• 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:
    preform and monobloc blade for turbomachine fibrous preform for a turbomachine blade, this preform is being obtained by a three-dimensional weave of a piece. according to the invention, the preform comprises a first longitudinal part (41), capable of forming a blade root, a second longitudinal wall (42) extending through the first longitudinal part and capable of forming a blade section, and a first transverse part (51) extending transversely from the junction between the first and second longitudinal parts (41, 42) and capable of forming a first platform.
    公开号:BR112015010844B1
    申请号:R112015010844-0
    申请日:2013-11-12
    公开日:2021-04-06
    发明作者:Matthieu Gimat；Dominique Marie Christian Coupe
    申请人:Snecma；Safran；
    IPC主号:
    专利说明:

    [0001] [0001] This report refers to a fiber preform for a turbomachine blade and also for a single-piece blade, formed using such a preform, an intermediate housing and a turbomachine including that blade.
    [0002] [0002] Such a preform can be used to produce a monobloc blade, having aerodynamic platforms. Such blades can, in particular, be guide blades and can be incorporated into the intermediate housing of an airplane turbojet, for example. STATE OF THE PREVIOUS TECHNIQUE
    [0003] [0003] A turbojet with a conventional side passage has a fan, or fan, distributing an air stream that is divided into both a primary stream, which is directed to the compressors, the combustion chamber and then to the turbocharger turbines, and also a secondary or side chain, which supplies the largest fraction of the thrust.
    [0004] [0004] The secondary current flows in a secondary passage provided between the outer shell of the jet and an inner shell containing the hot part of the turbomachine. These two housings are connected together and held in position by an intermediate housing composed of an inner hub, an outer cover and a plurality of structural arms extending radially and connecting the inner hub to the outer cover. In addition to their structural function of supporting the loads that result from the dynamic behavior of the turbomachinery as a whole, some of the structural arms are hollow, thus allowing installations to be passed, such as fluid pipes, electrical cables or, in fact, members for transmit mechanical strength.
    [0005] [0005] Furthermore, such a turbomachine includes a guide nozzle composed of a plurality of stationary blades, commonly referred to as outlet guide blades (OGVs), for the purpose of rectifying the secondary current coming from the fan.
    [0006] [0006] In order to reduce the weight of the turbojets and the number of parts composing them, proposals have been made to intermediate casings that incorporate the nozzle function, and that some of the structural arms are replaced by guide blades. However, such blades need to be provided with additional elements, such as aerodynamic platforms or fixing flanges, elements being fitted to the blade and significantly increasing its total weight, the number of parts involved (and particularly because of the fixers necessary to secure the elements in the shovel) and maintenance complexity.
    [0007] [0007] In order to improve some of the aspects mentioned above, proposals were made, and particularly in the French patent application FR 2 956 876, to design modules in the form of boxes composed of two composite blades, which are screwed on the internal and external platforms . However, although the progress provided by this solution is already significant, such a solution still involves a large number of parts, in particular fasteners, and it would be desirable to reduce that number in order to obtain more weight savings and also save time during assembly and maintenance.
    [0008] [0008] Such problems of reducing the weight or the number of parts used, saving space or simplifying manufacturing methods are found not only with guide blades, but they should be found more generally with all types of turbojet blades and, more particularly, with the fan blades.
    [0009] [0009] Therefore, there is a real need for a fiber preform, a shovel, an intermediate wrapper and a turbomachinery that avoid the disadvantages inherent to the aforementioned known systems. SUMMARY OF THE INVENTION
    [0010] [0010] This report refers to a fiber preform for a turbomachine blade, obtained by three-dimensional weaving of a single piece, said preform comprising a first longitudinal segment, suitable to form a blade root; a second longitudinal segment, extending through the first longitudinal segment and suitable for forming an airfoil part; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable to form a first platform.
    [0011] [0011] In this report, the terms "longitudinal", "transversal", "base", "top" and their derivatives are defined in relation to the main direction of the blade in question; the terms "axial", "radial", "tangential", "internal," external "and their derivatives are defined in relation to the main geometric axis of the intermediate housing and the turbomachinery. In addition, the terms" upstream "and" a downstream ”are used here in relation to the direction of advance of the weave (arrows T of the figures).
    [0012] [0012] Through this preform, it is possible to design a one-piece paddle, composed of a paddle root, an airfoil part and a platform: this one-piece design makes it possible to greatly reduce the number of parts that need to be designed and assembled together. In particular, there are considerable savings on fasteners and thus the weight and cost associated with them.
    [0013] [0013] In addition, incorporating the platform into the design of the blade itself gives rise to parts that are better optimized, without requiring extra thicknesses or additional parts to fix the various elements of the blade together. Such blades are therefore lighter and therefore provide significant savings in operation. The choice of composite materials also provides significant weight savings, and comparison with similar parts made of metal or ceramics.
    [0014] [0014] Of course, the maintenance of such a single-piece shovel is also made easier, since operations required for disassembly are reduced: in particular, it is possible to start work directly under the wing, because the fasteners are less numerous and more accessible.
    [0015] [0015] In certain embodiments, the preform further includes a second transverse segment extending transversely from the junction between the first and second longitudinal segments extending through the first transverse segment and going away from it, suitable for forming a second platform. It is often advantageous to provide the blade with a lateral pressure platform and a lateral suction platform, in order to provide an entire aerodynamic wall for the passage of air flow on either side of the blade.
    [0016] [0016] In certain embodiments, the first transverse segment is formed by at least a part of a free tail, said free tail and said second longitudinal segment being woven simultaneously in a non-interconnected manner, the non-interconnection starting at the junction between the first and second longitudinal segments.
    [0017] [0017] Such non-interconnection provides the advantage that the free tail weave corresponds to the transverse segment continuously with the first longitudinal segment, thereby structurally associating it with it, the first longitudinal segment forming the blade root that serves to support the shovel as a whole, while also assuming the downstream thickness along the second longitudinal segment, which is to form the airfoil part and which, therefore, needs to be thinner. Such a limit between the first and second longitudinal segments thus makes it possible to separate the weave from the part that is to become the structural part of the part that is to become the aerodynamic part: the transition of the required thickness between those two parts is made very easier, since, by separating the free tail, a considerable contribution to this change in thickness is already provided.
    [0018] [0018] In certain embodiments, the second transverse segment is done in an analogous manner.
    [0019] [0019] In other embodiments, the second transverse segment and said first longitudinal segment are woven together in a non-interconnected manner, said non-interconnection ending at the junction between the first and second segments. Weaving in this way advantageously makes it possible to reduce the number of layers devoted to the weaving of the platforms, while retaining the layers necessary to make the first transverse segment in the longitudinal segment.
    [0020] [0020] In other embodiments, the first transverse segment is formed by at least parts of the first and second free tails folded over one another, said first free tail and said first longitudinal segment being woven together, but in an unconnected manner, said second free tail and said second longitudinal segment being woven together, but in a non-interconnected manner, a layer crossing being provided at the junction between the first and second longitudinal segments in such a way that the threads of the first free tail extend into the second longitudinal segment and the wires of the second free tail come from the first longitudinal segment. The second transverse segment can be done in a similar way.
    [0021] [0021] In certain applications, it is desirable to have a blade root that is very thin, in order to allow it to be inserted in narrow spaces, for example, or a part of airfoil that retains a certain degree of thickness, p . in order to play an additional structural role: under such circumstances, the transition of the necessary thickness between the blade root and the airfoil part, that is, between the first and second longitudinal segments, may be small or even non- existing. Such a layer crossing then advantageously serves to provide such a continuity of thickness between the first and second longitudinal segments.
    [0022] [0022] In certain embodiments, the number of layers of yarn in the second longitudinal segment and, thus, its thickness, vary. This makes it possible to make the airfoil part thinner in order to improve its aerodynamic performance.
    [0023] [0023] In certain embodiments, the preform includes a third transverse segment and a fourth transverse segment, extending transversely on either side of the end upstream of the first longitudinal segment and suitable for forming blade fixing flanges; said third and fourth transverse segments are woven together in a non-interconnected manner, said non-interconnection ending at the upstream end of the first longitudinal segment. Through this preform, flanges are incorporated into the design and manufacture of the blade that serves to secure the blade to the turbomachinery: this amplifies the advantages mentioned above. In addition, the flanges are woven directly to extend the root, so that their structural connection with them is strengthened, thereby ensuring increased total mechanical strength.
    [0024] [0024] In certain embodiments, the preform further comprises a third transverse segment extending the second longitudinal segment and suitable for forming a blade head; and a fifth transverse segment, extending transversely from the junction between the second and third longitudinal segments and suitable to form a third platform. Certain blades are stationary and extend all the way through a fluid flow passageway: under such circumstances, the outer wall of the passageway may also need to have platforms placed on it. This preform serves to incorporate such a top platform also in the design and production of the blade: this amplifies the advantages mentioned above.
    [0025] [0025] In certain embodiments, the fifth transverse segment is obtained by non-interconnection analogous to that performed for the first transverse segment.
    [0026] [0026] In other embodiments, the fifth transverse segment is obtained by crossing a layer analogous to that performed for the first transverse segment.
    [0027] [0027] In certain embodiments, the preform similarly includes a sixth transverse segment, suitable for forming the second top platform: this provides a pair of top platforms, one on the pressure side and the other on the side suction.
    [0028] [0028] In certain embodiments, the preform includes seventh and eighth transverse segments analogous to the third and fourth transverse segments, and suitable for forming top flanges.
    [0029] [0029] In certain embodiments, the yarns used to weave the preform comprise carbon fibers. However, they can be any other type of yarn, for example, yarns comprising glass fibers or kevlar fibers.
    [0030] [0030] In certain embodiments, the wiring used for the three-dimensional weaving of the preform can be a 3D interlacing type wiring. However, the weaving of the outer surfaces of the passageway can be essentially two-dimensional, e.g. eg, being woven with a satin-type spinning.
    [0031] [0031] This report also refers to a turbomachine blade comprising a root, an airfoil part and a platform extending across the airfoil part, at the junction between the blade root and the airfoil part, said blade being made as a single piece of composite material by means of a fiber preform, according to any of the above embodiments, said preform being formed into a mold and embedded in a matrix.
    [0032] [0032] Through this one-piece configuration, incorporating at least one blade root, an airfoil part and a platform, the advantages described above are obtained in terms of mechanical strength, weight, cost, suitability for disassembly and ease of manufacture.
    [0033] [0033] In certain embodiments, the matrix is of the organic type. In particular, it can be an epoxy resin.
    [0034] [0034] In other embodiments, the matrix can be of the ceramic type.
    [0035] [0035] The present invention also provides an intermediate housing for a turbomachinery, comprising a plurality of blades, according to any of the above described embodiments, which are arranged angularly between an internal hub and an external cover.
    [0036] [0036] The present description also provides a turbomachinery fan having a plurality of blades, according to any of the above described embodiments.
    [0037] [0037] Finally, the present report refers to a turbomachinery including at least a blade or an intermediate enclosure or fan, according to any of the above embodiments.
    [0038] [0038] The characteristics and advantages specified above and others arise when reading the following detailed description of the embodiments of the proposed preform, the blade, the intermediate housing and the turbomachinery. This detailed description makes reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
    [0039] [0039] The attached drawings are diagrammatic and seek, above all, to illustrate the principles of the invention.
    [0040] [0040] In the drawings, from one figure to another, elements (or parts of an element) that are identical are identified by the same reference signs. In addition, the elements (or parts of an element) forming parts of different embodiments, but having functions that are analogous, are identified in the figures by numerical references that are incremented by 100, 200 etc.
    [0041] [0041] Figure 1 is a sectional elevation view of a turbomachinery of the invention.
    [0042] [0042] Figure 2 is a front view of an intermediate housing in an embodiment.
    [0043] [0043] Figure 3 is a perspective view of a shovel of a first embodiment.
    [0044] [0044] Figures 4A and 4B are diagrams showing the preform corresponding to this first embodiment of a shovel and how it is molded.
    [0045] [0045] Figure 5 is a simplified view of a non-interconnected zone.
    [0046] [0046] Figure 6 is a fragmentary and diagrammatic view of the weaving of this preform, corresponding to box VI of Figure 4A.
    [0047] [0047] Figures 7A and 7B are diagrams showing a second embodiment of a preform and how it is molded.
    [0048] [0048] Figures 8A and 8B are diagrams showing a third embodiment of a preform and how it is molded.
    [0049] [0049] Figures 9A and 9B are simplified layer crossing diagrams.
    [0050] [0050] Figures 10A and 10B are diagrams showing a fourth embodiment of a preform and how it is molded.
    [0051] [0051] Figures 11A and 11B are diagrams showing possible layer organization of the fourth preform. DETAILED DESCRIPTION OF METHODS
    [0052] [0052] In order to make the invention more concrete, the embodiments are described in detail below, with reference to the accompanying drawings. It should be remembered that the invention is not limited to these embodiments.
    [0053] [0053] Figure 1 is a sectional view of a vertical plane containing the main geometric axis A of a side-pass turbojet 1 of the invention. Going from upstream to downstream in the direction of the air flow it comprises: a fan 2; a low pressure compressor 3; a high pressure compressor 4; a combustion chamber 5; a high pressure turbine 6; and a low pressure turbine 7. In its upstream part, this turbojet 1 has an outer shell 8 and an inner shell 9 defining two concentric passages, a primary pass I and a secondary pass II. An intermediate housing 10 connects the outer and inner housing 8 and 9 to each other.
    [0054] [0054] In operation, the intermediate housing 9 divides the airflow accelerated by the fan 2 into a primary current, which follows the primary passage I and feeds the compressors 3, 4, the combustion chamber 5 and the turbines 6, 7 , as well as in a secondary stream, which follows the secondary or "lateral" passage that is ejected out of the turbojet, thereby supplying most of its thrust.
    [0055] [0055] Figure 2 is a diagrammatic front view of such an intermediate housing 10. It comprises an inner hub 11 attached to the intermediate housing 9 and an outer cover 12 attached to the outer housing 8. The inner hub 11 and the outer cover 12 are connected together, radially first by the structural arms 13 and secondly by the outlet guide blades (OGVs) 20.
    [0056] [0056] The structural arms 13 are hollow and serve to pass installations between the jet core included in the intermediate housing 9 and the periphery of the jet 1. Such installations include, in particular, hydraulic pipes, pneumatic tubes, electrical cables and, without a doubt, , mechanical force transmission shafts. These structural arms are preferably located at 6 hours and 12 hours in relation to the geometric axis A of the turbojet 1, that is, in the vertical plane, where most of the mechanical loads exerted by the weight of the turbojet accumulate.
    [0057] [0057] Figure 3 shows a first embodiment of a nozzle paddle 20 for such an intermediate casing 10. Such paddle 20 has a paddle root 21, an airfoil part 22 and a paddle head 23. The airfoil part 22 serves mainly to perform the aerodynamic function of the blade 20, while the root and head of the blade 21 and 23 serve mainly to fix the blade 20 and retain it mechanically.
    [0058] [0058] At its base end, the blade root 21 has base fixing flanges 33 and 34 extending substantially orthogonal to the blade root 21 and provided with holes 39, allowing the blade 20 to be fixed in the inner hub 11 of the intermediate housing 10.
    [0059] [0059] At its top end, the blade head 23 has top fixing flanges 37 and 38 extending substantially orthogonally to the blade head 23 and provided with holes 39 ', allowing the blade 20 to be fixed to the outer cover 12 of the intermediate housing 10.
    [0060] [0060] The paddle 20 also has lateral pressure and suction base platforms 31 and 32, extending substantially orthogonally to the airfoil part 22, on each of its sides, at the limit between the paddle root and the part airfoil 22. These base platforms 31 and 32 serve to mask the fasteners, in particular screws or bolts, used to secure the base flanges 33, 34 and thus the blade 20, thereby reconstituting an internal wall for the passage II, which is smooth and streamlined.
    [0061] [0061] Likewise, the paddle 20 has lateral pressure top and suction side platforms 35 and 36 extending substantially orthogonal to the airfoil part 22, on each side, at the limit between the paddle head 23 and the part of airfoil 22. These top platforms 35 and 36 serve to mask the fasteners, in particular screws or bolts, serving to secure the top flanges 37 and 38 and thus the blade 20, thereby reconstituting an external wall for the passage II which is smooth and aerodynamic.
    [0062] [0062] In this embodiment, the blade 20 has four platforms 31, 32, 35 and 36 and four fixing flanges 33, 34, 37 and 38, however, in other examples, certain platforms and / or certain flanges could be missing, in order to meet certain specific local details of the intermediate housing 10 or to facilitate certain aspects of assembly and maintenance.
    [0063] [0063] Figure 4A shows the three-dimensional (3D) woven preform 40, used to produce this first blade 20 embodiment. Figure 4B shows the same preform 40, after it has been shaped. Preform 40 is described below from upstream downstream in the weaving direction T, that is, from the bottom to the top of the figures. However, it should be understood that weaving could be carried out from the other end and occur in the opposite direction. Figure 6 shows, diagrammatically, the essential structures for weaving this preform 40 in box VI of Figure 4A.
    [0064] [0064] In this embodiment, preform 40 is woven 3D of carbon fibers, using 3D interlacing. Only the surfaces of preform 40 are bidimensionally (2D) woven using a satin weave.
    [0065] [0065] At the upstream end, the weaving begins with a first non-interconnected zone D1, and whose third and fourth transverse segments 53 and 54 are woven together and non-interconnectedly on opposite sides of a non-interconnected plane 61. It should be understood that the terms "transverse" and "longitudinal" are used here depending on the final position of the segment in question, the transverse segment necessarily being woven longitudinally before being folded across.
    [0066] [0066] Downstream of the first non-interconnected zone D1, a first interconnected zone L1 begins, in which the two strips above 53 and 54 are joined as a first longitudinal segment 41, which forms the root 21 of the blade 20.
    [0067] [0067] Weaving methods, which allow such non-interconnection to be carried out, are nowadays well known in the field of 3D weaving. As an illustration, Figure 5 shows such an unconnected weave in a simplified way. In the interconnected zone L, all layers of warp threads c (orthogonal to the plane of the figure) are held together by weft threads t (moving in the plane of the figure), thereby forming a single strip b0. Conversely, in the non-interconnected zone D, two strips b1 and b2 are woven together, but in a non-interconnected manner, that is, the weft threads t are independent in each of the strips b1 and b2, so that a plane does not -connected p is left between the two strips b1 and b2. Of course, such interconnection can be carried out equally well in the warp or weft direction and thus equally well with warp yarns and weft yarns.
    [0068] [0068] Downstream of this first interconnection zone L1 begins a second non-interconnected zone D2, in which a first free tail 50a, a second longitudinal segment 42 and a second free tail 50b are woven together in a non-interconnected manner, being separated respective non-interconnecting plans 62 and 63.
    [0069] [0069] Furthermore, within this second non-interconnected zone D2, the layer exits are progressively formed along the weave T, between the second longitudinal segment 42 and each of the free tails 50a and 50b. These layers are subsequently progressively reincorporated before the downstream end of the second longitudinal segment 42.
    [0070] [0070] The weaving methods that enable such layer exits to be carried out are now well known in the field of 3D weaving. Specifically, and as can be seen in Figure 6, the weft yarns are made to leave certain warp yarns free, referred to as "floating" yarns, because, since they are not attached to any weft yarns, they "float" and can subsequently be eliminated by shearing. It is possible, in this way, to eliminate the layers completely or in part, thereby allowing the thickness of certain areas of the preform to be reduced. In this embodiment, this serves to thin the second longitudinal segment 42 and thereby thin the airfoil part 22, which is derived therefrom.
    [0071] [0071] It should be noted in this topic that these layer exits are formed in this embodiment within the preform 40, while weaving is taking place: the warp threads c 'are thus included, that is, hidden, between the second longitudinal segment 42 on one side and the free tail 50a or 50b on the other side.
    [0072] [0072] Downstream of this second non-interconnected zone D2, the three aforementioned strips 50a, 42 and 50b are joined within a second interconnected zone L2, in order to form a third longitudinal segment 43, which is to form the head 23 of paddle 20.
    [0073] [0073] Finally, downstream of this second interconnected zone L2, a third non-interconnected zone L3 begins in which the seventh and eighth transverse segments are woven together in a non-interconnected manner, in order to present a non-interconnected plane 64.
    [0074] [0074] Once the weaving has been completed, the free tails 50a and 50b are cut out to form the first and fifth cross tails 51 and 55, respectively, and the second and sixth cross tails 52 and 56, respectively. These four cross tails 51,55, 52 and 56 are then folded outward, as represented by the arrows, in order to occupy their final transverse positions: they are used to form the pressure side and suction side platforms 31 and 32 and the pressure side and suction side top platforms 35 and 36.
    [0075] [0075] Once the free tails 50a and 50b have been cut, the float warp threads c ', located on the surface of the second longitudinal segment 42, become accessible and can be sheared.
    [0076] [0076] Finally, the third, fourth, seventh and eighth transverse segments 53, 54, 57 and 58 are folded out as represented by the arrows, in order to occupy their final transverse positions: they are used, respectively, to form the flanges base 33 and 34 and top flanges 37 and 38. Such a final configuration for preform 40 is shown in Figure 4B.
    [0077] [0077] Preform 40 can be moistened in order to make it more flexible and make it easier to manufacture the fibers. The preform is then inserted into an internal space molding mold, which corresponds to the desired configuration for preform 40.
    [0078] [0078] Preform 40 is then dried in order to become rigid, thereby maintaining the configuration imposed during molding. The performance 40 is finally placed in an injection mold having the desired dimensions for the final paddle 20, and a matrix is injected into it, in this embodiment an epoxy resin. As an example, such an injection can be performed by the technique of resin transfer molding (RTM). At the end of this step, a composite material paddle 20 is obtained which is composed of a woven preform 40 of carbon fibers embedded in an epoxy matrix. The machining stages can optionally be used to finish the technique and finish the blade 20.
    [0079] [0079] Figure 7A shows a second embodiment of a 3D woven preform 140 to produce a second paddle embodiment, which is entirely analogous to the first paddle embodiment 20, except that it does not have any top platforms. Figure 7B shows the same preform 140 after it has been formed.
    [0080] [0080] The weaving of this preform 140 is largely analogous to that of tool processing and is therefore not fully described again.
    [0081] [0081] Thus, going from upstream to the direction of weaving T, the weaving begins with a first non-interconnected zone D1, a first interconnected zone L1 and a second non-interconnected zone D2, analogous to the first embodiment. In contrast, the second non-interconnected zone D2 is extended by a third non-interconnected zone D3 ', in which the non-interconnected weaving of the free tails 150a and 150b is continued, while a third longitudinal segment 143 extends the second longitudinal passage 142 Consequently, the third longitudinal segment 143 is naturally not as thick as in the first embodiment. It is possible to compensate for this effect using thickness transition techniques, which are well known in the field of 3D weaving.
    [0082] [0082] Finally, downstream of this third non-interconnected zone D3 ', a fourth non-interconnected zone D4' begins, in which the non-interconnected weaving of the free tails 150a and 150b is continued, while the strip derived from the third longitudinal segment 143 is divided in a manner analogous to that of the first embodiment, in order to form the seventh and eighth transverse segments 157 and 158.
    [0083] [0083] The molding of this second preform embodiment 140 and the method of forming the final paddle are similar to those of the first embodiment. The final configuration of preform 140 is shown in Figure 7B.
    [0084] [0084] Figure 8A shows a third embodiment of a 3D woven preform 240, suitable for producing a paddle analogous to the first paddle embodiment 20. Figure 8B shows the same preform 240, after molding. This preform 240 shares a large number of characteristics with the embodiment of the first preform 40; these features in the form of the first preform 40; these characteristics are not described again. Preform 240 is described upstream downstream in the weaving direction T, that is, from the base towards the top of the figures. However, it should be understood that weaving could be carried out from the other end and in the opposite direction.
    [0085] [0085] At the upstream end, the weaving begins with a first non-interconnected zone D1 ", in which a first free tail 251a, of the first transverse segment 251, of the third transverse segment 253, of the fourth transverse segment 254 and a first tail free 252a, of the second transverse segment 252, are all woven together, in a non-interconnected manner, with the respective non-interconnection plans 265, 261 and 266.
    [0086] [0086] Downstream of the first non-interconnected zone D1 "begins a second non-interconnected zone D2, in which the non-interconnected weaving of the first free tails 251a, 252a, of the first and second transverse segments 251 and 252, continues, while the strips derived from the third and fourth transverse segments 253 and 254 are joined in a first longitudinal segment 241, which is to form the root 21 of the blade 20.
    [0087] [0087] Downstream of this second non-interconnected zone D2 ", a first crossing zone of layer C1" forms an interface with the third non-interconnected zone D3 ", in which a first free tail 250a, a second longitudinal segment 222 and a second free tail 250b are woven together in a non-interconnected manner together with corresponding non-interconnecting planes 262 and 263.
    [0088] [0088] In the first crossing zone of layer C1 ", the layers are crossed in such a way that the layers of threads of the first free tails 251a and 252a, of the first and second transversal segments 251 and 252, extend to the second segment longitudinal 242, while the layers of threads composing the free tails 250a and 250b are derived from the first longitudinal segment 241.
    [0089] [0089] Weaving methods, enabling the layers to be crossed in this way, are nowadays well known in the field of 3D weaving. As an illustration, Figure 9A is a simplified diagram of such a layer crossing. In the crossing zone of layer C, the weft threads c, from an upstream strip, are deflected downwards, in order to be attached downstream by the layer crossing zone C with the layers of the warp threads c of a strip of downstream base v2, while the weft threads t2 securing the layers of a base strip upstream m2 are deflected upwards in order to secure together the layers of a downstream top strip v1. Thus, the weft threads t1 and t2 intersect in the crossing zone of layer C. When associated with the technique of non-interconnection, this technique of crossing of layer makes it possible to weave two tails m2 and v2, which are not interconnected, so that they extend with each other, ensuring that they are securely attached to the main sheet m1, v1.
    [0090] [0090] In the preceding example, a plurality of wires t1 and t2 of each layer is involved in the layer crossing; however, in other examples, as in figure 9B, only one wire c1, c2 of each layer can be involved in the crossing of layers. This other example also illustrates that a layer crossing can be performed equally well with warp threads c1, c2 and weft threads t1, t2.
    [0091] [0091] Returning to figures 8A and 8B and the weaving of preform 240, within the third non-interconnected zone D3 ", the layer exits are formed progressively along the weave T, between the second longitudinal segment 242 and each of three causes 250a and 250b. These layers are subsequently progressively reincorporated before the downstream end of the second longitudinal segment 242.
    [0092] [0092] Downstream of this third non-interconnected zone D3 ", a second crossing zone of layer C2" forms an interface with a fourth non-interconnected zone D4 ", in which a second free tail 255b, of the fifth transverse segment 255, from the third longitudinal segment 243 and a second free tail 256b from the sixth transverse segment 256 are woven together in a non-interconnected manner, with respective non-interconnecting planes 267, 264 and 268.
    [0093] [0093] In the second crossing zone of layer C2 ”the layers cross, so that the layers of free tail threads 250a and 250b are extended towards the third longitudinal segment 243, while the layers of threads, making up the second free tails 255b, 256b, of the first and second transverse segments 255, 256, come from the second longitudinal segment 242.
    [0094] [0094] Finally, downstream of the fourth non-interconnected zone D4 ", a fifth non-interconnected zone D5" begins, in which the non-interconnected weaving of the second free tails 255b, 256b, of the first and second transverse segments 255, 256 , continues, while the strip coming from the third longitudinal segment 243 divides in a manner analogous to the first embodiment, in order to form the seventh and eighth transverse segments 257 and 258.
    [0095] [0095] Once the weaving has finished, the free tails 250a and 250b are cut, in order to form respectively the second free tail 251b of the first transverse segment 251 and the first free tail 255a of the fifth transverse segment 255, and also the second free tail 252b of the second transverse segment 252 and the first free tail 256a of the sixth transverse passage 256.
    [0096] [0096] The first and second free tails of each of the transverse segments 251, 252, 255 and 256 are then folded towards each other, as shown by the arrows, in order to assume their final transverse positions. Adhesive or stitching can be provided between each of the first and second free tails. The transverse segments 251,252, 255 and 256, respectively, form the base platforms on the pressure side and on the suction side 31 and 32 and the top platforms on the pressure side and suction side 35 and 36 of the paddle 20.
    [0097] [0097] Once the free tails 250a and 250b have been cut, the floating threads c ', which exist on the surface of the second longitudinal segment 242, are available and can be sheared.
    [0098] [0098] Finally, the third, fourth, seventh and eighth transverse segments 253,254, 257 and 258 are folded outward, as shown by the arrows, in order to occupy their final transverse positions: they form, respectively, the base flanges 33 and 34 and the top flanges 37 and 38.
    [0099] [0099] Such final configuration for preform 240 is shown in Figure 8B. The method of forming the blade 20 of this preform 240 is analogous to that of the first embodiment.
    [0100] [0100] Figure 10A shows a fourth embodiment of a three-dimensional woven preform 340, which enables a fourth embodiment of a shovel to be realized. Unlike the first three embodiments described above, this fourth embodiment does not represent a guide paddle of the intermediate wrapper, but undoubtedly a paddle paddle 2. However, the weaving method described above can equally well be adapted to other types of shovel and also to other types of shovel. Under such circumstances, it is possible, for example, to provide fastening flanges in a manner analogous to any of the first three embodiments. Figure 10B shows the same preform 340 after it has been molded.
    [0101] [0101] The weaving of this preform 340 is largely analogous to that of the first embodiment and is therefore not fully described again. The main difference lies in the use of non-interconnection in a “relay” configuration, making it possible to devote only N layers of weaving to the platforms, while 2N layers are required in the above embodiments.
    [0102] [0102] Thus, from upstream downstream in the direction of the weave T, the weave begins with a first non-interconnected zone D1 ”', in which the first cross-section 351 and the first longitudinal segment 341 are woven together in a non-interconnected manner with a non-interconnected plan 365 between them. During weaving, the first transverse segment 351 thus extends along a first side of the first longitudinal segment 341, the right side of the figure.
    [0103] [0103] Downstream of the first non-interconnected zone D1 "', a second non-interconnected zone D2"' begins, in which a free tail 350 and a second longitudinal segment 342 are woven together in a non-interconnected manner with a non-interconnected plane. -connected 363 between them. In this second non-interconnected zone D2 '', the free tail 350 thus extends along the second side of the second longitudinal segment 342, that is, the opposite side of the first transverse segment 351, to the left of the figure. Thus, the layers of the first transverse segment 351 are extended in the second longitudinal segment 342, while the layers of the free tail 350 are taken from the first longitudinal segment 341.
    [0104] [0104] Once the weaving has been completed, the second transverse segment 352 is obtained by cutting the free tail 350 in a manner analogous to the above embodiments. Under such circumstances, the first transverse segment 351 and the second transverse segment 352 are folded outward along the arrows in Figure 10B in order to occupy their final transverse positions: they form, respectively, the pressure side and side platforms. suction paddle.
    [0105] [0105] Other aspects of the molding of this fourth form of making a preform 340 and the method of forming the final blade are also analogous to the molding and forming described above. Since this preform 340 is for use in producing a fan blade, it can be seen that it does not have a third longitudinal segment and that it has no third and fourth transverse segments.
    [0106] [0106] Several layer transitions can be provided at the interface between the non-interconnected zones D1 "’ and D2 "’. In a first configuration shown in Figure 11A, these are simple non-interconnections, in which the layers of the first transverse segment 351 are extended linearly into the second longitudinal segment 342, in order to form their outermost layers; likewise, the free tail layers 350 are made linearly from the outermost layers of the first longitudinal segment 341.
    [0107] [0107] It can be seen at this point that the first longitudinal segment 341 can receive considerable, near its base end, and can then be made thinner towards the second longitudinal segment 342, in particular by making use of layer outputs. This makes it possible for the blade root, which is to be made using this first longitudinal segment 341, to receive a sambladura shape, allowing it to be mounted in the slots of a fan disk, while also ensuring that the airfoil, which is derived from the second longitudinal segment 342, is suitably thin.
    [0108] [0108] Figure 11B shows a variant in which the layer intersections are provided at the interface between the non-interconnected zones D1 "’ and D2 "’. In such a variant, it is no longer just the outermost threads of the first longitudinal segment 341 or the second longitudinal segment 342, respectively, that are used to form the second cross segment 352 or the first cross segment 351, respectively: some of the threads in these segments cross-sections 351, 352, in this example, are taken from the layers closest to the nuclei of the longitudinal segments 341, 342. The use of such weaves provides better attenuation of the imbalance that can be generated by the non-interconnection D1 ”'and D2”' in a relay configuration: the transition at the platform level is thus made smoother.
    [0109] [0109] A specific advantage of this fourth embodiment is to reduce the number of layers devoted to weaving the platforms. If each platform has N layers, only one thickness of N-layer is required, in addition to the layers of the longitudinal segments for the purpose of weaving both platforms, whereas twice N layers are necessary in the first three embodiments, that is, N layers on each of the two sides.
    [0110] [0110] A first advantage that stems directly from this reduction in the number of layers is the possibility of using a loom in a configuration that is simpler or of producing blades that are thicker or that are more complex.
    [0111] [0111] In addition, the thickness transition at the interface between the root and the airfoil is less and this is favorable.
    [0112] [0112] Finally, this weaving technique gives rise to less debris, thereby naturally reducing production costs: in this fourth embodiment, only one free tail needs to be cut, unlike two free tails in the other embodiments.
    [0113] [0113] The embodiments described above in the present description are given as a non-limiting illustration and, in light of this description, a person skilled in the art can easily modify these embodiments or can imagine others, while remaining within the scope of the invention .
    [0114] [0114] In addition, the various characteristics of these embodiments can be used alone or in combination. When they are combined, these features can be combined as described above or, otherwise, the invention is not limited to the specific combinations described in this report. In particular, unless otherwise specified, any feature described with reference to any embodiment may be applied in a manner analogous to any other embodiment.
    权利要求:
    Claims (9)
    [0001]
    Fiber preform for a turbomachine blade, obtained by three-dimensional monobloc weaving, comprising: a first longitudinal segment (241), suitable for forming a blade root (21); a second longitudinal segment (242), extending from the first longitudinal segment (241) and suitable to form an airfoil part (22); and a first transverse segment (251), extending transversely from the junction between the first and second longitudinal segments (241, 242), and suitable to form a first platform (31), characterized by the fact that the first transverse segment (251) is formed by at least parts of the first and second free tails (251a, 251b) folded over one another, said first free tail (251a) being woven together and in a non- interconnected with said first longitudinal segment (241), and still said second free tail (251b) being woven together and in a non-interconnected manner with said second longitudinal segment (242), a layer crossing (C1 ”) being provided at the junction between the first and second longitudinal segments (241, 242) so that the wires of the first free tail (251a) extend into the second longitudinal segment (242), and so that the wires of the second free tail (251b) come of the first longitudinal segment (241).
    [0002]
    Preform according to claim 1, characterized by the fact that it also includes a second transverse segment (252), extending transversely from the junction between the first and second longitudinal segments (241, 242), extending from the first transverse segment ( 251) and going away from it, suitable for forming a second platform (32).
    [0003]
    Preform according to claim 1 or 2, characterized by the fact that the number of layers of threads and, thus, the thickness of the second longitudinal segment (242) vary.
    [0004]
    Preform according to any one of claims 1 to 3, characterized in that it includes a third transverse segment and a fourth transverse segment (253, 254) extending transversely on each side of the end upstream of the first longitudinal segment (241) in the weaving direction (T), and suitable for forming the attachment flanges (33, 34) of the blade (20); and wherein said third and fourth transverse segments (253, 254) are woven together in a non-interconnected manner, said non-interconnected (D1) ending at the upstream end of the first longitudinal segment (241).
    [0005]
    Preform according to any one of claims 1 to 4, characterized by the fact that it further comprises: a third longitudinal segment (243) extending through the second longitudinal segment (242) and suitable for forming a blade head (23); and a fifth cross section (255) extending transversely from the junction between the second and third longitudinal segments (242, 243) and suitable to form a third platform (35).
    [0006]
    Turbomachine shovel, comprising: a shovel root (21); an airfoil part (22); and a platform (23), extending across the airfoil (22), at the junction between the blade root (21) and the airfoil part (22); said blade (20) being characterized by the fact that it is made in a monobloc manner of composite material, by means of a fiber preform (40) as defined in any one of claims 1 to 5, said preform (40) being shaped in a mold and embedded in a matrix.
    [0007]
    Intermediate housing for turbomachinery, which connects an outer housing (8) and an inner housing (9) defining two concentric passages, characterized by the fact that it comprises a plurality of blades (20) as defined in claim 6, arranged angularly between an inner hub (11) and an outer covering (12).
    [0008]
    Fan for turbomachinery, characterized by the fact that it comprises a plurality of blades (2) as defined in claim 6.
    [0009]
    Turbomachine, characterized by the fact that it includes at least one blade (20) as defined in claim 6, or an intermediate housing (10) as defined in claim 7, or a fan (2) as defined in claim 8.
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    同族专利:
    公开号 | 公开日
    EP2919955A1|2015-09-23|
    CA2891293A1|2014-05-22|
    JP6367818B2|2018-08-01|
    EP2919955B1|2017-08-02|
    RU2015122679A|2017-01-10|
    RU2653823C2|2018-05-14|
    CA2891293C|2021-01-12|
    BR112015010844A2|2017-07-11|
    US20160245103A1|2016-08-25|
    US10508559B2|2019-12-17|
    JP2015537149A|2015-12-24|
    CN105026123A|2015-11-04|
    WO2014076408A1|2014-05-22|
    CN105026123B|2018-02-09|
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    法律状态:
    2018-03-06| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2018-03-13| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2018-03-20| B06I| Publication of requirement cancelled [chapter 6.9 patent gazette]|Free format text: ANULADA A PUBLICACAO CODIGO 6.6.1 NA RPI NO 2462 DE 13/03/2018 POR TER SIDO INDEVIDA. |
    2019-12-10| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-02-02| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-04-06| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 12/11/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201261725632P| true| 2012-11-13|2012-11-13|
    US61/725,632|2012-11-13|
    US201361856878P| true| 2013-07-22|2013-07-22|
    US61/856,878|2013-07-22|
    PCT/FR2013/052714|WO2014076408A1|2012-11-13|2013-11-12|Monobloc preform and blade for turbo machine|
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