack and / or flight from a dawn. Indeed, from a mechanical point of view and in accordance with the certification requirements, the leading edge and the trailing edge must be able to resist or limit damage when they are subjected to various stresses such as bird strikes or the repetition of flight cycles (erosion / service life).
    The difficulty in obtaining thin portions with good mechanical strength by three-dimensional weaving is explained by:
    - the size or the important title of the strands or threads used for 3D or multilayer weaving which is of the order of a millimeter, and
    - the number of layers of strands or threads required in warp and weft to ensure good mechanical strength because it is more difficult to obtain optimal mechanical strength by interlacing only two layers of threads (minimum number of layers of warp threads or weft to form a 3D or multi-layer weaving) than by interlacing a greater number of layers of threads.
    Subject and summary of the invention
    The present invention therefore aims to provide a solution for a blade of composite material which does not have the aforementioned drawbacks and which makes it possible to easily form fine parts on the blade with good mechanical properties.
    To this end, the invention provides in particular a blade body of composite material comprising a fibrous reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a portion of the foot or lower portion and a vertex d blade or an upper portion and, in a transverse direction, between a leading edge and a trailing edge, characterized in that the fibrous reinforcement of the blade body comprises a first part consisting of a plurality of layers of wires linked together by three-dimensional or multilayer weaving and a second part forming all or part of at least one leading edge or a trailing edge of the blade, the second part comprising a plurality of short fibers randomly oriented, the threads of the plurality of layers of yarns of the first portion and the short fibers of the second portion being embedded in the matrix.
    By combining in the same fibrous reinforcement a three-dimensional or multi-layer weaving with short fibers, it is possible to obtain a blade body with fine thicknesses at the leading and / or trailing edge while ensuring good hold. blade body mechanics. The short fibers provide rigidity which ensures good mechanical strength in the fine parts of the blade body where three-dimensional or multi-layer weaving is absent. The use of short fibers offers great freedom of design and allows fine parts to be made over a small area or, conversely, over a large area.
    According to a first particular characteristic of the blade body of the invention, the second part forms a part of the blade leading edge, the second part extending in the longitudinal direction over a height less than the total height of the edge. dawn attack. It is thus possible to use the short fibers to define a fine leading edge only in the part of the blade body where there are aerodynamic needs.
    According to a second particular characteristic of the blade body of the invention, the short fibers are carbon fibers having a length between 1 mm and 50 mm or a length between 0.1 mm and 1 mm.
    The invention also relates to a blade made of composite material comprising a blade body according to the invention, in which the second part of the blade body forms all or part of a blade leading edge and in which the edge blade attack further comprises a metal foil covering the second part. A blade is thus obtained comprising a leading edge which is both fine and resistant to impacts with foreign bodies.
    The blade can be in particular a fan blade, an outlet guide blade, an inlet guide blade, or a blade with variable setting angle.
    The invention also relates to a method of manufacturing a blade body of composite material comprising:
    - the production of a fibrous preform,
    - placing the fiber preform in an injection mold,
    - injecting a resin into the preform,
    - The transformation of the resin into a matrix so as to obtain a blade body of composite material comprising a fibrous reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a portion of the foot or lower portion and a blade tip or an upper portion and, in a transverse direction, between a leading edge and a trailing edge of the blade, characterized in that the fiber preform of the blade body comprises a first part consisting of '' a plurality of layers of yarns linked together by three-dimensional or multilayer weaving and a second part consisting of short fibers randomly oriented, the short fibers of the second part being placed adjacent to the first part in a part of the mold d injection corresponding to all or part of at least the leading edge or the trailing edge of the blade.
    By combining in the same fibrous reinforcement a three-dimensional or multi-layer weaving with short fibers, it is possible to obtain a blade body with fine thicknesses at the leading and / or trailing edge while ensuring good hold. blade body mechanics. The short fibers provide rigidity which ensures good mechanical strength in the fine parts of the blade body where three-dimensional or multi-layer weaving is absent. The use of short fibers offers great freedom of design and allows fine parts to be made over a small area or, conversely, over a large area.
    In addition, with the method of the invention, the scraps of threads or strands from three-dimensional or multilayer weaving can be advantageously used to supply the short fibers, which makes it possible to control the cost of manufacturing the blade body. The method of manufacturing the blade body of the invention is also simple to implement.
    According to a first particular characteristic of the process of the invention, the short fibers of the second part are placed adjacent to the first part in a part of the injection mold corresponding to a part of the leading edge of the blade according to the longitudinal direction.
    According to a second particular characteristic of the process of the invention, the short fibers are carbon fibers having a length between 1 mm and 50 mm or a length between 0.1 mm and 1 mm.
    The invention also relates to a method of manufacturing a blade of composite material comprising the production of a blade body according to the invention, in which the second part of the blade body forms all or part of the edge of the blade. 'blade attack, the method further comprising fixing a metal foil on the second part.
    Brief description of the drawings
    Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of nonlimiting examples, with reference to the appended drawings, in which:
    FIG. 1 very schematically illustrates a three-dimensional woven fibrous blank intended for the production of a fibrous structure in accordance with an embodiment of the invention;
    Figure 2 is a schematic view of a fibrous structure obtained from the fibrous blank of Figure 1;
    Figure 3 is a schematic view of a fibrous structure after removal of a leading edge portion;
    Figure 4 is a schematic perspective view showing the placement of the fiber structure of Figure 4 and a portion of short fibers in an injection mold;
    Figure 5 is a schematic perspective view showing the placement of the injection mold in an injection tool;
    FIG. 6 is a schematic perspective view showing the carrying out of an operation of injecting a liquid composition of matrix precursor into the fiber preform in order to obtain a blade body made of composite material;
    Figure 7 is a schematic perspective view of the blade body of composite material obtained after the operation of Figure 6;
    Figure 8 is a schematic perspective view showing the assembly of a metal foil on the trailing edge of the blade body of Figure 7;
    Figure 9 is a schematic perspective view showing a blade of composite material obtained after assembly of the metal foil on the trailing edge of the blade body;
    FIG. 10 is a cross-sectional view of the blade of FIG. 9.
    Detailed description of embodiments
    The invention applies generally to the production of blade bodies or blades of composite material produced from a fibrous preform into which a liquid composition, precursor of a matrix material, is injected and then transformed. so as to obtain a blade comprising a fibrous reinforcement densified by a matrix. Non-limiting examples of such blades are in particular the fan blades, the outlet guide vanes (called OGV for “Outlet Guide Vane”), the inlet guide vanes (called IGV for “Inlet Guide Vane”), the vanes for variable setting angle (called VSV for “Variable Stator Vane”), etc.
    A manufacturing method in accordance with the invention is described in relation to the manufacture of a turbomachine fan blade. The process for manufacturing a blade of composite material according to the invention begins with the production of a fibrous blank obtained by three-dimensional weaving or by multilayer weaving.
    By three-dimensional weaving or 3D weaving is meant here a mode of weaving by which at least some of the warp threads link weft threads on several weft layers such as for example interlock weaving. By interlock weaving is meant here a 3D weaving weave in which each layer of warp links several layers of wefts with all the threads of the same warp column having the same movement in the plane of the weave.
    By multilayer weaving, we mean here a 3D weaving with several weft layers whose basic weave of each layer is equivalent to a conventional 2D fabric weave, such as a weave of canvas, satin or twill type, but with certain points of the weave which link the weft layers together.
    The production of the fibrous structure by 3D or multilayer weaving makes it possible to obtain a connection between the layers, therefore to have good mechanical strength of the fibrous structure and of the piece of composite material obtained, in a single textile operation.
    An exemplary embodiment of a fibrous structure according to the invention is now described. In this example, the weaving is carried out on a Jacquard type loom.
    FIG. 1 very schematically shows the weaving of a fibrous blank 100 from which a fibrous structure 200 can be extracted (FIG. 2) making it possible to obtain a fibrous reinforcement preform of a blade body of an aeronautical engine.
    The fibrous blank 100 is obtained by three-dimensional weaving, or 3D weaving, or by multilayer weaving produced in a known manner by means of a jacquard type loom on which a bundle of warp or strand wires 101 has been placed in a plurality of layers, the warp threads being linked by weft layers 102 also arranged in a plurality of layers, some weft layers comprising braids as explained below in detail. A detailed embodiment of a fibrous preform intended to form the fibrous reinforcement of a blade for an aeronautical engine from a 3D woven fibrous blank is in particular described in detail in the documents US 7 101 154, US 7 241 112 and WO 2010/061140.
    The fibrous blank 100 is woven in the form of a strip extending generally in a longitudinal direction Dl corresponding to the longitudinal direction of the blade to be produced. In the fiber blank 100, the fiber structure 200 has a variable thickness determined as a function of the longitudinal thickness and of the profile of the blade of the blade to be produced. In its part intended to form a foot preform, the fibrous structure 200 has an additional thickness 203 determined as a function of the thickness of the blade root to be produced. The fibrous structure 200 is extended by a portion of decreasing thickness 204 intended to form the stilt of the blade and then by a portion 205 intended to form a blade of the blade. The part 205 has in a transverse direction Dt perpendicular to the longitudinal direction Dl a profile of variable thickness between its edge 205a intended to form a portion of the leading edge of the blade and its edge 205b intended to form a trailing edge of dawn. The part 205 comprises first and second faces 205c and 205d extending between the edges 205a and 205b (FIG. 2) and intended to form the lower face and the upper face, or vice versa, of the blade of the blade.
    The fibrous structure 200 is woven in a single piece and must have, after cutting the nonwoven threads of the blank 100, the almost definitive shape and dimensions of the blade (“net shape”), in practice by being modulated over-lengths of fiber and over-thicknesses of resin which will then be machined. To this end, in the thickness variation parts of the fibrous structure, as in the decreasing thickness part 204, the reduction in thickness of the preform is obtained by gradually removing weft layers during weaving.
    Once the weaving of the fibrous structure 200 in the blank 100 is completed, the nonwoven threads are cut. The fibrous structure 200 illustrated in FIG. 2 is then obtained, a structure woven in one piece. The edge 205a of the fibrous blank 200 is intended to form a blade leading edge, this leading edge having to have at least in its upper part a small thickness, for example less than 3 mm. This small thickness is difficult to achieve with three-dimensional weaving because of a too large size or title of the warp and weft threads. Furthermore, such a small thickness can only be obtained with three-dimensional weaving by using a minimum number of layers of warp and weft threads, namely two layers of warp threads and one layer of weft threads or vice versa, insufficient number to ensure mechanical strength equivalent to that obtained in the rest of the fibrous structure which comprises a greater number of layers of warp threads and layers of weft threads.
    In the example described here, the part of the leading edge of the blade which must have the small thickness incompatible with a three-dimensional weaving is represented by the part 206 of the fibrous structure illustrated in FIG. 2. The part 206 extends on a height H206 which is less than the total height hbosa of the edge 205a in the longitudinal direction Dl. Part 206 corresponds to the leading edge part of the final blade body which must meet aerodynamic needs. The rest of the edge 205a situated between the part of decreasing thickness 204 and the part 206 in the longitudinal direction D1 can be kept in the form of three-dimensional weaving because it is not necessary to reduce the thickness as much as at the level of the portion 206. The height H206 of the part 206 generally corresponds to 40% or less of the total height H2osa of the trailing edge to be produced. However, the part 206 may extend over a greater height in the longitudinal direction, or even over the entire height H205a of the edge 205a.
    In accordance with the invention and as illustrated in FIG. 3, the part 206 is separated from the fibrous structure 200, for example by cutting, in order to be replaced by a part obtained from short fibers as explained below in detail . According to an alternative embodiment, the part 206 of the fibrous structure 200 may not be woven, the float yarns present in this portion being cut at the end of the weaving.
    The next step is to place the fibrous structure 200 in an injection mold 50 (Figure 4). The mold 50 comprises a first shell 51 comprising at its center a first imprint 511 corresponding in part to the shape and dimensions of the blade to be produced, the imprint 511 being surrounded by a first contact plane 512. The first shell 51 further comprises an injection port 510 intended to allow the injection of a liquid matrix precursor composition into a fibrous preform. The tool 50 also includes a second shell 52 comprising at its center a second imprint 521 corresponding in part to the shape and dimensions of the blade to be produced, the second imprint 521 being surrounded by a second contact plane 522 intended to cooperate with the first contact plane 512 of the first shell 51. The second shell further comprises an evacuation port 520 intended to cooperate with a pumping system.
    The first and second shells can in particular be made of metallic material such as aluminum for example or of graphite.
    The fibrous structure 200 is firstly positioned in the cavity 511 of the first shell 51 as illustrated in FIG. 4. The first shell comprises a part 511a of the cavity 511 corresponding to the part 206 of the fibrous structure which has been withdrawn. Once the fibrous structure 200 is placed in the first shell 51, the part 511a is filled with a plurality of short fibers 210, for example short carbon fibers, as illustrated in FIG. 4. The short fibers 210 are placed randomly , that is to say without determined orientation. The short fibers have a diameter much smaller than the diameter of the warp and weft threads or strands used to weave the fibrous structure 200, the short fibers having for example a diameter less than or equal to 50 μm. The short fibers typically have a length of between 0.1 mm and 1 mm. However, so-called “intermediate” short fibers between 1 mm and 50 mm in length can also be used. Advantageously, the scraps of the threads or strands resulting from the manufacture of the fibrous structure can be used as a means of supplying short fibers, for example after multiple cuts which allow the fibers present in the threads or strands to be untied and short fibers of small diameter
    The second shell 52 is then placed on the first shell 51 in order to close the shaping tool 50, the second shell 52 comprising a part 521a of the imprint 512 corresponding to the part filled with short fibers 210.
    Once the tool 50 is closed as illustrated in FIG. 5, the first and second shells are in a position called “assembly position”, that is to say a position in which the first and second impressions 511, 521 are placed opposite one another while the first and second contact planes 512 and 522 are also opposite one another. In this configuration, the first and second indentations 511, 521 together define an internal volume 53 having the shape of the blade body to be produced and in which the fibrous structure 200 and the short fibers 210 are placed. In the example described here, the imprint 511 is intended to form the lower surface side of the blade preform while the imprint 521 is intended to form the upper side of the blade preform.
    The mold 50 containing the fibrous structure 200 and the short fibers 210 can be placed in a compacting and forming tool 60 (FIG. 5). The tool 60 comprises a lower part 61 on which the first shell 51 of the tool 50 rests and an upper part 62 placed on the second shell 52 of the tool 50. The compacting and forming tool 60 is subjected to the application of a compaction pressure PC applied for example by placing the tool 60 in a press (not shown in FIG. 5). The application of the PC pressure brings the first and second shells 51 and 52 closer together until the first and second contact planes 512 and 522 meet, which makes it possible both to compact the fibrous structure 200 and the short fibers 210 according to a determined rate of compaction in order to obtain a rate of fibers also determined and to shape the fibrous structure according to the profile of the blade to be manufactured. This gives a preform 300 consisting of the fibrous structure 200 and short fibers 210 having the shape of the blade to be produced (FIG. 6). The preform 300 has a profile of variable thickness between its edge 305a intended to form a blade leading edge and its edge 305b intended to form a blade trailing edge. The preform 300 includes first and second faces 305c and 305d extending between the edges 305a and 305b and intended to form the lower surface and the upper surface, or vice versa, of the blade of the blade. The preform 300 comprises a first part 301 made up of a plurality of layers of yarns 101 and 102 (FIG. 1) linked together by three-dimensional or multilayer weaving and a second part 310 made up of short fibers 210 randomly oriented.
    In FIG. 6, the mold 50 is placed between a lower part 71 and an upper part 72 of an injection tool 70. The lower part 71 and the upper part 72 of the tool 70 are equipped with heating means ( not shown in Figure 6). Once the tool 70 is closed, the blade is then molded by impregnating the preform 300 with a thermosetting resin which is polymerized by heat treatment. The well known injection or transfer molding process known as RTM (Resin Transfer Molding) is used for this purpose. In accordance with the RTM process, a resin 530, for example a thermosetting resin, is injected via the injection port 510 of the first shell 51 into the internal space 53 defined between the two cavities 511 and 521 and occupied by the preform 300. The port 520 of the second shell 52 is connected to an evacuation duct maintained under pressure (not shown in FIG. 6). This configuration allows the establishment of a pressure gradient between the lower part of the preform 300 where the resin is injected and the upper part of the preform located near the port 520. In this way, the resin 530 injected substantially at the level of the lower part of the preform will gradually permeate all of the preform by circulating therein to the discharge port 520 through which the surplus is discharged. Of course, the first and second shells 51 and 52 of the mold 50 may respectively comprise several injection ports and several discharge ports.
    The resin used can be, for example, an epoxy resin of temperature class 180 ° C (maximum temperature supported without loss of characteristics). Resins suitable for RTM processes are well known. They preferably have a low viscosity to facilitate their injection into the fibers. The choice of the temperature class and / or the chemical nature of the resin is determined according to the thermomechanical stresses to which the part must be subjected. Once the resin has been injected into all of the reinforcement, it is polymerized by heat treatment in accordance with the RTM process.
    After injection and polymerization, the blade body is removed from the mold. It can possibly undergo a post-curing cycle to improve its thermomechanical characteristics (increase in the glass transition temperature). In the end, the blade is cut to remove the excess resin and the chamfers are machined. No other machining is necessary since, the part being molded to the almost definitive dimensions of the blade, it complies with the dimensions required after the clipping machining.
    As illustrated in FIG. 7, there is obtained a blade body 400 formed of a fibrous reinforcement densified by a matrix, the blade body comprising a blade 405 extending in a longitudinal direction Dl between a portion of the foot or portion lower 403 and a blade tip or an upper portion 406 and, in a transverse direction Dt, between a leading edge 405a and a trailing edge 405b. According to the invention, the fibrous reinforcement of the blade body 400 comprises a first part 401 consisting of the plurality of layers of wires (wires 101 and 102 in FIG. 1) linked together by three-dimensional or multilayer weaving and a second part 410 adjacent to the first portion forming a part of the leading edge of the blade body, the second part 410 comprising the plurality of short fibers randomly oriented (short fibers 210 in FIG. 4). The threads of the plurality of layers of threads of the first part 401 and the short fibers of the second part 410 are embedded in the matrix, the matrix thus ensuring cohesion between the part of the reinforcement made up of woven threads and the part of the reinforcement made up short fibers.
    The blade body thus obtained can be used as it is, that is to say already constitute a blade, for applications where there is no risk of impact with foreign bodies, for example birds.
    Otherwise, for example for an aeronautical engine fan blade, it is necessary to protect the leading edge of the blade body because the transition between the first part 401 comprising the woven wires and the second part 410 comprising the short fibers may have insufficient mechanical strength against impacts with foreign bodies. To this end, as illustrated in FIG. 8, a metal foil 500 is assembled, for example by gluing, on the leading edge 405a of the blade body. The assembly of the foil with the blade body can also be carried out at the same time as the injection and polymerization of the resin. In this case, the foil is positioned in the injection mold with the fibrous structure, the fixing of the foil to the blade body being produced by co-firing.
    After assembly, a blade 600 of composite material is obtained comprising a blade 605 extending in a longitudinal direction Dl between a foot or lower portion 603 and a top or an upper portion 606 and, in a transverse direction Dt, between an edge d attack 605a and a trailing edge 605b. The leading edge here is constituted at least in part by the metal foil 500 which covers the second part 410 (FIG. 9). More specifically, as illustrated in FIG. 10, the metal foil 500 comprises a solid nose 510 forming the edge of the leading edge and two fins 520 and 530 extending from the nose 510 and respectively on the side of the lower surface 605c and the extrados 605d face of the dawn. The fins make it possible to compensate for the difference in stiffness between the first part 401 and the second part 5 410 and to ensure the management of the forces, which makes it possible to give the blade sufficient mechanical strength.
    Depending on the requirements for mechanical strength of the blade body, the shape of the transition between the first part 401 and the second part 410 may be different from a rectilinear geometry 10 as illustrated here. The transition between these two parts can for example have an oblique shape or an arc.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Blade body of composite material (400) comprising a fibrous reinforcement (200) densified by a matrix, the blade body extending in a longitudinal direction (DL) between a portion of foot or lower portion (403) and a blade tip or an upper portion (406) and, in a transverse direction (DT), between a leading edge (405a) and a trailing edge (405b), characterized in that the fibrous reinforcement of the body blade comprises a first part (401) made up of a plurality of layers of threads linked together by three-dimensional or multilayer weaving and a second part (410) forming all or part of at least one leading edge (405a) or a blade trailing edge (405b), the second part (410) comprising a plurality of short fibers randomly oriented, the wires of the plurality of layers of wires of the first part (401) and the short fibers of the second part (410) being embedded in the matrix.
    [2" id="c-fr-0002]
    2. blade body according to claim 1, wherein the second part (410) forms a part of the blade leading edge (405a), the second part (401) extending in the longitudinal direction (DL) over a height (H206) less than the total height (H205a) of the blade leading edge.
    [3" id="c-fr-0003]
    3. blade body according to claim 1 or 2, wherein the short fibers are carbon fibers having a length between 1 mm and 50 mm.
    [4" id="c-fr-0004]
    4. blade body according to any one of claims 1 to 3, wherein the short fibers are carbon fibers having a length between 0.1 mm and 1 mm.
    [5" id="c-fr-0005]
    5. blade made of composite material (600) comprising a blade body (400) according to any one of claims 1 to 4, in which the second part (410) of the blade body forms all or part of an edge blade leading edge (405a) and wherein the blade leading edge further comprises a metal foil (500) covering the second part (410).
    [6" id="c-fr-0006]
    6. Dawn according to claim 5, the blade (600) is a blade from at least one fan blade, an outlet guide blade, an inlet guide blade, or a blade with variable pitch angle.
    [7" id="c-fr-0007]
    7. Method for manufacturing a blade body of composite material (400) comprising:
    - producing a fibrous texture (200),
    - placing the fibrous texture (500) in an injection mold (50),
    - injecting a resin (530) into the fiber preform (300),
    - The transformation of the resin into a matrix so as to obtain a blade body of composite material (400) comprising a fibrous reinforcement (200) densified by a matrix, the blade body extending in a longitudinal direction (DL ) between a foot portion or lower portion (403) and a blade tip or an upper portion (406) and, in a transverse direction (DT), between a leading edge (405a) and a trailing edge d blade (405b), characterized in that the fiber preform of the blade body (300) comprises a first part (301) made up of a plurality of layers of threads linked together by three-dimensional or multilayer weaving and a second part ( 310) consisting of short fibers randomly oriented, the short fibers of the second part (310) being placed adjacent to the first part (301) in a part (511a) of the injection mold (50) corresponding to all or part of at least the leading edge e (405a) or the trailing edge of the blade (405b).
    [8" id="c-fr-0008]
    8. The method of claim 7, wherein the short fibers of the second part (310) are placed adjacent to the first part (301) in a part of the injection mold corresponding to a part of the leading edge d 'blade in the longitudinal direction.
    [9" id="c-fr-0009]
    9. The method of claim 7 or 8, wherein the short fibers are carbon fibers having a length between 1 mm and 50 mm.
    5
    [10" id="c-fr-0010]
    10. Method according to any one of claims 7 to 9, in which the short fibers are carbon fibers having a length of between 0.1 mm and 1 mm.
    [11" id="c-fr-0011]
    11. A method of manufacturing a blade made of composite material 10 (600) comprising producing a blade body (400) according to the method of any one of claims 7 to 10, the second part (410) of the body blade forms all or part of the blade leading edge (405a), the method further comprising fixing a metal foil (500) on the second part (410).
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    同族专利:
    公开号 | 公开日
    US11015462B2|2021-05-25|
    FR3081370B1|2020-06-05|
    US20190360345A1|2019-11-28|
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    法律状态:
    2019-04-18| PLFP| Fee payment|Year of fee payment: 2 |
    2019-11-29| PLSC| Search report ready|Effective date: 20191129 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1854234|2018-05-22|
    FR1854234A|FR3081370B1|2018-05-22|2018-05-22|BLADE BODY AND BLADE OF COMPOSITE MATERIAL HAVING FIBROUS REINFORCEMENT COMPOSED OF THREE-DIMENSIONAL WEAVING AND SHORT FIBERS AND THEIR MANUFACTURING METHOD|FR1854234A| FR3081370B1|2018-05-22|2018-05-22|BLADE BODY AND BLADE OF COMPOSITE MATERIAL HAVING FIBROUS REINFORCEMENT COMPOSED OF THREE-DIMENSIONAL WEAVING AND SHORT FIBERS AND THEIR MANUFACTURING METHOD|
    US16/418,147| US11015462B2|2018-05-22|2019-05-21|Blade body and a blade made of composite material having fiber reinforcement made up both of three-dimensional weaving and also of short fibers, and method of fabrication|
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