• 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 compaction assembly comprising a conformation mold (24) delimiting an upwardly open housing, able to receive a pre-cut woven preform (10a), and a compaction tool (128) vertically movable and forming, with the shaping mold (24), a compaction assembly of said preform previously placed in the housing. The compaction tool (128) has at least one foot portion (128A). The compaction tool includes at least three separate compaction blocks (1281-1287). Application to the manufacture of composite fan blades for a turbomachine.
    公开号:FR3024959A1
    申请号:FR1457909
    申请日:2014-08-21
    公开日:2016-02-26
    发明作者:Yann Marchal；Jeremy Engel；Matthieu Gimat
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present disclosure relates to a method of manufacturing a composite turbomachine blade and a compacting assembly used in this process. The composite blade may be of the type comprising a three-dimensional woven wire or fiber preform and a binder maintaining the relative disposition between the preform wires. Said preform may be formed of warp yarns and weft yarns, the warp yarn direction forming the longitudinal direction of the preform. In particular, the present invention relates to the manufacture of a fan blade for a turbomachine, in particular a turbojet engine. However, it is also contemplated in the context of the present invention to manufacture a blade for a low pressure compressor where the temperatures reached in operation are compatible with the thermomechanical resistance of this type of blade. It is also possible to implement the present invention for non-ducted fan blades (or "open rotor") or blades with integrated platform. BACKGROUND Conventionally, the blades of blowers made of composite material, in particular of carbon fibers, are made from a stack of unidirectional preimpregnated folds which are placed in a mold by orienting the successive folds differently. prior to compaction and autoclave polymerization. This very delicate technique requires manual stacking operations, which is time consuming and costly. It has also been proposed to prepare dry fiber woven preforms which are then sewn together prior to resin impregnation by injection into a closed mold. An alternative has been to make a single woven preform that is mounted with one or more solid inserts before injection. These solutions (US Pat. No. 5,672,417 and US Pat. No. 5,013,216), however, have the disadvantage of requiring the assembly of several parts and creating in these assembly areas, preferred sites of fragility, for example delamination, which is very harmful in terms of mechanical strength, especially for impact resistance. In order to overcome these drawbacks, document FR 2 861 143 proposes to produce a preform made of three-dimensionally woven fibers or yarns which can be used to form on its own, after any cutting and injection of the binder, the final piece forming all the parts of the turbomachine dawn, without resorting to the use of inserts or any other item reported. In particular, the manufacturing method shown in FR 2 892 339 is used, in which the woven preform then cut is shaped in a mold before injecting the binder and proceed to harden the latter. However, there are still a number of problems with how this formatting is done. GENERAL DISCLOSURE The purpose of this disclosure is to provide a compaction assembly that avoids the aforementioned disadvantages. In particular, this compacting assembly makes it possible to pre-compact the preform. The compacting assembly may be used for a preform obtained by three-dimensional weaving of yarns and intended to form a composite turbomachine blade, said preform comprising both the blade, the root of the blade and, between the blade and the foot, the stilt of dawn. This compacting assembly comprises a conformation mold delimiting an upwardly open housing capable of receiving a woven preform (which may have been cut beforehand), and a vertically movable compacting tool cooperating with the conformation mold to form a mold. compacting assembly for compacting said preform when it is placed in the housing. The compaction assembly defines a longitudinal direction and a vertical median plane parallel to the longitudinal direction. The compaction tool may comprise at least three separate compacting blocks, between which a central compaction block traversing said median plane and two lateral compaction blocks located at the lateral edges of said compaction tool, said compacting tools being adapted to descend one by one to the conformation mold independently, starting with the central compacting block. The compacting tool may be configured to descend toward the conformation mold.
    [0002] The present disclosure also relates to a method of manufacturing a composite turbomachine blade, using a compacting assembly. BRIEF DESCRIPTION OF THE DRAWINGS Other advantages and characteristics of the invention will emerge on reading the following description given by way of example and with reference to the appended drawings, in which: FIG. 1 is a general perspective view of a FIG. 2 illustrates a step of an exemplary manufacturing method, FIGS. 3 and 4 are cross-sectional views along directions III and IV of FIG. 2 showing the effect of compaction on the profile of two different portions of the preform, with a compaction assembly according to a first embodiment of the invention; FIG. 5 is a partial view of the preform of FIG. 1, showing in an enlarged manner the foot and the FIG. 6 is a sectional view similar to that of FIG. 4, with a compacting assembly according to a second embodiment of the invention, FIG. 7 is a perspective view of the tool. compaction FIG. 6 is a detailed description of the invention. DETAILED DESCRIPTION In the detailed description which follows, reference is made to the accompanying drawings showing examples of compaction assemblies or examples of the manufacturing process. The intention is that these examples are considered as merely illustrative, the scope of the invention not being limited to these examples. In an illustrative embodiment, the manufacturing method starts with a first step a) of making a three-dimensional preform by weaving, the woven preform comprising warp yarns 20a and weft yarns 20b. In these two groups of son, there are provided tracer son 22 visually identifiable from others and regularly located at least on the surface of the preform. The warp and weft yarns belong to the group consisting of carbon fibers, glass fibers, silica fibers, silicon carbide fibers, alumina fibers, aramid fibers and aromatic polyamide fibers. This woven preform in one piece is then cut according to a second step b) of the method. More exactly, this woven preform is cut out by cutting the contour from a predetermined three-dimensional abacus provided that after the deformation, the preform respects the geometry of the finished part. This cutting can be performed by water jet and / or by mechanical means (scissors, cutter, saw ....) and / or by laser cutting.
    [0003] This leads to a cut preform 10a as visible in Figure 1. We find the parts intended to form the blade 12 and the foot 14 of the blade, and the stilt 13 which is the parde transition between the blade 12 and the foot 14. In particular, the warp yarns 20a and weft yarns 20b used for three-dimensional weaving are carbon fibers (black) and glass fibers or Kevlar (white) form tracer yarns 22 located substantially at the surface of the preform, along the longitudinal main direction parallel to the warp yarns 20a and along the transverse direction parallel to the weft yarns 20b. In this way, the tracer son 22 appear white on the remainder of the preform which is black, and the tracer son 22 are therefore very visible. In addition, these tracer son are detectable by conventional non-destructive testing technologies (such as X-ray tomography or ultrasound) to verify the conformity of the final part. In particular, these tracer son 22 are present here at the surface 30 of the two faces (respectively intended to form the intrados wall 17 and the extrados wall 18) of the blade at predetermined locations in order to serve as a reference point for positioning for cutting and other processing steps of the preform as will be discussed below. In this step of cutting, it is intended to keep a series of tracer wires 22 located on the surface of the preform along at least one reference face 16, which in the illustrated case is the face intended for to form the leading edge. Then, a step c) is performed in which a predeformation of the cut preform 10a is performed. More specifically, during step c), said predeformation is carried out by placing the cut preform 10a in a shaping mold 24 (FIG. 2) having different parts delimiting between them a cavity or housing 26 intended to house the cut preform 10a and presenting markers serving as a reference for the positioning of at least some of the marking threads 22. Various systems for locating and positioning the cut preform 10a can be used, in particular a laser projector 27 (see FIG. 2) which projects a light beam at the ideal location of a tracer wire 22 so that it is then easy to move the corresponding tracer wire 22 accordingly to obtain the predetermined positioning. Alternatively or additionally, masks, taking again the contour and / or the position of all or part of the tracer son 22, can be arranged on the preform in order to control its good positioning. When the cut preform 10a is provided in the conformation mold 24, the cut preform 10a is placed in a configuration which deforms it applying a rotation (arrow 25a in FIG. 2) around an axis 0 ('parallel to its main direction, which has the effect of twisting the blade around this axis In some cases, it is also possible to provide that the shaping mold 24 has a movable portion 24a, sliding and intended to be positioned against the end free of the foot 14 of the preform in order to come to exert a constraint (arrow 25b in FIG. 2) realizing the desired deformation of this portion 14 of the preform, or avoiding certain types of deformation in this part while a deformation is exerted on other portions of the preform 10b It is to be understood that many different possibilities are possible for conforming the cut preform 10a by using the threads 22 The positioning strategy of the cut preform 10a in the shaping mold 24 is also related to the cutting or clipping profile made previously, depending on the reference surface (s) chosen, in particular among the foot, the head, the leading edge 16, the trailing edge 19 or any other predetermined zone. It is conceivable that the introduction of the cut preform 10a in the conformation mold 24 is sufficient to achieve all the necessary deformations to achieve the final desired shape. However, in some cases, this step c) can also be advantageously carried out in several sub-steps. A binder comprising a thermosetting resin is then injected into said injection mold in order to impregnate the entire preform and to maintain the relative disposition between the son of the preform; said injection mold is heated; and leaving the mold a composite molded piece having substantially the shape and dimensions of said blade. In a step d), which follows step c) and before carrying out the injection of the binder, a pre-compacting of at least a portion of the preformed preform 10b is carried out, comprising the foot and preferably the 20 foot 14 and the stilt 13, over the entire width of the predeformed preform 10b. This pre-compacting blocks certain fibers in a desired position, resulting in an intermediate geometry of the preform, which is even closer to the desired final shape. The compacting tool 28 used for this purpose, visible schematically and partially in FIG. 2, can advantageously be made by completing the shaping mold 24 with the necessary equipment. Indeed, the compaction tool 28 is movable (up and down) and must be able to be heated to a temperature of the order of 100 ° C.
    [0004] During this step d), it is the sizing products coating the son and which are used to facilitate the weaving, which allow the blocking of the relative position of the fibers of the pre-compacted portion. Subsequently, wetting of the pre-compacted preform 10c is carried out and drying is carried out in an oven, whereby a stiffened preform is provided. In fact, this stiffening will sufficiently freeze the conformation given during step c ) to the cut preform 10a 10a, become the preformed preform 10b, so that it can be placed later easily in the injection mold 24 without substantially changing its shape which corresponds to that of the aforementioned pre-deformation.
    [0005] If necessary, a tackifier may optionally be added inside the preform, for example a dilute resin, in particular of the epoxy type, the whole being capable, under the effect of the heat and the pressure exerted during the pre-compacting step d), the woven carbon fibers are bonded together to prevent the preformed preform 10b from undergoing any subsequent deformation, in particular during the injection step. The compaction tool 28 has a shape and dimensions that allow it to fit into the housing 26 of the shaping mold 24 to allow the woven preform to be compacted at an intermediate fiber volume level with respect to the fiber volume ratio. definitive of the final piece. For example, it is intended to produce a preform compacted with the compaction tool 28 having a fiber volume content of between 35% and 55%, so that the final part, after injection, has a fiber volume content of between 20% and 55%. 50% and 60%. Referring to Figures 3 and 4, showing a cross section of a predeformed preform and a compaction assembly according to one embodiment of the invention (conformation mold 24 and compacting tool 28). FIG. 3 is a cross-section at the foot 14, while FIG. 4 is a cross-section at the stilt 13. These figures show how the predeformation is applied to these different parts of the predeformed preform 10b (line dashed lines) and lead to the compacted preform 10c (solid line).
    [0006] For the foot 14 (Figure 3), the housing 26 of the shaping mold 24 has a rectangular section and the compaction tool 28 has a foot portion 28A whose rectangular section is complementary to that of the housing 26. For the 13 (Figure 4), the housing 26 of the conformation mold 24 has a section with a convex bottom 26a and flared sides 26b towards the opening of the housing 26. The compacting tool 28 portion 28B stag portion whose section comprises substantially vertical sides 28b and a bottom 28a, intended to come opposite the convex bottom of the shaping mold 24. This bottom 28 is concave with a profile having larger radii of curvature than the convex profile of the bottom of the housing 26 of the conformation mold 24. The compaction tool 28 according to this embodiment is monoblock so that during its movement, it descends (or rises) entirely in (or from) the housing. t 26 of the conformation mold 24, 10 thus compressing the preformed preform 10b. In order to avoid damaging the fibers of the preformed preform 10b, and in particular of pinching them, the surfaces of the conformation mold 24 and the compaction tool 28 facing towards the housing have no abrupt (or projecting) ridge but consist of of faces with angles softened by rounded or radiated connections forming fillets. In such a situation, when the compacting tool 28 goes down, considering the stag portion 28B compressing the stalk 13 of the preform (FIG. 4), it is firstly the lateral edges 16a and 19a of the preformed preform 10b, respectively to form the leading edge 16 and the trailing edge 19, which come into contact with the compaction tool 28 at the location of the side edges 28c of the bottom 28a. Next, the contact is progressively made with the entire surface of the stilt 13 turned facing the compaction tool 28, ending in the central zone (band) of this surface, passing through a median plane PM of the compacting set. This median plane PM, which is not necessarily a plane of symmetry for the compaction assembly and for the preform, is vertical, parallel to the axis 0 (oriented in the main direction of the preform, and 30 is located halfway between the lateral edges 26b of the housing 26 of the shaping mold 24 and between the lateral edges 28b of the compaction tool 28. This configuration sometimes entails certain disadvantages with respect to the pre-deformation of stilt 13: thus, in the case of FIGS. 4 and 5, the lateral edges 16a and 19a of the preformed preform 10b are on the one hand thinner in thickness and undergoing a greater flexion than the rest of the the stalks, fibers forming the preform undergo buckling, which may be detrimental to the good thermomechanical strength of the final blade.The areas of the cut preform 10a which undergo this undesirable buckling are shown in FIG. at the two locations Z1 and Z2 corresponding to the thin edges of the stilt 13 located near the blade 12. In order to avoid the aforementioned drawbacks, the compaction tool of the compacting assembly comprises at least a portion 10 of foot and in that said compacting tool comprises at least three separate compacting blocks, among which a central compaction block passing through said median plane and two lateral compacting blocks located at the lateral ends of said compacting tool, said compacting blocks being able to descend one by one in the direction of the shaping mold independently, starting with the central compaction block. In this way, the compaction tool can be formed of at least three parts, and these parts can be moved down at different times, starting with the central compaction block which goes down first so that the first contact between the compacting tool and the cut preform is made at the central zone of the surface of the stilt facing the compacting tool. In this way, thanks to the compacting unit of the invention, the lateral edges of the stilt of the preform are compacted last, which makes it possible to minimize or even avoid buckling fibers of these zones. thin in pre-compaction. Said stilt portion may comprise an odd number of 30 separate compacting blocks, so as to form a geometry with a central compaction block passing through said median plane and on either side of this central compaction block, a number identical to other compaction blocks. This solution also has the additional advantage of making it possible, in addition, to measure the level of pre-compaction exerted by each of these compacting blocks on the preform, which can be measured by the volume ratio of intermediate fibers. resulting from this precompaction. In some embodiments, said compacting blocks are adapted to descend one by one towards the conformation mold 5 in an order that compact the entire width of said preform starting with said central compacting block and then each compacting block adjacent to the one previously descended, and until the block of lateral compaction. In some embodiments, said compaction tool 10 has a single foot portion. In other embodiments, the compaction tool includes a leg portion 128A and a stag portion 128B, as illustrated in FIG. 7. In some embodiments, said compaction blocks are adapted to descend toward the shaping mold, beginning with the central compaction block, and then all compaction blocks on one side of the center plane. preferably one by one and step by step from the central compacting block to the second side compacting block. According to another alternative, said compacting blocks are able to descend towards the conformation mold symmetrically with respect to the median plane. In some embodiments, the entire compaction tool 128 is divided into at least three separate compaction blocks, including a central compaction block 1281 passing through the center plane PM 25 of the compaction tool 128, said compaction blocks being able to descend towards the shaping mold 24 independently, starting with the central compacting block 1281. In the example of Figures 6 and 7, the entire compaction tool 128 is divided into seven separate compaction blocks 1281, 1282, 1283, 1284, 1285, 1286, 1287, distributed around and on either side of the median plane PM. In this way, the downward movement of the entire compacting tool 128 (leg portion 128A and stub portion 128B) can be decomposed, beginning with the central compacting block 1281 passing through the midplane PM of the compacting tool 128 (downward arrow D1 and dashed line 1281 'in FIG. 6), then the two compacting blocks 1282 and 1283 located on either side of the central compacting block 1281 (arrows descending D2 and D3 and dotted lines 1282 'and 1283' in Fig. 6), and so on to the two side compacting blocks 1286 and 1287 at the lateral ends of the compacting tool 128. As is visible in Figure 7, optionally, the compaction tool 128 comprises at least one window 132 for displaying the position of at least one tracer wire when the preform is placed in the housing defined between the shaping mold 24 and the 10 c tool 28. This window 132 consists for example of a portion of the compaction tool 128 made of a transparent material, or preferably an opening through the entire thickness of the compaction tool 28.
    [0007] This window 132 may be disposed in a zone of the stilt portion 128B which is adjacent to the foot portion 128A, preferably at the central compacting block 1281. Such a window 132 makes it possible in particular to verify that the Tracer wires 22 visible through this window (e.g., span output tracer wire) are properly positioned and remain so during the compacting operation. In the example illustrated in FIGS. 6 and 7, the compacting tool 128 is divided into seven separate compacting blocks 1281, 1282, 1283, 1284, 1285, 1286, 1287.
    [0008] The compacting blocks 1281, 1282, 1283, 1284, 1285, 1286, 1287 can also be lowered to compact the preform 10b with different speeds and / or forces exerted by these compacting blocks on the preform which are different from each other. where precompaction levels or volume levels of intermediate fibers resulting from this pre-compaction which are different between compaction blocks 1281, 1282, 1283, 1284, 1285, 1286, 1287. In the illustrated examples, there are seven compaction blocks 1281, 1282, 1283, 1284, 1285, 1286, 1287, but in general, at least five, for example exactly five, can be provided.
    [0009] A method of manufacturing a composite turbomachine blade may comprise the following steps: a) a preform is made by three-dimensional weaving of wires 20a, 20b, 22, said preform comprising both the blade 12, the foot 14 of the blade and, between the blade 12 and the foot 14, the stilt of the blade 13, the son 20 5 comprising visually identifiable tracer son 22 arranged at least on the surface of the preform ; b) cutting said preform leaving intact a series of tracer son 22 located along a reference face 16 of the preform, whereby a cut preform 10a is provided adapted to take the shape and dimensions of the constituent parts dawn; c) preforming said cut preform 10a, whereby a predeformed preform 10b is provided; d) pre-compacting of said preformed preform 10b, whereby a pre-compacted preform 10c is provided; E) wetting the pre-compacted preform 10c and drying in an oven, whereby a stiffened preform is provided; f) providing an injection mold 24 in which is placed said stiffened preform; g) injecting into said injection mold a binder comprising a thermosetting resin in order to impregnate the entire rigidified preformed preform and to maintain the relative disposition between the wires 20a, 20b, 22 of the stiffened preform; h) heating said injection mold; and i) a composite molded piece having substantially the shape and dimensions of said blade is removed from the mold. During step c), said predeformation is carried out by placing the cut preform 10a in the housing 26 delimited by a shaping mold 24 and during step d) said pre-compaction of said preformed preform 10b is carried out using a tool compaction device 128 movable and cooperating with the conformation mold 24 to form a compacting assembly defining a longitudinal direction and a vertical median plane PM parallel to the longitudinal direction. Thus, preferably, during step d), the compacting tool 28 descends towards the shaping mold 24.
    [0010] According to a preferred embodiment, said compacting tool 128 is capable, during step d), of compacting at least the foot 12 of said preformed preform 10b, starting with the middle and progressively going as far as possible. at the edge of the preformed preform 5 10b. Thus, thanks to this advantageous arrangement, it avoids fiber buckling in the foot zone 12 and the staggering zone 13 of the preform during the compaction step. In this method, said compaction tool 128 is able, during step d), to descend towards the shaping mold 24 so that said compaction blocks descend one by one towards the shaping mold 24 in accordance with a This order compresses the entire width of said preform 10b beginning with its central portion passing through the median plane PM and then each portion adjacent to the preceding one, progressively moving away from the median plane PM. Said compaction tool 128 can be adapted, during step d), to descend towards the shaping mold 24 symmetrically with respect to said median plane PM. In the figures, there is shown the case of a foot 14 which remains rectilinear throughout the manufacturing process. It is understood that without departing from the scope of the present invention, it is possible to envisage the case of a foot which is twisted, or deformed according to any other action, when it is placed in the conformation mold 24. Moreover, according to a variant embodiment not shown, the compaction tool 128 covers not only the foot 14 and the stilt 13 of the blade, but also a portion of the blade 12 of the blade. Also, in the foregoing description, it has been mentioned that compaction tool 128 performs a precompaction step, i.e., step d). However, it is also possible to use this compaction tool 128 alternately as part of the injection mold 24 and use it only for steps f) and g). According to another variant, this same compaction tool 128 can be used both for step d) of pre-compaction and for steps f) and g). In this description, "understand / understand" is meant to specify the presence of named features, but does not exclude the presence or addition of one or more other features.
    [0011] The above description is given by way of example, and not limitation. With the disclosure above, the person skilled in the art could design variants that are within the scope of the invention. On the other hand, the various features of the embodiments or examples disclosed herein may be used alone or in different combinations with each other, and are not intended to be limited to the specific combinations described herein.
    权利要求:
    Claims (6)
    [0001]
    REVENDICATIONS1. Compaction assembly for a woven preform obtained by three-dimensional weaving of yarns (20) and intended to form a composite turbomachine blade, said preform comprising both the blade (12), the foot (14) of the blade and between the blade (12) and the foot (14), the stilt of the blade (13), the compacting assembly comprising a conformation mold (24) defining a housing (26) open upwards, suitable receiving a woven preform, and a compaction tool (28) vertically movable and cooperating with the conformation mold (24) to form a compaction assembly for compacting said preform (10b) when placed in the housing (26). ), wherein said compaction tool (28) has at least one foot portion (128A), said compaction assembly defining a longitudinal direction and a vertical midplane (PM) parallel to the longitudinal direction, the compacting tool (128) comprising at least three blocks of com separate plating (1281-1287), including a central compaction block (1281) passing through said median plane (PM) and two lateral compaction blocks (1286, 1287) at the lateral ends of said compaction tool (128), said compaction blocks being adapted to descend one by one to the conformation mold (24) independently, beginning with the central compaction block (1281).
    [0002]
    2. compaction unit according to claim 1, characterized in that said compaction blocks are adapted to descend one by one towards the shaping mold (24), starting with said central compaction block (1281) and then each block compacting adjacent to that previously descended to the side compacting block (1286, 1287) to compact an entire width of said preform (10b). 30
    [0003]
    3. compaction unit according to any one of claims 1 or 2, characterized in that the compaction tool (128) comprises at least one window (132) for viewing the position of at least one tracer wire (22). ) when the preform is placed in the housing (26) 3024 959 16
    [0004]
    4. A method of manufacturing a composite turbomachine blade, characterized in that it comprises the following steps: a) a preform is made by three-dimensional weaving of wires (20a, 20b, 22), said preform comprising the blade (12), the root (14) of the blade and, between the blade (12) and the foot (14), the stilt of the blade (13), the wires (20a, 20b, 22) comprising visually identifiable tracer leads (22) disposed at least on the surface of the preform; b) said preform is cut by leaving intact a series of tracer yarns (22) located along a reference face (16) of the preform, whereby a shaped preform (10a) is provided which can take the form and the dimensions of the constituent parts of the dawn; c) preforming said cut preform (10a), whereby a predeformed preform (10b) is provided; d) pre-compacting said preformed preform (10b) whereby a pre-compacted preform (10c) is provided; e) the pre-compacted preform (10c) is wetted and dried, whereby a stiffened preform is provided; f) providing an injection mold in which is placed said stiffened preform; 20 g) injecting into said injection mold a binder comprising a thermosetting resin in order to impregnate the entire rigidified preform and to maintain the relative disposition between the wires (20a, 20b, 22) of the stiffened preform; h) heating said injection mold; and i) a composite molded piece having substantially the shape and dimensions of said blade is removed from the mold, characterized in that during step c) said predeformation is carried out by placing the cut preform (10a) in the housing (26). ) delimited by a shaping mold (24), in that during step d) said pre-compaction of said predeformed preform (10b) is carried out by using a compaction tool (128) movable and cooperating with the mold of conformation (24), in that during step d), at least the foot portion (14) of the preform (10b) is pre-compacted, and in that the preform (10b) is precompacted in starting at the middle and progressively going to the edge of the preform (10b). 3024 959 17
    [0005]
    The method of claim 4, wherein said compacting tool (128) comprises at least three separate compacting blocks (1281-1287) and, in step d), the compacting block (128) is lowered to direction of the conformation mold (24) such that said compacting blocks descend one by one toward the conformation mold (24) in an order beginning with a central portion of the preform and then each portion adjacent to the preceding one, so to compact a whole width of the preform (10b).
    [0006]
    6. A process according to claims 4 or 5, wherein during steps c) and d) a compaction unit according to any one of claims 1 to 3 is used.
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    US20160288380A1|2016-10-06|
    US11072100B2|2021-07-27|
    JP2016538152A|2016-12-08|
    RU2659995C2|2018-07-04|
    BR112016007437A2|2017-08-01|
    JP6989582B2|2022-01-05|
    FR3024959B1|2016-09-09|
    CN105682904B|2017-12-22|
    JP2020055316A|2020-04-09|
    EP3052304A1|2016-08-10|
    WO2015049474A1|2015-04-09|
    CA2926170A1|2015-04-09|
    EP3052304B1|2017-08-23|
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    法律状态:
    2015-08-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-26| PLSC| Publication of the preliminary search report|Effective date: 20160226 |
    2016-08-04| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-15| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457909A|FR3024959B1|2014-08-21|2014-08-21|PROCESS AND ASSEMBLY FOR MANUFACTURING AUBE COMPOSITE|FR1457909A| FR3024959B1|2014-08-21|2014-08-21|PROCESS AND ASSEMBLY FOR MANUFACTURING AUBE COMPOSITE|
    PCT/FR2014/052512| WO2015049474A1|2013-10-04|2014-10-03|Method and assembly for the production of a composite blade|
    RU2016117233A| RU2659995C2|2013-10-04|2014-10-03|Method and device for the production of a composite blade|
    CA2926170A| CA2926170C|2013-10-04|2014-10-03|Method and assembly for the production of a composite blade|
    CN201480058777.1A| CN105682904B|2013-10-04|2014-10-03|For manufacturing the method for composite turbomachine blade and holding down assembly|
    EP14789324.2A| EP3052304B1|2013-10-04|2014-10-03|Method and assembly for the production of a composite blade|
    BR112016007437A| BR112016007437A2|2013-10-04|2014-10-03|compaction assembly for a preform, and method for fabricating a composite turbocharger blade|
    US15/026,918| US11072100B2|2013-10-04|2014-10-03|Method and compaction assembly for manufacturing a composite turbomachine blade|
    JP2016520063A| JP2016538152A|2013-10-04|2014-10-03|Method for manufacturing a composite turbomachine blade and compression assembly therefor|
    JP2019218272A| JP6989582B2|2013-10-04|2019-12-02|Methods for manufacturing composite turbomachinery blades and compression assemblies for them|
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