One-piece preform of the awl incorporating overlapping portions of unidirectional fabric
The use of unidirectional fabric portions in three-dimensional weaving simplifies the shaping of composite material blades, addressing deployment challenges and enabling complex geometries with improved mechanical properties.
Patent Information
- Application Number
- FR2022013052
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2022-12-09
- Publication Date
- 2024-12-13
- Estimated Expiration
- 2042-12-09
AI Technical Summary
The deployment of platforms, walls, and spoilers during the shaping of composite material blades produced by three-dimensional weaving is difficult due to the limitations of deployability of three-dimensional woven textures and the problem of triple points at the intersection of walls, spoilers, and the blade base.
A manufacturing process involving three-dimensional weaving with unidirectional fabric portions to facilitate the shaping of fibrous preforms, reducing stresses and tensions at connection points, allowing for the formation of complex geometries in composite material blades.
The process enables the production of composite material blades with improved mechanical properties and complex geometries by simplifying the shaping of platforms, walls, and spoilers, enhancing the deployability of fibrous preforms.
Smart Images
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Abstract
Description
Title of the invention: One-piece blade preform incorporating overlapping unidirectional fabric portions. Technical field
[0001] The present invention relates to the field of composite material blades comprising a fibrous reinforcement densified by a matrix. The targeted field is that of gas turbine blades for aircraft engines or industrial turbines. Prior art
[0002] The production of blades in composite material for turbomachinery has already been proposed.
[0003] Organic matrix composites (OMCs) and ceramic matrix composites (CMCs) replace metallic parts in certain sections of turbomachinery. Their use helps optimize aircraft performance, particularly by improving turbomachine efficiency and reducing the overall mass of the turbomachine, thereby significantly reducing harmful emissions (CO, CO2, NOx, etc.).
[0004] US patent 9,086,454 describes the manufacture of a turbomachine blade from a composite material comprising a fibrous reinforcement densified by a matrix. More precisely, this process is characterized by the fact that the fibrous blank produced by three-dimensional weaving is shaped to obtain a one-piece fibrous preform having a first part forming the blade and root preform and at least a second part forming the blade platform preform. Thus, after densification of the preform, it is possible to obtain a composite material blade having a fibrous reinforcement consisting of the preform and densified by the matrix, forming a single piece with a platform equipped with overlapping fins.The production of fibrous reinforcement by three-dimensional weaving in a single piece offers several advantages, including giving the blade very good mechanical properties, in particular very good resistance to delamination, and allowing the production of parts with complex geometries.
[0005] On a gas turbine blade, secondary sealing and aerodynamic functions are required. In the lower part of the blade, i.e., near the blade root, these functions are ensured by platforms connected to each other by flanges and cover flaps. In the case of a blade made of composite material with a fibrous reinforcement produced by three-dimensional weaving in a single piece, the deployment of the platforms, flanges, and flaps during the shaping of the fibrous blank (creation of the blade preform) can prove to be difficult due to the limitations of the deployability of three-dimensional woven textures and the problem of the triple point at the intersection of the walls, the spoilers and the foot of the dawn. Description of the invention
[0006] It is therefore desirable to be able to propose a solution for the production of blades in composite material from a three-dimensional weave which does not present the aforementioned disadvantages.
[0007] To this end, the invention proposes a method for manufacturing a fibrous preform of a turbomachine blade made of composite material, the method comprising:
[0008] - the formation by three-dimensional or multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns of a fibrous blank extending, along a longitudinal direction corresponding to the longitudinal direction of the blade to be produced, between first and second longitudinal ends, the fibrous blank extending, along a transverse direction corresponding to the transverse direction of the blade to be produced, between first and second transverse ends intended to form respectively a leading edge and a trailing edge of the blade, the fibrous blank extending, along a thickness direction of the blank, between first and second faces intended to form respectively an intrados face and an extrados face of the blade,
[0009] the fibrous blank being separated along the thickness direction into first to fifth parts in first to fourth unbonds each extending along the longitudinal direction from a unbond bottom present at a determined distance from the first longitudinal end of the fibrous blank, the first part being located between the second and fourth parts, on the one hand, and the third and fifth parts, on the other hand, the first part being connected by weaving to the second to fifth parts in a zone extending between the first longitudinal end of the blank and the unbond bottoms,
[0010] the fourth and fifth parts comprising on the side of the first transverse end of the blank a portion in which the warp yarns are not woven with the weft yarns so as to define first and second portions of unidirectional fabric, each portion of unidirectional fabric extending over a determined distance along the longitudinal direction at least from the bottom of the third and fourth unbindings and over a determined distance along the transverse direction from the first transverse end,
[0011] the second and third parts comprising on the side of the second transverse end a portion in which the warp yarns are not woven with the weft yarns so as to define third and fourth portions of single-fabric rectional, each portion of unidirectional tissue extending over a determined distance along the longitudinal direction at least from the bottom of the first and second debondings and over a determined distance along the transverse direction from the second transverse extremity,
[0012] - the formation, from the fibrous blank, of a preform of the blade to be produced, by unfolding on either side of the first part of the draft of segments of the second to fifth parts not linked to the first part and by shaping the unfolded segments of the second to fifth parts to form parts of preforms of platforms, walls and spoilers, the shaping of the segments of the second to fifth parts including folding the first to fourth portions of unidirectional fabric onto the first part.
[0013] The shaping of the walls and spoilers is greatly facilitated by the presence of unidirectional fabric sections at the triple points of the fiber blank. Indeed, the stresses and tensions induced in the blank at the connections of the second to fifth sections with the first section can be considerably reduced thanks to the relaxation provided by the unidirectional fabric sections. It is thus possible to obtain preforms of movable blades with a complex geometry from a single-piece woven fiber blank.
[0014] According to a feature of the process of the invention, the shaping of the unfolded segments of the fourth and fifth parts includes the formation of preform parts of a first platform, preform parts of an upstream wall, and preform parts of an upstream spur, and in which the shaping of the unfolded segments of the second and third parts includes the formation of preform parts of a second platform, preform parts of a downstream wall, and preform parts of a downstream spur.
[0015] According to another feature of the process of the invention, the formation of the preform parts of an upstream wall and the preform parts of an upstream spoiler includes folding along the transverse direction of a first part of the first and second portions of unidirectional fabric onto a second part of said first and second portions of unidirectional fabric extending along the longitudinal direction.
[0016] According to another feature of the method of the invention, the formation of the preform parts of a downstream wall and the preform parts of a downstream spoiler includes folding along the transverse direction of a first part of the third and fourth portions of unidirectional fabric onto the first part.
[0017] The invention also relates to a method for manufacturing a fixed or moving turbomachine blade made of composite material, the method comprising:
[0018] - the manufacture of a turbomachine blade preform according to the fa- process Brication of a fibrous preform of a blade,
[0019] - the densification of the preform by a matrix to obtain a blade made of material composite having integrated first and second platforms, an integrated upstream wall and a integrated downstream wall, and an integrated upstream berm and a integrated downstream berm.
[0020] The invention further relates to a fibrous blade preform for a turbomachine having a three-dimensional or multi-layer weave comprising in one piece parts of first and second platform preform, parts of upstream and downstream wall preform, parts of upstream and downstream spoiler preform, and a blade preform part, the preform further comprising first and second portions of unidirectional fabric folded over the stilt preform part and third and fourth portions of unidirectional fabric folded over the blade part.
[0021] According to a feature of the preform of the invention, a first part of the first and second portions of unidirectional fabric is folded down in the transverse direction on the part of the blade preform at the level of the upstream wall preform parts and the upstream spoiler preform parts.
[0022] According to a feature of the preform of the invention, a part of the third and fourth portions of unidirectional fabric is folded down in the transverse direction onto a second part of said first and second portions of unidirectional fabric extending in the longitudinal direction at the level of the downstream wall preform parts and the downstream spoiler preform parts.
[0023] According to another feature of the preform of the invention, it further comprises a foot preform part and a stilt preform part.
[0024] The invention further relates to a turbomachine blade made of composite material comprising a fibrous reinforcement densified by a matrix, the blade comprising first and second platforms, upstream and downstream walls, upstream and downstream spoilers and a blade, the fibrous reinforcement comprising a fibrous blade preform according to the invention.
[0025] The invention further relates to a movable turbomachine blade made of composite material comprising a fibrous reinforcement densified by a matrix, the blade comprising a foot, a strut, first and second platforms, upstream and downstream walls, upstream and downstream spoilers and a blade, the fibrous reinforcement comprising a fibrous blade preform according to the invention.
[0026] The invention further relates to an aeronautical engine comprising a plurality of blades according to the invention.
[0027] The invention further relates to an aircraft comprising at least one engine according to the invention. Brief description of the drawings
[0028] [Fig.1] Fig.1 is a schematic plan view of a woven fibrous blank intended for the production of a fibrous preform of a movable blade according to an embodiment of the invention,
[0029] [Fig.2] The [Fig.2] is a lateral cross-sectional view of the rough draft of the [Fig.1] along plane II-n of the [Fig.1],
[0030] [Fig.3] The [Fig.3] is a side cross-sectional view of the rough draft of the [Fig.1] along plane III-III of the [Fig.1],
[0031] [Fig.4] The [Fig.4] is a side cross-sectional view of the rough draft of the [Fig.1] along plane IV-IV of the [Fig.1],
[0032] [Fig.5] The [Fig.5] is a schematic view at enlarged scale of weaving plans of the rough of the [Fig.1],
[0033] [Fig.6] The [Fig.6] is a schematic view at enlarged scale of weaving plans of the rough of the [Fig.1],
[0034] [Fig.7] Fig.7 is a schematic perspective view showing a step in the production of a preform of a moving blade from the fibrous blank of Figures 1 to 4,
[0035] [Fig.8] Fig.8 is a schematic perspective view showing another step in the production of a preform of a movable blade from the fibrous blank of Figures 1 to 4,
[0036] [Fig.9] Fig.9 is a schematic perspective view showing another step in the production of a preform of a movable blade from the fibrous blank of Figures 1 to 4,
[0037] [Fig.1OA] Fig.1OA is a schematic perspective view showing another step in the production of a preform of a movable blade from the fibrous blank of Figures 1 to 4,
[0038] [Fig.1OB] Fig.1OB is a schematic perspective view showing another step in the production of a preform of a movable blade from the fibrous blank of Figures 1 to 4.
[0039] [Fig. 11 A] The [Fig. 11 A] is a schematic perspective view showing another step the fabrication of a preform of the moving blade from the fibrous blank shown in figures 1 to 4,
[0040] [Fig. 1 IB] The [Fig. 1 IB] is a schematic perspective view showing another step in the production of a preform of a movable blade from the fibrous blank of Figures 1 to 4,
[0041] [Fig. 12] The [Fig.8] a schematic perspective view showing a movable blade obtained from the blade preform of figures 1 IA and 1 IB. Description of the implementation methods
[0042] The invention is applicable to different types of platform turbomachine blades integrated. It is particularly applicable to fixed compressor blades, i.e., those without a base or strut. It is also applicable to moving compressor and turbine blades of various gas turbine bodies.
[0043] The [Fig.1] shows in plan view a fibrous blank 101 from which a fibrous preform of a movable blade can be formed according to an embodiment of the invention.
[0044] The blank 101 is obtained from a strip 100 woven by three-dimensional (3D) weaving, the strip 100 generally extending in a direction D. "Three-dimensional weaving" or "3D weaving" here refers to a weaving method in which at least some of the weft yarns interlace warp yarns over several layers of warp yarns, or vice versa. An example of three-dimensional weaving is the so-called "interlock" weave. The weaving is carried out, for example, with warp yarns extending in the direction D, it being noted that weaving with weft yarns extending in this direction is also possible. A plurality of blanks 101 can be woven one after the other in the direction D. It is also possible to weave several parallel rows of blanks 101 simultaneously.
[0045] In the embodiment shown in Figures 1 to 4, a fibrous blank 101 extends, along a longitudinal direction DL corresponding to the longitudinal direction of the blade to be produced, between first and second longitudinal ends 101a, 101b and, along a transverse direction DT corresponding to the transverse direction of the blade to be produced, between first and second transverse ends 101c, 101l, intended to form respectively a leading edge and a trailing edge of the blade. The fibrous blank further extends, along a thickness direction DE of the blank, between first and second faces 101e, 101l, intended to form respectively an intrados face and an extrados face of the blade.
[0046] The fibrous blank 101 comprises, within its thickness (thickness direction DE), first through fifth portions 102, 103, 104, 105, 106 extending along the longitudinal direction DL. The first portion 102 is debonded from the second through fifth portions 106 and 107 at a debonding zone Zdei comprising first through fourth debondings 103a, 104a, 105a, 106a (Figures 2 to 4). The debondings 103a, 104a, 105a, 106a extend across the entire width of the blank 101 along the transverse direction DT. The debonds 103a, 104a, 105a, 106a each extend along the longitudinal direction Dl from a debonding bottom 103b, 104b, 105b, 106b present at a determined distance from the first longitudinal end 101a of the fibrous blank 101. The first part 102 is located along the thickness direction DE between the second and fourth parts 103, 105, on the one hand, and the third and fifth parts 104, 106, on the other hand.The first part 102 is linked to the second to fifth parts 103 to 106 by 3D weaving in an area 107 extending between the first longitudinal end. The transverse 101a of the blank and the bottoms 103b, 104b, 105b, 106b of the unties 103a, 104a, 105a, 106a. The area 107 is intended to form a blade foot. In the example described here, the untie bottoms 103b and 104b extend between the first and second transverse ends 101c, lOld in a straight line parallel to the transverse direction DT ([Fig.l]) so as to form a flat lower platform, while the untie bottoms 105b and 106b have a slope between the first and second transverse ends 101c, lOld ([Fig.l]) so as to form an inclined upper platform as explained below.
[0047] In a well-known way, a debonding is provided between two layers of warp yarns by omitting to pass a weft yarn through the debonding zone to link yarns of warp layers located on either side of the debonding.
[0048] The drawings in Figures 5 and 6 show an example of 3D weaving with an interlock weave and unlinks 105a and 106a, the unlinks 103a and 104a being obtained in the same way as the unlinks 105a and 106a. In [Fig. 6], the unlinks are represented by dashed lines. Part 102 comprises a plurality of warp yarn layers (8 in the illustrated example) which are linked by 3D weaving. Parts 105 and 106 each comprise a plurality of warp yarn layers (4 in the example illustrated in [Fig. 6]) which are linked together by 3D weaving.
[0049] In the zone 107 located between the first longitudinal end 101a and the unlinkages 103a, 104a, 105a and 106a delimited by the unlinkage bottoms 103b, 104b, 105b and 106b the warp yarn layers of parts 102 to 106 are all linked together ([Fig.5]).
[0050] According to the invention, the fourth and fifth parts 105, 106 comprise, on the side of the first transverse end 101c of the blank, a portion in which the warp yarns are not woven with the weft yarns so as to define first and second portions of unidirectional fabric 1051 and 1061 ([Fig. 2]). Each portion of unidirectional fabric 1051, 1061 extends for a determined distance along the longitudinal direction DL at least from the unbinding point 105b, 106b of the third and fourth unbinding points 105a, 106a and for a determined distance along the transverse direction DT from the first transverse end 101c. In the example described here, the unidirectional tissue portions 1051 and 1061 extend on either side of the unbinding bases 105b, 106b ([Fig.2]).
[0051] Similarly, the second and third parts 103, 104 comprise, on the side of the second transverse end 10Id, a portion in which the warp yarns are not woven with the weft yarns so as to define third and fourth portions of unidirectional fabric 1031, 1041 ([Fig. 4]). Each portion of unidirectional fabric extends over a determined distance along the longitudinal direction DL at least from the bottom of the first and second unbindings 103a, 104a and over a distance determined along the transverse direction DT from the second transverse end lOld. In the example described here, the unidirectional tissue portions 1031 and 1041 extend on either side of the unbinding bases 103b, 104b ([Fig.4]).
[0052] After weaving, as shown in Figures 7 and 8, a fibrous preform 130 of the blade to be produced is formed from the blank 101. More specifically, the first part 102 is shaped to form a foot preform portion 137, a spar preform portion 138, and a blade or airfoil preform portion 139 comprising first and second transverse edges 139c and 139d intended to form the leading and trailing edges of the blade to be produced, respectively. The airfoil preform portion also comprises first and second faces 139e and 139f intended to form an intrados and an extrados face of the blade to be produced, respectively. The parts 103 and 104 not connected to parts 105 and 106, respectively, are cut to form segments 103d and 104d. Similarly, parts 105 and 106 not connected to part 102 are cut out to form segments 105d and 106d.Segments 103d and 104d not connected to parts 105 and 106 respectively, and segments 105d and 106d not connected to part 102, are unfolded or deployed. Unfolding is carried out at the unbundling points. Segments 103d and 104d are first shaped to form lower preform parts 133a and 134a, while segments 105d and 106d are first shaped to form upper preform parts 135a and 136a.
[0053] As illustrated in [Fig.9], the first and second portions of unidirectional fabric 1051 and 1061 are first folded down along the longitudinal direction DL onto the first part 102 of the blank shaped to form the preform part of blade 139.
[0054] As illustrated in Figures 10A and 10B, the shaping of the unfolded segments 105d, 106d continues to form preform parts of an upstream wall 135d, 136d, preform parts of an upstream spur 135b, 136b, and preform parts of a downstream spur 135c and 136c. The formation of the upstream wall preform parts 135d, 136d and the upstream spoiler preform parts 135b, 136b includes the folding along the transverse direction DT of a first part 1051a, 1061a respectively of the first and second portions of unidirectional fabric 1051, 1061 on a second part 1051b, 1061b respectively of the first and second portions of unidirectional fabric 1051, 1061 held against the blade preform part 139 along the longitudinal direction DL.This greatly facilitates the shaping of the upstream wall preform parts 135d, 136d and the upstream spoiler preform parts 135b, 136b by reducing the tensions and stresses on the texture of the fibrous blank in particular at the folds of . suitcase corner type.
[0055] As illustrated in Figures 11A and 11B, the shaping of the unfolded segments 103d, 104d continues to form preform parts of a downstream wall 133d, 134d, and preform parts of a downstream spoiler 133c, 134c. The formation of the preform parts of the downstream wall 133d, 134d and the preform parts of the downstream spoiler 133c, 134c comprises folding, along the transverse direction DT, a first part 1031a, 1041a, respectively, of the third and fourth portions of unidirectional fabric 1031, 1041 onto a second part 1031b, 1041b, respectively, of the third and fourth portions of unidirectional fabric 1031, 1041 held against the stilt preform part 138 along the direction longitudinal DL.This greatly facilitates the shaping of the downstream wall preform parts 133d and 134d and the downstream spoiler preform parts 133d and 134d by reducing the tensions and stresses on the texture of the fibrous blank, particularly at the suitcase-corner folds.
[0056] The next step is to densify the fibrous preform 130. Densifying the fibrous preform intended to form the fibrous reinforcement of the blade to be manufactured consists of filling the porosity of the preform, in all or part of its volume, with the material constituting the matrix. This densification can be carried out in a manner known per se, using the liquid process (CVL), the gas process (CVI), the ceramic filler injection process (Slurry Cast), the silicon alloy impregnation process (MI or RMI), or a combination of one or more of these processes.
[0057] The liquid process consists of impregnating the preform with a liquid composition containing a precursor of the matrix material. The precursor is usually in the form of a polymer, such as a high-performance epoxy resin, possibly diluted in a solvent. The preform is placed in a mold that can be sealed tightly with a cavity shaped like the final molded blade. The mold is then closed, and the liquid matrix precursor (for example, a resin) is injected into the entire cavity to impregnate all the fibrous material of the preform.
[0058] The transformation of the precursor into a matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after removal of any solvent and crosslinking of the polymer, the preform always being held in the mold having a shape corresponding to that of the part to be produced.
[0059] In the case of the formation of a carbon or ceramic matrix, the heat treatment consists of pyrolyzing the precursor to transform the matrix into a carbon or ceramic matrix, depending on the precursor used and the pyrolysis conditions. For example, liquid ceramic precursors, particularly SiC or SiCN, These can be polycarbosilane (PCS), polytitanocarbosilane (PTCS), or polysilazane (PSZ) type resins, while liquid carbon precursors can be resins with relatively high coke content, such as phenolic resins. Several consecutive cycles, from impregnation to heat treatment, can be carried out to achieve the desired degree of densification.
[0060] In the case of forming an organic matrix, in particular, the densification of the fibrous preform can be achieved by the well-known resin transfer molding (RTM) process. According to the RTM process, the fibrous preform is placed in a mold having the external shape of the part to be produced. A thermosetting resin is injected into the internal space of the mold containing the fibrous preform. A pressure gradient is generally established in this internal space between the point where the resin is injected and the resin discharge ports in order to control and optimize the impregnation of the preform by the resin.
[0061] The densification of the preform can also be achieved by polymer impregnation and pyrolysis (PIP), or by impregnation with a slurry (“slurry cast”), containing for example SiC and organic binders, followed by infiltration with liquid silicon (“melt infiltration”).
[0062] The densification of the fibrous preform can also be achieved, in a known manner, by gaseous means through chemical vapor infiltration of the matrix (CVI). The fibrous preform corresponding to the fibrous reinforcement of the blade to be produced is placed in a furnace into which a reactive gaseous phase is admitted. The pressure and temperature prevailing in the furnace and the composition of the gaseous phase are chosen so as to allow the diffusion of the gaseous phase within the porosity of the preform to form the matrix by deposition, at the core of the material in contact with the fibers, of a solid material resulting from the decomposition of a constituent of the gaseous phase or from a reaction between several constituents, unlike the pressure and temperature conditions specific to CVD (Chemical Vapor Deposition) processes which lead exclusively to deposition on the surface of the material.
[0063] The formation of a SiC matrix can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of MTS while a carbon matrix can be obtained with hydrocarbon gases such as methane and / or propane giving carbon by cracking.
[0064] A densification combining liquid and gaseous route can also be used to facilitate implementation, limit costs and manufacturing cycles while obtaining satisfactory characteristics for the intended use.
[0065] The densification processes described above make it possible to produce, from the fibrous structure of the invention, mainly parts made of composite material organic matrix (CMO), carbon matrix (C / C) and ceramic matrix (CMC).
[0066] In the case of manufacturing a part from an oxide / oxide composite material, the fibrous structure is impregnated with a slurry loaded with refractory oxide particles. After removal of the liquid phase of the slurry, the resulting preform is subjected to heat treatment to sinter the particles and obtain a refractory oxide matrix. The impregnation of the structure can be carried out using processes employing a pressure gradient, such as injection molding (RTM) or submicron powder aspirate (APS).
[0067] After densification, a blade 200 is obtained in composite material which, as illustrated in the [Fig. 12], comprises in its lower part a foot 207 formed by the foot preform part 137 of the fibrous preform 130 which extends into a stilt 208 formed by the stilt preform part 138 of the preform 130 and a blade or aerodynamic profile 209 formed by the blade preform part 139 of the preform 130. The blade 209 comprises a leading edge 209a and a trailing edge 209b corresponding respectively to the first and second transverse edges 139c and 139d of the fibrous preform 130 as well as an intrados face and an extrados face 209e and 209f corresponding respectively to the first and second faces 139e and 139f of the preform 130.The auger 200 further comprises a lower platform 210 corresponding to lower platform preform parts 133a and 134a of preform 130, an upper platform 220 corresponding to upper preform parts 135a and 136a of preform 130, an upstream wall 230 corresponding to upstream wall preform parts 135d and 136d of preform 130, an upstream cover spoiler 240 corresponding to upstream spoiler preform parts 135b and 136b of preform 130, a downstream wall 250 corresponding to downstream wall preform parts 133d and 134d of preform 130, and a downstream cover spoiler 260 corresponding to downstream spoiler preform parts 135c and 136c of preform 130. 130.
Claims
1. Claims Method for manufacturing a fiber preform for a turbomachine blade made of composite material, the method comprising: - forming by three-dimensional or multi-layer weaving between a plurality of layers of warp threads and a plurality of layers of weft threads a fibrous blank (101) extending, in a longitudinal direction (DL) corresponding to the longitudinal direction of the blade to be produced, between first and second longitudinal ends (101a, 101b), the fibrous blank extending, in a transverse direction (Dt) corresponding to the transverse direction of the blade to be produced, between first and second transverse ends (101c, 101d) intended to form respectively a leading edge and a trailing edge of the blade, the fibrous blank extending, in a thickness direction (DE) of the blank, between first and second faces (101e, 101f) intended to form respectively an intrados face and an extrados face of the blade, the fibrous blank being separated along the thickness direction into first to fifth parts (102, 103, 104, 105, 106) in first to fourth unlinkings (103a, 104a, 105a, 106a) each extending along the longitudinal direction from a unlinking bottom (103b, 104b, 105b, 106b) present at a determined distance from the first longitudinal end (101a) of the fibrous blank (101), the first part (102) being located between the second and fourth parts (103, 105), on the one hand, and the third and fifth parts (104, 106), on the other hand, the first part being connected by weaving to the second to fifth parts in an area extending between the first longitudinal end (101a) of the outline and the background (103b, 104b, 105b, 106b) of the unbindings (103a, 104a, 105a, 106a), the fourth and fifth parts (105,106) comprising on the side of the first transverse end (101c) of the blank a portion in which the warp threads are not woven with the weft threads so as to define first and second portions of unidirectional fabric (1051, 1061), each portion of unidirectional fabric extending over a determined distance in the longitudinal direction at least from the bottom (105b, 106b) of the third and fourth unlinkings (105a, 106a) and over a determined distance in the transverse direction from the first transverse end (101c), the second and third parts (103, 104) comprising on the side of the second transverse end (101d) a portion in which the warp threads are not woven with the weft threads so as to define third and fourth portions of unidirectional fabric (1031, 1041), each portion of unidirectional fabric extending over a determined distance in the longitudinal direction at least from the bottom (103b, 104b) of the first and second unlinkings (103a, 104a) and over a determined distance in the transverse direction from the second transverse end (101d), - the formation, from the fiber blank, of a preform (130) of the blade to be produced, by unfolding on either side of the first part (102) of the blank of segments (103d, 104d, 105d, 106d) of the second to fifth parts (103, 104, 105,106) not connected to the first part and by shaping the unfolded segments of the second to fifth parts to form parts of platform preforms (133a, 134a, 135a, 136a), low walls (133d 134d, 135d, 136d and spoilers (133b, 134b, 135b, 136b, 133c, 134c, 135c, 136c), shaping the segments of the second to fifth parts comprising folding the first to fourth portions of unidirectional fabric onto the first part.,
2. The method of claim 1, wherein shaping the unfolded segments (105d, 106d) of the fourth and fifth portions (105, 106) comprises forming preform portions of a first platform (135a, 136a), preform portions of an upstream wall (135d, 136d), and preform portions of an upstream spoiler (135b, 136b), and wherein shaping the unfolded segments (103d, 104d) of the second and third portions (103, 104) comprises forming preform portions of a second platform (133a, 134a), preform portions of a downstream wall (133d, 134d), and preform portions of a downstream spoiler (133c, 134c).
3. The method of claim 2, wherein forming the upstream wall preform portions (135d, 136d) and the upstream spoiler preform portions (135b, 136b) comprises folding in the transverse direction a portion (1051a, 1061a) of the first and second unidirectional fabric portions (1051, 1061) onto a second portion (1051b, 1061b) of said first and second unidirectional fabric portions extending in the longitudinal direction.
4. A method according to claim 2 or 3, wherein the formation of the preform portions of a downstream wall (133d, 134d) and preform portions of a downstream spoiler (133c, 134c) comprises folding in the transverse direction a portion (1031a, 1041a) of the third and fourth unidirectional fabric portions (1031, 1041) onto the first portion.
5. Method for manufacturing a turbomachine blade from composite material, the method comprising: - manufacturing a turbomachine blade preform according to any one of claims 1 to 4, - densifying the preform by a matrix to obtain a blade from composite material having first and second integrated platforms, an integrated upstream wall and a downstream wall, and an integrated upstream spoiler and a downstream spoiler.
6. A fiber blade preform (130) for a turbomachine having a three-dimensional or multi-layer weave comprising, in a single piece, first and second platform preform portions (135a, 136a, 133a, 134a), upstream and downstream wall preform portions (135d, 136d, 133d, 134d), upstream and downstream spoiler preform portions (135b, 136b, 133c, 134c), and a blade preform portion (139), the preform further comprising first and second unidirectional fabric portions (1031, 1041) folded over the stilt preform portion and third and fourth unidirectional fabric portions (1051, 1061) folded over the blade portion.
7. The preform of claim 6, wherein a portion (1031a, 1041a) of the first and second unidirectional fabric portions (1031, 1041) is folded in the transverse direction over the blade preform portion (139) at the upstream wall preform portions and the upstream spoiler preform portions.
8. A preform according to claim 6 or 7, wherein a portion (1051a, 1061a) of the third and fourth unidirectional fabric portions (1051, 1061) is folded in the transverse direction over a second portion (1051b, 1061b) of said first and second unidirectional fabric portions extending in the longitudinal direction at the downstream wall preform portions and the downstream spoiler preform portions.
9. A preform according to any one of claims 6 to 8, further comprising a foot preform portion (137) and a stilt preform portion (138).
10. Turbomachine blade made of composite material comprising first and second platforms, upstream and downstream walls, upstream and downstream spoilers and a blade portion, the fiber reinforcement comprising a fiber blade preform according to any one of claims 6 to 8.
11. A movable turbomachine blade made of composite material comprising a root, a stilt, first and second platforms, upstream and downstream walls, upstream and downstream spoilers and a blade portion, the fiber reinforcement comprising a fiber blade preform according to claim Q
12. y. An aeronautical engine comprising a plurality of blades according to claim 10 or a plurality of moving blades according to claim 11.
13. Aircraft comprising at least one engine according to claim 12.