• 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:
    The invention relates to a method for producing a fibrous preform (10) woven impregnated with a matrix precursor resin, said resin having in the green state a glass transition temperature Tg °, the process comprising: impregnation of threads or strands (41) with the resin, feeding a loom (20) with the impregnated yarns or strands maintained at a temperature of between Tg0 and Tg0 + 10 ° C, and weaving yarns or strands into the loom to obtain the woven fiber preform impregnated with resin. The invention also relates to a method of manufacturing a composite material part and an installation for manufacturing the fiber preform.
    公开号:FR3059266A1
    申请号:FR1661642
    申请日:2016-11-29
    公开日:2018-06-01
    发明作者:Bernard Serge Most Vincent；Jean Francois Techer Marc-Emmanuel
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    (54) PROCESS FOR MANUFACTURING A WOVEN FIBROUS PREFORM AND A PART OF COMPOSITE MATERIAL.
    (© The invention relates to a process for manufacturing a woven fibrous preform (10) impregnated with a matrix precursor resin, said resin having in the raw state a glass transition temperature Tg °, the process comprising: impregnation of threads or strands (41) with the resin, feeding a weaving loom (20) with the impregnated threads or strands maintained at a temperature between Tg ° and Tg ° + 10 ° C, and the weaving of yarns or strands in the loom in order to obtain the woven fiber preform impregnated with resin The invention also relates to a process for manufacturing a piece of composite material and an installation for manufacturing the fiber preform.
    1.
    Invention background
    The present invention relates to the general field of methods for manufacturing woven fibrous preforms and parts made of composite material comprising a fibrous reinforcement densified by a matrix.
    The use of composite materials is now common in the aeronautical field, in order to reduce the mass of parts to increase the overall efficiency of the engine. For example, the blades or the casing of the fan of an aeronautical turbomachine are now made of composite material with an organic matrix.
    To manufacture parts of complex shape such as those mentioned above, the resin injection molding or RTM (“Resin Transfer Molding”) process is known in particular. This well-known process consists in shaping a dry fibrous preform previously woven into a mold, then in injecting resin inside the porosity of said preform in order to obtain, after heat treatment of polymerization of the resin, the composite material part.
    However, the RTM process has drawbacks. To ensure good mechanical resistance of the parts thus produced, it is generally necessary to increase the toughness of the resin by adding additives which increase its viscosity. Such a more viscous resin is difficult to use in the RTM process, because of the high injection pressures it requires. In addition, during injection, preferential paths for the resin form in the preform, which leaves porosities in the final part which are difficult to remove. Similarly, when using strands of fibers, the injected resin generally has more difficulty in plugging the microporosities present between the fibers and between the strands. Finally, the aforementioned problems reduce the homogeneity of the polymerization reaction during the curing of the resin, which can, in the long term, create internal stresses in the final part and reduce its lifetime.
    There are also known methods implementing the use of plies pre-impregnated with resin, also called “prepregs”. The use of prepregs makes it possible to use more viscous resins than in the RTM process, and to have a matrix having improved tenacity. However, prepregs are generally in the form of two-dimensional fabrics which are ill-suited to the manufacture of complex three-dimensional parts.
    There is therefore a need for a method of manufacturing a part made of composite material having improved mechanical strength which does not have the aforementioned drawbacks.
    Subject and summary of the invention
    The main object of the present invention is therefore to overcome such drawbacks by proposing, according to a first aspect, a method for manufacturing a woven fibrous preform impregnated with a matrix precursor resin, said resin having a temperature in the raw state. glass transition Tg °, the process comprising:
    - the impregnation of wires or strands with the resin,
    - feeding a loom with impregnated threads or strands maintained at a temperature between Tg ° and Tg ° + 10 ° C.
    - the weaving of threads or strands in the loom in order to obtain the woven fibrous preform impregnated with resin.
    By “resin in the raw state” or “raw resin” is meant a resin which has not yet been cooked or exposed to a temperature at which its polymerization or cooking may have started. In other words, Tg ° corresponds to the glass transition temperature of a resin which has a substantially zero polymerization rate. A distinction is thus made between Tg ° and Tg “, which in turn corresponds to the glass transition temperature of the cured resin, that is to say the polymerization of which is completely or almost completely completed. In general, the raw glass transition temperature Tg ° is lower than the glass transition temperature of the polymerized resin Tg °°.
    The method of manufacturing a fibrous preform according to the invention makes it possible to obtain a woven preform impregnated with resin obtained for example by three-dimensional or multilayer weaving. The fibrous preform obtained can thus constitute the fibrous reinforcement of a piece of composite material of complex shape. In addition, the preform can be impregnated with more viscous resins than those typically used in an RTM process since no injection will be necessary to impregnate and densify the preform. Such resins are, for example, those known, which are used in prepregs. It is therefore now possible to benefit from the high tenacity of these resins in a room with a fibrous reinforcement obtained by three-dimensional weaving. A method of manufacturing such a part will be detailed below.
    By “three-dimensional weaving”, “3D weaving”, “multi-layer weaving” is understood here a mode of weaving by which at least some of the warp threads bind weft threads on several weft layers. Such weaving can be carried out in a jacquard type loom, in a manner known per se.
    The glass transition temperature of the resin in the green state 10 may be the glass transition temperature measured by differential scanning calorimetry (DSC) on the resin in the green state.
    In general, the temperature at which the threads are kept to supply the loom will be chosen according to the type of resin used. More precisely, this temperature must not be lower than the Tg ° of the raw resin to prevent the latter from being too brittle and to avoid damaging the threads or strands when the latter pass through the loom. In addition, this temperature should not be higher than Tg ° + 10 ° C in order to avoid that the resin is too liquid and sticky, which would make the weaving of pre-impregnated threads or strands difficult to carry out in the loom. and would cause the latter to become dirty.
    In an exemplary embodiment, the wires or strands may be made of carbon or of silicon carbide.
    In an exemplary embodiment, the resin can be an epoxy thermosetting resin. For example, the resin used can be a commercial resin such as that sold under the reference “HexPIy® 8552” by the company Hexcel, or else the resin “CYCOM® 934” from the company CYTEC. The resin used can also be a resin from the bismaleimide family (MBI), or a thermoplastic resin.
    In an exemplary embodiment, the strands or strands impregnated with resin may be present in a refrigerated enclosure supplying the loom with strands or strands impregnated with resin. The wires or strands can be stored in the refrigerated enclosure, or can alternatively simply pass through it before being woven.
    The invention also relates, according to a second aspect, to a method of manufacturing a part made of composite material comprising a fibrous reinforcement densified by a matrix, the method comprising the following steps:
    manufacture of a woven fibrous preform impregnated with a matrix precursor resin by a process such as that described above,
    - placing the fiber preform in a cavity of a mold having the shape of the part to be manufactured,
    heating the fiber preform to a softening temperature of the resin so as to liquefy the resin,
    - elimination of the air present in the fibrous preform,
    - compacting the fiber preform in the mold,
    heat treatment of polymerization of the resin present in the porosity of the fibrous preform so as to obtain the part made of composite material, and
    - release of the composite material part.
    The elimination of the air present in the fibrous preform can be achieved by evacuating the mold cavity, or by creating a vacuum in a closed enclosure in which the mold is present. Preferably, the elimination of the air present in the fiber preform is carried out simultaneously or after the heating of the fiber preform to a softening temperature of the resin so as to allow better escape of the air bubbles from the preform. The softening temperature of the resin can be, in known manner, the temperature at which the viscosity of the resin reaches a minimum, or even the temperature allowing the evacuation of the air bubbles present in the preform. The compacting of the fibrous preform in the mold makes it possible to degrade any excess resin present in the preform, and can be accompanied by a phase of maintaining a compaction pressure on the mold and / or a reinjection excess resin in the mold to maintain a uniform pressure inside the mold cavity.
    By implementing such a process, the porosity of the preform is uniformly saturated with resin and the absence of residual porosity is ensured. Thus, the polymerization or curing of the resin can be carried out uniformly throughout the impregnated preform, reducing the presence of internal stresses in the final part. The method according to the invention thus makes it possible to produce parts of composite material comprising a fibrous reinforcement obtained for example by three-dimensional weaving, and a matrix obtained from resins with higher tenacity and more viscous than those used in the RTM processes, this which was not possible before.
    In an exemplary embodiment, the manufactured part can be a fan blade or an aeronautical turbomachine fan casing.
    In an exemplary embodiment, the step of compacting the fibrous preform in the mold may include reinjecting into the mold a surplus of resin which has disgorged from the preform so as to maintain a uniform pressure inside the cavity of the mold.
    The invention finally relates, according to a third aspect, an installation for the manufacture of a woven fibrous preform impregnated with a matrix precursor resin, comprising: a weaving loom, an enclosure in which son or strands impregnated with resin, the enclosure being configured to supply the loom with threads or strands. According to the invention, the temperature inside the enclosure is between the glass transition temperature Tg ° of the resin in the raw state and Tg ° + 10 ° C.
    In an exemplary embodiment, the loom can be in the enclosure.
    Brief description of the drawings
    Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment thereof devoid of any limiting character. In the figures:
    FIG. 1 is a very schematic view of an example of an installation for implementing a process for manufacturing a woven fibrous preform impregnated with resin according to the invention,
    FIGS. 2A to 2D illustrate different stages of an example of a method of manufacturing a part made of composite material according to the invention, and
    - Figures 3A to 3C illustrate different stages of a variant method of manufacturing a part made of composite material according to the invention.
    Detailed description of the invention
    FIG. 1 very schematically shows an installation 1 making it possible to produce a fiber preform 10 impregnated with resin. The installation 1 comprises a weaving loom 20, for example of the jacquard type, and an enclosure 30 located upstream of the weaving loom (in the direction of conveying the weaving threads towards the weaving loom). Rollers 40 of son or strands 41 pre-impregnated with resin are stored inside the enclosure 30. The enclosure 30 comprises an opening 31 allowing the threads or strands of the rollers 40 to feed the loom 20. According to in the invention, the temperature inside the enclosure 30 is between the glass transition temperature Tg ° of the resin in the raw state and Tg ° + 10 ° C so that the wires or strands 41 which feed the loom 20 are at the temperature of the enclosure 30.
    In a variant not illustrated, the installation may include the loom 20, the rollers 40, and an enclosure cooled to a temperature between Tg ° and Tg ° + 10 ° C in which the loom 20 and the rollers 40.
    Still in a variant not illustrated, the threads or strands 41 can be dry on the rollers 40, and pass through a resin bath when they are conveyed to the loom so as to impregnate them with resin before their weaving. In this case, care should be taken to ensure that the impregnated wires or strands are at the correct temperature before being woven.
    The wires or strands 41 can be made of carbon, ceramic such as silicon carbide SiC, glass or even aramid. The resin can be chosen from epoxy resins, and optionally include additives making it possible to increase its toughness.
    To obtain a woven fibrous preform impregnated with resin, the pre-impregnated threads or strands 41 coming from the rollers 40 stored in the enclosure 30 are woven using the loom 20. The temperature at which said threads are maintained or strands 41 makes their weaving possible without fouling of the loom 20, since the resin is neither too brittle, nor too liquid or sticky. As indicated above, the weaving can be a three-dimensional weaving, but also multilayer or two-dimensional. The three-dimensional weaving can, in the example illustrated, be an “interlock” weaving weave, known per se. Other types of known multilayer weaving can be used, such as in particular those described in document WO 2006/136755.
    An example of a method of manufacturing a part made of composite material according to the invention will now be described in connection with FIGS. 2A to 2D.
    After having obtained a woven fiber preform 10 impregnated with resin as described above, the preform 10 is cut out and the threads leaving the layers are cut, then the preform 10 is positioned in a mold 50. The mold 50 illustrated diagrammatically in the figures comprises a support part 51 and a countermold 52, which define between them a hollow cavity 43 in which the preform 10 is placed. The cavity 53 has a shape and dimensions corresponding to the part to be manufactured. The support part 51 here comprises seals 54 which seal the mold 50 when it is closed. In the example illustrated, the mold 50 also includes a vent 55.
    The mold 50 can then be gradually closed, as illustrated in FIG. 2B. Before, after or during the closing of the mold 50, the preform 10 is heated to a softening temperature of the resin. When the mold 50 is closed in a leaktight manner and the resin present in the preform 10 is softened or liquefied, the air present in the cavity 53 can then be eliminated by creating a vacuum. The air is here evacuated from the cavity 53 by the vent 55. In this way, a preform 10 impregnated with resin in all its internal porosity and free of air bubbles is thus obtained.
    Then, a compaction pressure can be applied to the mold 50 in order to shape the preform and degrade the excess resin present in the preform, as illustrated in FIG. 2C. This surplus can be evacuated through the vent 55 by means not shown. In addition, it is possible to maintain a homogeneous pressure inside the cavity 53 by reinjecting part of the resin which was removed during the compaction.
    Finally, the mold 50 is heated, preferably uniformly, in order to initiate the polymerization (baking) of the resin present in the preform 10 and to densify the preform 10 (FIG. 2D). There is thus obtained after baking, the piece of composite material which can then be removed from the mold and on which it is possible to produce finishes.
    Another example of implementation of a method according to the invention is illustrated in FIGS. 3A to 3C.
    In this example, the mold 50 is placed in an airtight enclosure 60 and provided with a vent 61. Unlike the example illustrated in FIGS. 2A to 2D, the elimination of the air present in the impregnated preform 10 is produced by creating a vacuum in the enclosure 60 (FIG. 3A), and no longer directly inside the closed mold 50. In this way, the mold 50 can be closed after the step of eliminating the air present in the preform 10. As before, the mold is then closed and a compaction pressure is applied to the mold 50 (FIG. 3B) to shape the preform and drain the excess resin. Finally, the mold 50 is heated in order to polymerize the resin, densify the preform 10 and obtain the final part (FIG. 3C). The part can then be removed from the mold.
    The method of manufacturing a part made of composite material according to the invention has been illustrated using a mold comprising a support part and a counter-mold. It will be noted that, in a variant, other known means can be used to densify the preform, for example an assembly with a vacuum cover placed in an autoclave.
    In this presentation, the expression "between ... and ..." should be understood as including the limits.
    Example
    It is sought to manufacture an aeronautical turbomachine fan blade from an organic matrix composite material by a method according to the invention. The following steps are carried out successively:
    - carbon fiber strands are impregnated with a resin sold under the reference HexPIy® 8552 from the company Hexcel, the glass transition temperature Tg ° of this resin in the raw state given by the manufacturer and obtained by DSC is l '' order of -4 ° C (-3.95 ° C),
    the strands are placed in the form of a roll in a cabinet refrigerated at 0 ° C., the cabinet comprising openings making it possible to feed a loom with said strands,
    the strands maintained at 0 ° C. are woven in the loom by three-dimensional weaving in order to obtain a fibrous preform of woven blade impregnated with resin,
    - the woven preform is optionally cut using scissors,
    the preform is placed in the cavity of a mold having the shape of the blade to be manufactured,
    - the mold is heated to a temperature of 100 ° C in order to soften the resin,
    - the mold is closed and a vacuum is created inside the cavity in order to evacuate the air present in the preform,
    - a compaction pressure is applied to the mold to shape the preform and ensure a uniform pressure in the mold cavity, if necessary, resin is injected which would have disgorged from the preform during this step,
    - the mold is heated to 110 ° C for 150 minutes after a ramp of gradual rise in temperature in order to polymerize the resin,
    - the dawn thus obtained is demoulded, and
    - possibly finishing operations.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. A method of manufacturing a woven fibrous preform (10) impregnated with a matrix precursor resin, said resin having in the raw state a glass transition temperature Tg °, the method comprising:
    - the impregnation of wires or strands (41) with the resin,
    - feeding a weaving loom (20) with the impregnated threads or strands maintained at a temperature between Tg ° and Tg ° + 10 ° C, and
    - the weaving of threads or strands in the loom in order to obtain the woven fibrous preform impregnated with resin.
    [2" id="c-fr-0002]
    2. The method of claim 1, wherein the son or strands (41) are carbon or silicon carbide.
    [3" id="c-fr-0003]
    3. Method according to any one of claims 1 and 2, wherein the resin is an epoxy thermosetting resin.
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 3, in which the wires or strands (41) impregnated with resin are present in a refrigerated enclosure (30) supplying the loom (20) with wires or strands impregnated with resin. .
    [5" id="c-fr-0005]
    5. Method for manufacturing a part made of composite material comprising a fibrous reinforcement densified by a matrix, the method comprising the following steps:
    manufacture of a woven fibrous preform (10) impregnated with a matrix precursor resin by a process according to any one of Claims 1 to 4,
    - placement of the fiber preform in a cavity (54) of a mold (50) having the shape of the part to be manufactured,
    heating the fiber preform to a softening temperature of the resin so as to liquefy the resin,
    - elimination of the air present in the fibrous preform,
    - compacting the fiber preform in the mold,
    heat treatment of polymerization of the resin present in the porosity of the fibrous preform so as to obtain the part made of composite material, and
    - release of the composite material part.
    [6" id="c-fr-0006]
    6. The method of claim 5, wherein the manufactured part is a fan blade or a fan casing of an aeronautical turbomachine.
    [7" id="c-fr-0007]
    7. Method according to any one of claims 5 and 6, wherein the step of compacting the fibrous preform in the mold comprises reinjection into the mold of a surplus of resin having disgorged from the preform so as to maintain a uniform pressure inside the mold cavity.
    [8" id="c-fr-0008]
    8. Installation (1) for the manufacture of a woven fibrous preform (10) impregnated with a matrix precursor resin, comprising: a loom (20), an enclosure (30) in which threads or strands are stored (41) impregnated with resin, the enclosure being configured to supply the loom with threads or strands, characterized in that the temperature inside the enclosure is between the glass transition temperature Tg ° of the resin raw and Tg ° + 10 ° C.
    [9" id="c-fr-0009]
    9. Installation according to claim 8, wherein the loom (20) is in the enclosure (30).
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    同族专利:
    公开号 | 公开日
    FR3059266B1|2019-01-25|
    US11052573B2|2021-07-06|
    WO2018100263A1|2018-06-07|
    EP3548239B1|2020-12-30|
    CN110035876A|2019-07-19|
    US20200376716A1|2020-12-03|
    EP3548239A1|2019-10-09|
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    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-01| PLSC| Publication of the preliminary search report|Effective date: 20180601 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661642A|FR3059266B1|2016-11-29|2016-11-29|METHOD FOR MANUFACTURING A WOVEN FIBROUS PREFORM AND A COMPOSITE MATERIAL PART|
    FR1661642|2016-11-29|FR1661642A| FR3059266B1|2016-11-29|2016-11-29|METHOD FOR MANUFACTURING A WOVEN FIBROUS PREFORM AND A COMPOSITE MATERIAL PART|
    PCT/FR2017/053163| WO2018100263A1|2016-11-29|2017-11-20|Method for manufacturing a woven fibrous preform and a composite material part|
    EP17812002.8A| EP3548239B1|2016-11-29|2017-11-20|Method for manufacturing a woven fibrous preform and a composite material part|
    US16/464,546| US11052573B2|2016-11-29|2017-11-20|Method of fabricating both a woven fiber preform and a composite material part|
    CN201780073583.2A| CN110035876A|2016-11-29|2017-11-20|A method of manufacture braided fiber prefabricated component and composite material component|
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