• 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 manufacturing a turbomachine blade from a preform (10) of polymerized composite material in a mold comprising a lower part (16) and an upper part (22), comprising at least one step closure during which the upper part (22) of said mold (18) is brought onto the lower part (16) of the mold (18) containing the preform (10), characterized in that it comprises, prior to said step closure, at least one insertion sub-step during which is inserted into a lower portion (21) of the preform (10) a first end (28) of a member (30) of immobilization in one direction substantially transverse, and a positioning sub-step during which there is a second end (32) opposite said element (30) in a complementary receiving cavity (34) opening into the lower part (16) of the mold (18) .
    公开号:FR3026980A1
    申请号:FR1459739
    申请日:2014-10-10
    公开日:2016-04-15
    发明作者:Nicolas Ashtari；Marc-Emmanuel Techer
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The field of the present invention is that of the manufacture of gas turbine engines, such as turbomachines, and in particular those intended for the propulsion of aircraft. The present invention more particularly relates to a method of manufacturing a turbomachine blade of composite material, a preform for forming the blade of the turbomachine, and a mold for carrying out such a method. A turbomachine blade typically has a foot and a blade, the foot having oblique lateral faces connected to the blade and intended to form bearing surfaces in a mounting cell of a rotor disc. The dawn is generally made of lightweight materials in order to participate in the lightening of the turbomachine and to limit the inertia of the rotor of which it is part.
    [0002] A turbine engine blade is also subjected to particularly important stresses at the level of his foot, particularly at the bearing surfaces. Indeed, the forces exerted on the air flow by the blade, in the radially outer zone thereof, creates high stresses at its attachment zone, that is to say in the foot of the blade. 'dawn. This leads to using a material both light and resistant for the manufacture of dawn. A known solution to these constraints is to use a composite material. It is thus known to make a blade using a preform formed by weaving fibers, said fibers being compacted and embedded in a thermosetting resin matrix. The fibers thus provide the mechanical reinforcement function, the resin matrix making it possible to ensure the holding of the blade. EP-A1-1,526,285, in the name of the Applicant, discloses a method of manufacturing a preform by three-dimensional weaving of fibers, particularly carbon fibers. The preform thus obtained comprises a foot portion and a blade portion, connected by oblique lateral faces intended to form bearing surfaces of the foot in a mounting cell of a rotor disc. As described in EP-A1-1.777.063, also in the name of the Applicant, the preform is then disposed in a mold whose footprint comprises a foot zone and a blade zone, which are connected to the mold. one to the other by oblique lateral faces corresponding to the aforementioned lateral faces of the preform. The loosening of the fibers after weaving of the preform generates a swelling thereof, also known as the expansion phenomenon. The preform then has dimensions greater than the dimensions of the part to be produced. The preform is first compacted into a mold having a lower portion and an upper portion. To do this, the preform is disposed in the lower part of the mold, then the mold is closed by bringing the upper part of the mold to the lower part, transversely to the longitudinal axis of the blade, and axially the foot of the preform using a movable part of the mold which is interposed between the lower and upper parts. The role of this mobile part is to force the fibers of the foot of the preform to press against the oblique faces of the mold. Then a partial vacuum is made in the mold and a thermosetting resin is injected into the mold so as to impregnate the entire preform.
    [0003] The preform and the resin are then heated to polymerize and thus harden the resin. The fibers are then held in position by the resin matrix and the assembly forms a blade which is both light and rigid. The plating of the fibers of the preform against the oblique lateral faces of the mold makes it possible to limit the hollows at its zones intended to form the bearing surfaces of the foot in a mounting cell of a rotor disc.
    [0004] The existence of numerous depressions indeed generates, after injection of the resin, clusters or pockets of resin which, alone, have low mechanical strengths. The bearing surfaces being areas subject to high stresses, it is necessary to limit the appearance of such clusters or pockets of resin, which is obtained by biasing the foot of the preform with the aid of the moving part. of the mold. However, it has been found that another source of defects is the positioning of the fabric preform in the lower part of the mold.
    [0005] Indeed, the positioning of this tissue preform in the injection mold is delicate but essential. However, the closure of the upper part of the mold is likely to apply a force on the preform which may tend to move in the mold and to move in an incorrect position. Therefore, the preform may locally no longer be pressed against the walls of the mold, and therefore the surface of the blade may have, after injection of the resin, clusters or pockets of resin corresponding to areas not having been occupied by weaving.
    [0006] The mechanical strength of these zones is less than that normally required for such a blade, and for this reason the presence of such clusters or pockets of resin must absolutely be avoided.
    [0007] In fact, an inadequate positioning of the fabric of the preform can only be observed after injection and demolding of the part. No repair procedure is possible and the part must be scrapped.
    [0008] The invention overcomes this disadvantage by providing a manufacturing method to ensure the position of the preform in the mold. Thus, the invention proposes a method for manufacturing a turbomachine blade of composite material comprising: a first step of producing a preform of axial general orientation, by three-dimensional weaving of threads, said preform comprising a blade root portion and blade blade portion; - a second step of placing the preform in a lower portion of a mold, a footprint of which is substantially complementary to lower portions of the foot portion; vane blade and blade blade portion of the preform; - a third mold closing step of providing an upper portion of said mold, a footprint of which is complementary to upper portions of the blade root portion and of the vane blade part of the preform, on the lower part of the mold containing the preform, - a fourth step of compacting the preform in said mold, and - a fifth step of injecting The resin is vacuum molded to impregnate the compacted preform and form a rigid blade after polymerization of the resin.
    [0009] According to the invention, this method is characterized in that it comprises, prior to the third step, at least one insertion sub-step during which the first part of the preform is inserted into a first sub-step. end of an immobilizing element in a substantially transverse direction, and a positioning sub-step during which there is a second opposite end of said element in a complementary receiving cavity opening into the lower part of the mold.
    [0010] According to other features of the method: the method comprises, after the fifth step, a sub-step of removing the second end of the element; the insertion sub-step intervenes before the second step and the positioning sub-step occurs during the second step, alternatively, the positioning sub-step occurs during the second step and the insertion sub-step occurs during the second step after the second step; positioning sub-step; during the insertion sub-step, the immobilizing element is inserted into an area of the lower part of the blade root intended to form part of a drop subsequently removed, in the course of a sixth finishing step, the polymerized raw preform is demolded and then cut to separate from the falls, so as to obtain the final dawn, the sub-step of deletion being carried out concomitantly at said cut.
    [0011] The invention also proposes an immobilization element intended to cooperate on the one hand with a preform of axial general orientation, obtained by three-dimensional weaving of composite material yarns, of a turbomachine blade, and on the other hand with an impregnating mold of said preform. According to the invention, this element comprises a first end capable of being inserted into the preform and an opposite second end 10 able to project out of the preform and to cooperate with the mold. According to other characteristics of the immobilizing element: the first end is configured in peak or in point, the second end is shaped as a pin capable of cooperating with a cavity of complementary shape of the mold.
    [0012] The invention also proposes an impregnating mold for the manufacture of a turbomachine blade of composite material, comprising a lower part of a mold whose imprint is substantially complementary to a lower part of a blade preform, and an upper part of which an impression is substantially complementary to an upper part of the blade preform, said upper part being able to be attached to said lower part. This mold is characterized in that the lower portion has at least one cavity opening into the interior of the cavity, which is adapted to receive a fixed immobilization element of the blade preform.
    [0013] According to another characteristic of the mold, the cavity opens into a part of the cavity of the lower part of the mold which does not delimit a functional surface of the final blade.
    [0014] The invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the following description given by way of nonlimiting example and with reference to the accompanying drawings, in which: - Figure 1 is a schematic view of a preform implemented in the context of the method according to the invention; FIG. 2 is a diagrammatic cross-sectional view of the third step of closing a mold of a molding process according to a prior art; FIG. 3 is a schematic sectional view representative of the insertion sub-step according to a first embodiment of a manufacturing method according to the invention; FIG. 4 is a diagrammatic sectional view representative of the positioning sub-step according to the first embodiment of the manufacturing method; FIG. 5 is a diagrammatic sectional view representative of the positioning sub-step according to a second embodiment of a manufacturing method according to the invention; FIG. 6 is a schematic sectional view representative of the insertion sub-step according to the second embodiment of the manufacturing method according to the invention; - Figure 7 is a schematic sectional view representative of the third step of closing the mold according to the method of the invention.
    [0015] In the following description, like reference numerals refer to like parts or having similar functions. In known manner, a method of manufacturing a turbomachine blade of composite material comprises a first step in which is made, by weaving in three dimensions of son (not shown), a preform 10, as shown in FIG. 1. Such a preform 10 has an axial general orientation, corresponding to the horizontal direction of the figures.
    [0016] The preform 10 is made by one-piece weave, generally made of carbon fiber, and essentially comprises a blade root portion 12, intended to ensure the fixing of the finished blade to a disk of turbomachine rotor, and a blade blade portion 14 for cooperating with a flow of air or gas within the turbomachine. In a second step of such a process, the preform 10 is placed in a lower part 16 of a mold 18 such as that shown in FIG. imprint 20 which is substantially complementary to a lower portion 21 of the preform, that is to say of the lower portions of the blade root portion 12 and the blade blade portion 14 of the preform 10. The mold 18 has an upper portion 22 which is attached to the lower portion 16 during a third step of closing the mold 18. This upper portion 22 has a cavity 24 which is complementary to an upper portion 23 of the preform 10, that is to say, upper portions of the blade root portion 12 and the blade blade portion 14 of the preform 10. The closure of the mold 18 makes it possible to define a complete cavity, consisting of imprint 20 and imprint 24, which allows the injection of resin into the preform 10. Then the method comprises a fourth step of compacting the preform 10 in said mold 18. During this step, as illustrated in FIG. 2, a force is generally exerted on a end 26 of the foot 12 of the preform, so as to compact the fibers in contact with the walls of the imprints 20 and 24, as indicated by the arrows of Figure 2. Then, during a fifth injection step, vacuum injected into the mold 18 a resin to impregnate the compacted preform 10, which allows to form a rigid blade after polymerization of the resin. Finally, during a sixth finishing step, the polymerized raw preform 10 is demolded and then cut to separate from the falls, in order to obtain the final dawn. In particular, significant drops are arranged at the free end 26 of the foot 12. It has been found that correct positioning of the tissue preform in the cavity 20 of the lower part 16 of the mold 18 is an essential condition of obtaining a finished blade having optimum strength characteristics. Indeed, incorrect positioning of the fabric preform in the lower part of the mold 18 may cause the preform 10 to be no longer pressed against the walls of the mold 18, and thus the surface of the blade may have, after injection of the resin, clusters or resin pockets corresponding to areas not occupied by the weaving.
    [0017] However, incorrect positioning does not necessarily result from an incorrect disposition of the preform 10 in the lower part 16 of the mold 18 by the operator, but can occur when the mold 18 is closed. when the upper portion 22 of the mold 18 is folded over the lower portion 16 that the preform 10 is most likely to move. The invention overcomes this disadvantage by providing a manufacturing method for immobilizing the preform 18 in the mold 10 during its closure. For this purpose, the invention proposes a manufacturing method of the type described above, characterized in that it comprises, prior to the third step, at least one insertion sub-step during which is inserted in the part lower 21 of the preform 10 a first end 28 of an immobilizing element 30 in a substantially transverse direction, and a positioning sub-step during which there is disposed an opposite second end 32 of said element 30 in a cavity 34 receiving element opening into the lower part 16 of the mold 18. For this purpose, an immobilizing element 30 is used which, as illustrated in FIGS. 3 to 6, has a first end 28 capable of being inserted into the weave. of the preform 10 and an opposite second end, which is able to protrude out of the preform 10 as shown in FIGS. 3, 4 and 7, to cooperate with the mold c as shown in Figure 7.
    [0018] The immobilizing element 30 thus makes it possible to axially immobilize the preform 10, which prevents it from slipping into the cavity 20 of the lower part 6 of the mold 18 when the upper part 22 of the mold 18 is folded over the lower part 16, and also its sliding relative to said upper part 22.
    [0019] Advantageously, to allow the insertion of the first end 28 of the immobilizing element into the weave of the preform, this first end 28 is configured in peak or in point. The second end 32 is shaped as a pin, for example cylindrical, which is adapted to cooperate with the cavity 34 of complementary shape formed in the lower part 16 of the mold 10 and which opens into the cavity 20 of said lower part 16. L immobilizing element 30 can be interposed in two different ways between the preform 10 and the lower part 126 of the mold. According to a first embodiment of the method, the insertion sub-step intervenes before the second step and the positioning sub-step occurs during the second step.
    [0020] Thus, as shown in FIG. 3, the first end 28 of the immobilizing element 30 is firstly inserted into the preform 10, as shown in FIG. 3, and then the preform 10 provided with the element is placed. immobilizing in the cavity 20 of the lower part 16 of the mold 18, so that the second end 32 of the immobilizing element enters the cavity 34 of the mold 18. Then the mold 18 is closed as shown in FIG. FIG. 7 According to a second embodiment of the method, the positioning sub-step occurs during the second step and the insertion sub-step takes place during the second step after the sub-step. positioning. Thus, as shown in FIG. 5, the second end 32 of the immobilizing element 30 is firstly placed in the cavity 34 of the cavity 20 of the lower part 16 of the mold 18, as shown in FIG. 5, then the preform 10 is placed on the first end 28 of the immobilizing element 30, as shown in FIG. 6, so that the first end enters the weave of the preform 10. Then the mold is closed again 18, as shown in FIG. 7. In this variant of the method, it will be noted that it is desirable for the second end 32 of the immobilizing element 30 to be stably received in the cavity 34, in order to guarantee the transversality, here in the vertical direction, of the immobilizing element, to facilitate the penetration of its first end 28 into the immobilizing element. Furthermore, it will be understood that the immobilizing element 30 remains interposed between the preform 10 and the lower part 16 of the mold 20 throughout the duration of the fifth step, and consequently during and after the polymerization of the mold. resin. As a result, during the demolding of the blade, the first part of the immobilizing element remains trapped in the weave of the preform.
    [0021] Also, after the fifth step, the method comprises a sub-step of removing the second end 32 of the element 30. In a conventional manner, the mold 18 defines in the final blade a portion 36 delimited by the dashed lines of Figure 7, which is not functional and which is able to be part of a fall which is intended to be cut off from the dawn emerging from the mold 18 to constitute the final dawn.
    [0022] Preferably, the cavity 34 opens into a portion of the cavity 20 of the lower part 16 of the mold which does not delimit a functional surface of the final blade, and which therefore corresponds to this portion 36.
    [0023] Part 36 corresponds to a part intended to be cut during the finishing of the cured raw blade, and therefore does not form part of the foot portion 12 intended to ensure the attachment of the blade to a rotor disk. , nor part of the blade portion intended to be subjected to a gas flow in the turbomachine. The immobilizing element 30 is therefore able to be removed at the same time as the part 36 during the cutting of the blade. Thus, it will be understood that, regardless of the embodiment of the method, during the insertion sub-step, the immobilizing element 30 is inserted into an area of the lower part of the foot. dawn intended to be part of a fall later removed. Then, during a sixth finishing step, the polymerized raw preform is demolded and then cut to separate falls, and in particular the portion 36 to obtain the final blade. The sub-step of suppressing the second end 32 of the element 30 is thus advantageously carried out concomitantly with said blank, by eliminating all the prisoner element of the portion 36 of the polymerized preform 10.
    [0024] The invention therefore proposes a particularly simple and advantageous method which makes it possible to prevent the movements of a woven preform 10 in a mold 18 during a molding process of a blade by resin injection, and consequently to limit defects that may lead to dawn scrapping. Advantageously, it is therefore avoided losing, by disposal, molded blades whose cost is not negligible.
    [0025] Considering the high duration of polymerization of such a blade, the use of this method, by drastically reducing the number of blades discarded, significantly increases the production of blade blades. turbine engine.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of manufacturing a turbomachine blade of composite material comprising: - a first step of producing a preform (10) of axial general orientation, by three-dimensional weaving of threads, said preform (10) comprising a part ( 12) and a blade blade portion (14); - a second step of placing the preform (10) in a lower portion (16) of a mold (18), one of which imprint (20) is substantially complementary to lower portions of the blade root portion (12) and blade blade portion (14) of the preform (10), - a third mold closing step (18). ) comprising providing an upper portion (22) of said mold (18), an indentation (24) of which is complementary to upper portions of the blade root portion (12) and the blade blade portion (14) of the preform (10), on the lower part (16) of the mold (18) containing the preform (10), - a fourth step of compaction of the a preform (10) in said mold (18), and - a fifth vacuum injection step in the mold (18) of a resin for impregnating the compacted preform (10) and forming a rigid blade after polymerization resin, characterized in that it comprises, prior to the third step, at least one insertion sub-step during which is inserted into a lower portion (21) of the preform a first end (28) of an immobilizing element (30) in a substantially transverse direction, and a positioning sub-step during which an opposite second end (32) of said element (30) is disposed in a complementary receiving cavity (34) opening in the lower part (16) of the mold (18). 3026980 16
    [0002]
    2. Manufacturing process according to the preceding claim, characterized in that it comprises, after the fifth step, a substep of removing the second end (32) of the element (30).
    [0003]
    3. Manufacturing method according to one of claims 1 to 2, characterized in that the insertion sub-step occurs before the second step and in that the positioning sub-step occurs during the second step. .
    [0004]
    4. Manufacturing process according to one of claims 1 to 3, characterized in that the positioning sub-step occurs during the second step and in that the insertion sub-step occurs during the second step. step after the positioning sub-step.
    [0005]
    5. Manufacturing process according to one of the preceding claims, characterized in that: during the insertion sub-step, the immobilization element (30) is inserted in a zone (36) of the part lower blade root (21) (21) intended to form part of a drop subsequently removed; during a sixth finishing step, the polymerized raw preform (10) is demolded and then cut to separate the falls, in order to obtain the final blade, the sub-step of deletion being carried out concomitantly with said cut.
    [0006]
    6. Element (30) of immobilization, intended to cooperate on the one hand with a preform (10) of axial general orientation, obtained by weaving in three dimensions of son composite materials, a turbine engine blade, and on the other hand with a mold (18) for impregnating said preform (10), characterized in that it comprises a first end (28) capable of being inserted into the preform (10) and a second end (32) opposed able to protrude out of the preform (10) and to cooperate with the mold (18).
    [0007]
    7. element (30) of immobilization according to claim 6, characterized in that the first end (28) is configured in peak or peak. 3026980 17
    [0008]
    8. element (30) of immobilization according to claim 6 or 7, characterized in that the second end (32) is shaped as a pin adapted to cooperate with a cavity (34) of complementary shape of the mold (18).
    [0009]
    9. Impregnation mold (18) for the manufacture of a turbomachine blade of composite material, comprising a lower portion (16) of mold, a cavity (20) is substantially complementary to a lower portion (21) of a blade preform (10), and an upper part (22), an impression of which is substantially complementary to an upper part (23) of the blade preform, said upper part (22) being suitable for being attached on said lower part (16), characterized in that the lower part (16) has at least one cavity (34) opening into the cavity (20), which is adapted to receive an immobilizing element ( 30) integral with the blade preform (10).
    [0010]
    10. Mold (18) for impregnation according to the preceding claim, characterized in that the cavity (34) opens into a portion of the cavity (20) of the lower portion (16) of the mold (18) which delimits not a functional surface of the final dawn. 20
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    公开号 | 公开日
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    引用文献:
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    法律状态:
    2015-10-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-15| PLSC| Publication of the preliminary search report|Effective date: 20160415 |
    2016-10-11| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1459739A|FR3026980B1|2014-10-10|2014-10-10|METHOD FOR IMMOBILIZING A PREFORM IN A MOLD|FR1459739A| FR3026980B1|2014-10-10|2014-10-10|METHOD FOR IMMOBILIZING A PREFORM IN A MOLD|
    US14/880,006| US10987881B2|2014-10-10|2015-10-09|Method for immobilising a preform in a mould|
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