Fibrous preform with stiffeners formed by unidirectional layers of yarns

Abstract

Fibrous preform with stiffeners formed by unidirectional layers of yarns. The invention relates to a fibrous preform (10) for a turbomachine blade comprising two fibrous portions (14) forming an aerodynamic profile of the blade defining between them an internal volume (16), wherein each fibrous portion has at least one vibration-damping fibrous stiffener (19a; 19b) comprising one or more unidirectional layers of yarns (191a; 191b) which is present in the internal volume. Figure for the abstract: Fig. 3.

Description

Title of the invention: Fibrous preform with stiffeners formed by unidirectional layers of yarns Technical field

[0001] The present invention relates to a fiber preform intended to form a reinforcement for a turbomachine blade and provided in an interior volume with one or more fiber stiffeners formed by one or more unidirectional layers of threads, which make it possible to dampen the vibration modes during operation. The invention also relates to a method for manufacturing a turbomachine blade comprising the formation of a matrix in a porosity of the fiber preform. Prior art

[0002] Aircraft parts are commonly made of composite material, comprising a fibrous reinforcement and a matrix present in the porosity of this reinforcement, with the aim of reducing the mass while retaining good mechanical properties. The fibrous reinforcement can be obtained by three-dimensional weaving or by stacking two-dimensional fabric layers. In particular, US 2013017093 is known, which describes an aircraft propeller blade comprising a fibrous reinforcement comprising two fibrous portions forming an aerodynamic profile and defining between them an interior volume in which a lower density conforming insert is present. This solution makes it possible to further reduce the mass while retaining satisfactory mechanical properties.The problem of reducing mass and preserving mechanical properties by switching to composite material arises, in particular, for turbomachine blades, in particular outlet guide vanes or flow straighteners ("Outlet Guide Vane"; "OGV") which are subject to significant mechanical loads during operation.

[0003] It is desirable to provide turbomachine blades made of composite material having a reduced mass while presenting optimized mechanical strength, in particular with respect to the vibratory stresses exerted on the part in operation. Statement of the invention

[0004] The invention relates to a fiber preform for a turbomachine blade comprising two fiber portions forming an aerodynamic profile of the blade and defining between them an interior volume, wherein each fibrous portion has at least one vibration damping fibrous stiffener comprising one or more unidirectional layers of yarns which is present in the interior volume.

[0005] For the sake of brevity, the expression “fibrous damping stiffener of the vibrations” will be referred to in the following as “fibrous stiffener”.

[0006] The vibratory stresses during operation of the turbomachine can induce undesirable modes within a blade in operation. In this respect, [Fig. 1] illustrates, at four successive times represented from top to bottom, the displacement of the fibrous portions 14 forming the aerodynamic profile of an outlet guide vane made of composite material under the effect of vibrations encountered during operation. The fibrous portions 14 vibrate in phase opposition with modification of the distance between these portions 14 which has been identified by the inventors as being able to damage the part and / or negatively impact the performance of the engine, by the geometric modification of the aerodynamic profiles linked to the modifications of the modal deformations in the operating range.In order to address this problem, the invention proposes the incorporation of fibrous stiffeners which make it possible to oppose the vibration of the fibrous portions in phase opposition and their relative displacement and to couple their movements, in particular at the level of the vibrational antinodes. The use of unidirectional layers of yarns makes it possible to provide the desired stiffness to significantly dampen problematic vibration modes in operation, while limiting disturbances to the textile definition of the fibrous portions in order to reduce the risk that the stiffeners will lead to uncontrolled textile modifications which could lead to embrittlement of the material.

[0007] In an exemplary embodiment, said at least one fibrous stiffener extends along a radial direction of the preform.

[0008] Alternatively, said at least one fibrous stiffener extends along an axial direction of the preform. It will be noted that it is not outside the scope of the invention if the fibrous preform has a fibrous stiffener extending along the radial direction, and another fibrous stiffener extending along the axial direction.

[0009] In one exemplary embodiment, the fibrous portions are formed by three-dimensional weaving.

[0010] In particular, said at least one fibrous stiffener may be present on a decoupling zone on which the unidirectional layer(s) of yarns are separated from the corresponding fibrous portion, and the yarns of this or these unidirectional layers may be woven with the corresponding fibrous portion outside the decoupling zone.

[0011] Such a characteristic advantageously contributes to optimizing the bending stiffness of the blade, which is of particular interest for certain applications, such as an outlet guide blade.

[0012] As a variant, said at least one fibrous stiffener is attached to each fibrous portion.

[0013] In an exemplary embodiment, said at least one fibrous stiffener extends to the across the interior volume from one fibrous portion to the other fibrous portion.

[0014] Such a characteristic helps to further improve the damping of problematic vibration modes in operation such as the natural modes of membranes.

[0015] In an exemplary embodiment, each fibrous portion has at least two vibration-damping fibrous stiffeners, each comprising one or more unidirectional layers of yarns and which are present in distinct regions of the interior volume.

[0016] Such a characteristic helps to further improve the damping of problematic vibration modes during operation.

[0017] In particular, each fibrous portion may have a first fibrous stiffener extending along the radial direction and present in a region delimited by the planes of equation XI = 0.15*C and X2 = 0.45*C, and a second fibrous stiffener extending along the radial direction and present in a region delimited by the planes of equation X3 = 0.50*C and X4 = 0.80*C, where C denotes the chord of the blade preform and the coordinates XI, X2, X3 and X4 being measured along the axial direction taking the leading edge as the origin.

[0018] Such an example constitutes a first example of a particular arrangement making it possible to optimize the damping of problematic vibration modes during operation.

[0019] In particular, each fibrous portion may have a first fibrous stiffener extending along the radial direction and present in a region delimited by the planes of equation X5 = 0.10*C and X6 = 0.40*C, a second fibrous stiffener extending along the radial direction and present in a region delimited by the planes of equation X7 = 0.35*C and X8 = 0.65*C, and a third fibrous stiffener extending along the radial direction and present in a region delimited by the planes of equation X9 = 0.60*C and X10 = 0.90*C, where C denotes the chord of the blade preform and the coordinates X5, X6, X7, X8, X9 and X10 being measured along the axial direction taking the leading edge as the origin.

[0020] Such an example constitutes a second example of a particular arrangement making it possible to optimize the damping of problematic vibration modes during operation.

[0021] The two examples of arrangement described above are applicable to various blade geometries, in particular whether they are mobile or fixed. However, the first arrangement can be preferred for blades with reduced chord length.

[0022] In an exemplary embodiment, the fiber preform is a preform of an outlet guide vane.

[0023] The invention also relates to a turbomachine blade comprising a fiber preform as described above, and a matrix present in a porosity of the fiber preform.

[0024] The blade may be an aircraft turbomachine blade.

[0025] The invention also relates to a turbomachine comprising a turbomachine blade described above. The turbomachine may be an aircraft turbomachine.

[0026] The invention also relates to a method for manufacturing a turbomachine blade made of composite material, comprising at least:

[0027] - the formation of a fibrous preform as described above, and - the formation of a matrix in a porosity of the fibrous preform.

[0028] In an exemplary embodiment, a shaping insert made of fugitive material is present in the interior volume of the preform, and the method comprises, after the formation of the matrix, the elimination of the shaping insert.

[0029] In this case, a blade is obtained made of composite material which is hollow, having an empty interior volume. It is, of course, not outside the scope of the invention if the shaping insert is not intended to be eliminated but to remain in the blade, for example so as to reduce its mass compared to a monolithic part without interior volume. Brief description of the drawings

[0030] [Fig-1] [Fig.l] schematically represents displacements in op phase position of fibrous portions of an outlet guide vane outside the invention for a vibratory mode in operation, at four successive times (from top to bottom).

[0031] [Fig.2] [Fig.2] schematically and partially represents an example of an outlet guide vane according to the invention.

[0032] [Fig.3] [Fig.3] schematically represents a section of the blade of [Fig.2] along III-III.

[0033] [Fig.3A] [Fig.3A] schematically and partially represents the extension of the fiber stiffeners present in the blade of figures 2 and 3 along the height.

[0034] [Fig.4] [Fig.4] schematically represents a section of a variant of the outlet guide vane according to the invention.

[0035] [Fig.5] [Fig.5] schematically represents a detail of the blade of [Fig.4] showing an example of arrangement of the unidirectional layers of fiber stiffener wires relative to the fiber portions.

[0036] [Fig.6] [Fig.6] schematically represents a variant of [Fig.5] showing another example of arrangement of the unidirectional layers of yarns of the fibrous stiffener relative to the fibrous portions.

[0037] [Fig.7] [Fig.7] schematically represents a variant of the blade of [Fig.4] with fibrous stiffeners passing through the interior volume and extending from one fibrous portion to the other fibrous portion.

[0038] [Fig.8] [Fig.8] represents, schematically and partially, a variant outlet guide vane according to the invention.

[0039] [Fig.9] [Fig.9] schematically represents another variant of the outlet guide vane according to the invention.

[0040] [Fig. 10] [Fig. 10] schematically represents an example of a flowchart of a method for manufacturing a part according to the invention. Description of the embodiments

[0041] The invention will be described below and in the attached drawings in application to an outlet guide vane. The invention nevertheless applies to other examples of turbomachine blades, such as a fan blade, a compressor blade or a turbine blade. It will be noted in particular that the invention can be applied to a static turbomachine blade as well as to a mobile turbomachine blade, for example a rotary one.

[0042] The following also provides a description of the invention applying to the case of a fiber preform formed by three-dimensional weaving, but the scope of the invention does not go beyond the scope of the invention when the preform is obtained by other techniques, for example by stacking layers of two-dimensional fabric or unidirectional layers.

[0043] [Fig.2] represents an example of an outlet guide vane 1 according to the invention. This blade 1 is a static turbomachine part which makes it possible to "straighten" the flow at the outlet of the fan in the secondary flow. The blade 1 comprises an aerodynamic profile 3, capable of directing the flow towards the downstream of the turbomachine, and platforms 5 and 7 which delimit a flow vein of the flow. The profile 3 extends between a leading edge 3a and a trailing edge 3b along an axial direction DA. The leading edge 3a is located on the upstream side and the trailing edge 3b on the downstream side. The platforms 5 and 7 are spaced along a radial direction DR. The profile 3 has in cross-section relative to the radial direction DR a curved shape of variable thickness between its leading edge 3a and its trailing edge 3b, as shown schematically in [Fig.3].

[0044] The blade 1 is made of composite material and comprises a fiber preform 10 obtained by three-dimensional weaving which is densified by a matrix present in the porosity thereof. The fiber preform 10 of the turbomachine part 1 corresponds to the fiber reinforcement 10 thereof and defines the aerodynamic profile. The fiber preform 10 is in the shape of the blade 1 and is formed by three-dimensional weaving of first and second threads, in the example illustrated. The formation of the fiber preform 10 initially comprises the formation of a fiber blank by three-dimensional weaving using a Jacquard-type loom on which a bundle of weft threads has been arranged in a plurality of layers, the weft threads being connected by warp threads. By "three-dimensional weaving" or "3D weaving" is meant here a fabric in in which at least some of the warp threads bind weft threads over several weft layers. It should be noted, however, that, within the scope of the invention, the first threads may be the warp threads and the second threads the weft threads or vice versa, the roles between warp and weft threads being interchangeable. The fiber preform may have an "interlock" weave, i.e. a three-dimensional weave in which each layer of first threads binds several layers of second threads with all the threads of the same column of first threads having the same movement in the plane of the weave. It is not outside the scope of the invention if another three-dimensional weave is used to form the preform. The material of the first and second threads is chosen according to the application, the first and second threads being able to be made of carbon or a ceramic material, such as silicon carbide or an oxide ceramic.

[0045] When weaving the fiber blank corresponding to the illustrated preform, a delinking is produced between two successive layers of second yarns on a delinking zone 12. This delinking makes it possible to define two fiber portions 14 that are delinked and not woven together on the delinking zone 12 and that can be separated from each other. The fiber portions 14 define between them an interior volume 16, which is here in the form of a pocket 16 or a cavity 16. In particular, in the delinking zone 12, no layer of yarns of a fiber portion 14 is woven with a layer of yarns of another fiber portion 14. In the delinking zone 12, no yarn connects both by weaving a layer of yarns of a fiber portion 14 with a layer of yarns of another fiber portion 14.The fibrous portions 14 may form fibrous skins, of relatively thin thickness, for example less than or equal to 10 mm, in particular between 2 mm and 10 mm. The fibrous portions 14 are each obtained by three-dimensional weaving in the example illustrated.

[0046] The uncoupling zone 12 extends here between a first axial end 12a located on the side of the leading edge 3a to a second axial end 12b located on the trailing edge 3b. The uncoupling zone 12 may extend over at least 50%, for example at least 75%, of a dimension of the preform, for example of the chord thereof (which corresponds to the distance between the leading edge 3a and the trailing edge 3b). In the example illustrated, the uncoupling zone 12 extends over substantially the entire height of the fiber preform 10 but it is not outside the scope of the invention if it extends over only a portion of this height. The weaving is continuous outside the uncoupling zone 12 so as to connect the fiber portions 14 and form a single piece of fabric. The leading edge 3a is here woven continuously so as to connect the two fibrous portions 14 by weaving in a woven zone 15.Such continuous weaving at the leading edge 3a is advantageous for strengthening its resistance to possible impacts. The trailing edge 3b is also here continuously woven so as to. connecting the two fibrous portions 14 by weaving in a woven zone 11. Alternatively, the fibrous portions 14 can be connected other than by weaving on the trailing edge 3b. In the example illustrated, radial disconnections can also be made so as to form the fibrous reinforcement of the platforms 5 to 7 from the fibrous reinforcement of the profile 3.

[0047] The interior volume 16 defined by the fibrous portions 14 is intended to accommodate the shaping insert 18 before the formation of the matrix. This insert 18 gives the desired shape to the fibrous preform, and in particular to the aerodynamic profile 3. In the example illustrated, the shaping insert 18 is introduced through a radial end of the fibrous preform which belongs to the decoupling zone 12. In the preform, the fibrous portions 14 enclose the shaping insert 18. The shaping insert 18 is illustrated here as being in a single piece but it is not outside the scope of the invention if it is made up of several separate elements. The shaping insert 18 can be produced by molding or machining in a block of material. The shaping insert 18 here comprises ends 18a and 18b rounded to the shape of the leading edge 3a and the trailing edge 3b respectively.The shaping insert 18 may also comprise a middle portion 18c between the ends 18a and 18b in the shape of at least part of the intrados and the extrados of the blade 1.

[0048] According to a first example corresponding to Figures 2 and 3, the blade 1 which is intended to be mounted in the turbomachine also comprises the shaping insert 18. In this case, a shaping insert 18 of lower density than the density of the fibrous portions 14 densified by the matrix will advantageously be chosen, with a view to lightening the part. The shaping insert 18 may be formed from a porous material, such as a foam or a cellular material, for example as described in document WO 2011 / 083250. The shaping insert 18 may be rigid so as not to deform during operation. According to a second example corresponding to [Fig. 4], the blade intended to be mounted in the turbomachine is hollow, the internal volume 16 being empty. In this case, the shaping insert 18 introduced to form the preform was removable or made of fugitive material and was removed after densification by the die.

[0049] As indicated above, fiber stiffeners have been integrated into the preform in order to improve the resistance of the blade to vibrational stresses during operation and thus increase its service life. The following describes details relating to these fiber stiffeners according to several exemplary embodiments.

[0050] In this respect, Figures 3, 3A and 4 illustrate a first example of fiber stiffeners that can be used in the context of the invention. The case of Figures 3 and 3A differs from the case of [Fig. 4] only in that the insert 18 is or is not present in the blade. In the illustrated example, each fibrous portion 14 has two fibrous stiffeners 19a-19b which are present in distinct regions of the interior volume 16. The invention is however not limited to this precise number of stiffeners. According to a variant, each fibrous portion may have more than two fibrous stiffeners, regularly spaced or not, for example at least three or four fibrous stiffeners. As a variant, each fibrous portion has only one fibrous stiffener.

[0051] Each fibrous stiffener 19a-19b is formed from several unidirectional layers of yarns 191a-191b, that is to say by several layers of yarns 191a-191b which extend substantially in the same direction. It is not outside the scope of the invention if the fibrous stiffeners comprise only a single unidirectional layer. The yarns 191a-191b are not woven or bonded together in each fibrous stiffener 19a-19b. The yarns 191a-191b are present in the interior volume 16, on an internal surface SI of the fibrous portions 14 delimiting this interior volume 16. The example illustrated concerns the case of fibrous stiffeners 19a-19b whose yarns 191a-191b extend along the radial direction DR. An orientation of the unidirectional layers along the axial direction DA is also possible and will be discussed later in connection with [Fig.9].In the example of figures 3 and 4, the fibrous stiffeners 19a-19b form reliefs projecting from the fibrous portions 14 in the interior volume 16. The wires 191a-191b are arranged in each stiffener 19a-19b so as to give the latter a variable thickness with possibly a maximum thickness positioned in a region of maximum relative displacement of the fibrous portions 14 associated with a vibrational mode of the blade in operation.

[0052] Those skilled in the art will recognize that the number and positioning of the stiffeners 19a-19b depends on the part and the vibratory stresses encountered during operation and will be able to seek a compromise between the desired damping effect and control of the mass of the blade incorporating the stiffeners.

[0053] In order to optimize the damping, it is possible to position each fiber stiffener 19a-19b in a region comprising an antinode of the vibrational mode and delimited by planes whose positions correspond to amplitudes of relative displacement of the fiber portions 14 equal to 20% of an amplitude of said antinode.

[0054] According to one example, each fibrous portion 14 may have (i) a first fibrous stiffener 19a present in a region delimited by the planes P1 and P2 respectively of equation XI = 0.15*C and X2 = 0.45*C, and (ii) a second fibrous stiffener 19b present in a region delimited by the planes P3 and P4 respectively of equation X3 = 0.50*C and X4 = 0.80*C, where C denotes the chord of the blade or the blade preform and the coordinates XI, X2, X3 and X4 are measured along the axial direction DA taking the leading edge 3a as the origin. The majority (more than 50%), or even all, of the threads 191a of the first fibrous stiffener 19a may be present between the planes PI and P2. The majority (more than 50%), or even all, of the wires 191b of the second fiber stiffener 19b may be present between planes P3 and P4.

[0055] It will be noted that fibrous stiffeners present on two distinct fibrous portions 14 may be opposite each other (the first fibrous stiffeners 19a are opposite each other as well as the second fibrous stiffeners 19b in the illustrated example). These fibrous stiffeners 19a or 19b may be present on the same plane orthogonal to the axial direction DA.

[0056] The wires 191a-191b of the unidirectional layers (or the stiffeners 19a and 19b) may each extend over at least 50% of the height H of the fiber preform or the blade, or even over at least 75% of this height. Unless otherwise stated, the height of the blade is measured along the radial direction DR.

[0057] According to one example and as illustrated in [Fig.3A], the wires 191a-191b may extend at least from the plane Q1 to the plane Q2 where the planes Q1 and Q2 are respectively of equation Y1 = 0.1*H and Y2 = 0.9*H, with possibly Y1 = 0.05*H and / or Y2 = 0.95*H, H designating the height of the blade or the blade preform and the coordinates Y1 and Y2 being measured along the radial direction DR taking as origin the internal radial end of the blade or the blade preform.

[0058] Figures 5 and 6 which will now be described show two variants of integration of the fibrous stiffeners 19a-19b into the textile of the fiber preform of the blade. These variants apply, in an equivalent manner, regardless of the number or position of the stiffeners. In the example illustrated in [Fig.5], the threads 191a can be co-woven with the fibrous portions 14 in the woven zones 194 and separated from the latter in a delinking zone 190. The delinking zone 190 is located between the woven zones 194. The woven zones 194 can form a single piece of fabric. The delinking 190 is here carried out along the radial direction DR but the same principle remains applicable to the case of stiffeners extending along the axial direction DA as described below. Thus in the example of [Fig.5], the uncoupling zone 190 is produced during the weaving of the blank in order to remove the wires 191a and form the stiffener 19a.The integration of the stiffeners thus does not require an additional step after weaving. In this case, an insert 192 can be positioned to hold the threads 191a in place during the formation of the matrix, which insert can advantageously be made of a fugitive material so as to be eliminated after the formation of the latter. In the variant of [Fig. 6], the threads 191a are attached to the corresponding fibrous portion 14 after the formation of the latter. They can be held by gluing for example or mechanically before the formation of the matrix. Figures 5 and 6 illustrate the case of the threads 191a of the stiffener 19a but remain, of course, applicable whatever the stiffener, and in particular for the stiffener 19b.

[0059] The examples which have just been described, in connection with figures 3 to 6, concern fibrous stiffeners 19a-19b which do not extend from one fibrous portion 14 to another. [Fig.7] illustrates a variant in which the fibrous stiffeners 19c and 19d comprise unidirectional layers of yarns 191c-191d extending through the interior volume 16 from one fibrous portion 14 to the other fibrous portion 14. Those skilled in the art will favor the use of a through-stiffener such as that of [Fig.7] or a non-through-stiffener as illustrated in Figures 3 and 4 depending on the compromise sought between vibration damping and control of the mass of the blade. The use of through-stiffeners 19c and 19d may be favored for large blades, such as fan blades. For smaller blade geometries, non-through stiffeners of the type shown in Figures 3 and 4 may be preferred. [Fig.7] illustrates a case without a conforming insert 18 but, according to a variant not illustrated, a conforming insert in several parts may be present in the interior volume 16.

[0060] Examples have just been described, in connection with FIGS. 3 to 7, in which each fibrous portion 14 has two fibrous stiffeners. The example of [Fig. 8] which will now be described concerns a variant in which each fibrous portion 14 has three fibrous stiffeners.

[0061] In the example of [Fig.8], each fibrous portion 14 has three fibrous stiffeners 19e, 19f and 19g which can each have a structure as described above. According to one example, each fibrous portion 14 may have (i) a first fibrous stiffener 19e present in a region delimited by the planes P5 and P6 respectively of equation X5 = 0.10*C and X6 = 0.40*C, (ii) a second fibrous stiffener 19f present in a region delimited by the planes P7 and P8 respectively of equation X7 = 0.35*C and X8 = 0.65*C, and (iii) a third fibrous stiffener 19g present in a region delimited by the planes P9 and P10 respectively of equation X9 = 0.60*C and X10 = 0.90*C, where C denotes the chord of the blade or of the blade preform. The coordinates X5, X6, X7, X8, X9 and X10 are measured along the axial direction DA taking the leading edge 3a as the origin.

[0062] According to one example, the following characteristics can also be verified:

[0063] - the wires of the unidirectional layer(s) of the first stiffener 19e can extend at least from plane Q3 to plane Q4 where planes Q3 and Q4 are respectively of equation Y3 = 0.2*H and Y4 = 0.7*H, with possibly Y3 being able to vary between 0.00*H and 0.40*H and / or Y4 being able to vary between 0.50*H and 0.90*H,

[0064] - the wires of the unidirectional layer(s) of the second stiffener 19f can extend at least from plane Q5 to plane Q6 where planes Q5 and Q6 are respectively of equation Y5 = 0.1 *H and Y6 = 0.9*H, with possibly Y5 being able to vary between 0.05 *H and 0.1 *H and / or Y6 being able to vary between 0.90*H and 0.95 *H, and

[0065] - the wires of the unidirectional layer(s) of the third stiffener 19g may extend at least from plane Q7 to plane Q8 where planes Q7 and Q8 are respectively of equation Y7 = 0.3*H and Y8 = 0.7*H, with possibly Y7 being able to vary between 0.10*H and 0.50*H, and / or Y8 being able to vary between 0.50*H and 0.90*H,

[0066] where H denotes the height of the blade or blade preform and the coordinates Y3, Y4, Y5, Y6, Y7 and Y8 are measured along the radial direction DR taking as origin the inner radial end of the blade or blade preform.

[0067] [Fig. 9] shows the case of a 19h fiber stiffener extending along the axial direction DA of the preform. In a manner similar to what was described above, it is possible to have several fiber stiffeners extending along the axial direction DA and arranged at different heights of the blade preform.

[0068] In order to optimize the damping, each fiber portion 14 may have at least one fiber stiffener 19h present in a region delimited by the planes P5 and P6 defined above and / or at least one fiber stiffener 19h present in a region delimited by the planes P7 and P8 defined above and / or at least one fiber stiffener 19h present in a region delimited by the planes P9 and P10 defined above. Alternatively, each fiber portion 14 may have at least one fiber stiffener 19h present in a region delimited by the planes P1 and P2 defined above and / or at least one fiber stiffener 19h present in a region delimited by the planes P3 and P4 defined above. The fiber stiffeners 19e may extend over more than 50% of the chord of the blade or the preform, as illustrated.

[0069] Various possible structures for blades and blade preforms according to the invention have just been described. The following describes details relating to the method of manufacturing the blade that can be implemented within the framework of the invention.

[0070] [Fig. 10] is a flowchart of an example of a method according to the invention. In a first step E10 a fiber blank of the blade is obtained. The blank can be obtained by three-dimensional weaving or by stacking two-dimensional fabric plies or unidirectional layers. The blank comprises the fiber stiffeners described above. As indicated above, these stiffeners can be formed during the weaving of the blank by carrying out a wire exit 191a on a delinking zone 190 (example of [Fig. 5]) or be integrated after obtaining the blank by attaching them to the fiber portions (example of [Fig. 6]). The blank is then shaped with introduction of the shaping insert 18 into the interior volume 16 (step E20). The fibrous portions 14 enclose the shaping insert 18 and take its shape to define the aerodynamic profile.The shaping insert 18 may be intended to be removed after formation of the matrix in order to obtain a hollow blade, or be present in the blade intended to be mounted in the turbomachine. Once the blank has been shaped and the shaping insert 18 introduced, the matrix is ​​formed in the porosity thereof by a method known per se (step E30). By . For example, in the case where the part is made of an organic matrix composite, the formation of the matrix may comprise injecting a resin into the porosity of the preform and curing, for example crosslinking it, so as to form the matrix. The matrix is ​​formed in the porosity of the fibrous portions 14 as well as around the wires 191a-191d of the unidirectional layers and in the inter-wire spaces 191a-191d. It is not outside the scope of the invention when the matrix is ​​not made of an organic material but of a ceramic material, for example in the case where the blade is intended to be mounted in the hot part of a turbomachine, for example in the case of a turbine blade. In this case, the ceramic matrix may be formed by chemical vapor infiltration (“CVI”), melt infiltration (“MELT-INFLATRATION”; “MI”) or by impregnation and pyrolysis of polymer ("Polymer Impregnation and Pyrolysis"; "PIP"). The matrix formation techniques are known per se and do not require further detail.

[0071] After forming the matrix, the shaping insert 18 can be eliminated if desired, for example by melting or dissolving with a solvent (optional step E40), or simply removing the insert. Machining or finishing treatments are also carried out, if desired, after forming the matrix in order to obtain the blade ready to be mounted in the turbomachine.

[0072] The expression “between ... and ...” must be understood as including the limits.

Claims

1.

2.

3. Claims Fibrous preform (10) for a turbomachine blade (1) comprising two fibrous portions (14) forming an aerodynamic profile of the blade and defining between them an interior volume (16), in which each fibrous portion has at least two vibration-damping fibrous stiffeners (19a-19g) each comprising one or more unidirectional layers of threads (191a-191d) and which are present in distinct regions of the interior volume, and in which: - each fibrous portion has a first fibrous stiffener (19a; 19c) extending along a radial direction (DR) and present in a region delimited by the planes (PI; P2) of equation XI = 0.15*C and X2 = 0.45*C, and a second fibrous stiffener (19b; 19d) extending along the radial direction and present in a region delimited by the planes (P3; P4) of equation X3 = 0.50*C and X4 = 0.80*C, where C denotes the chord of the blade preform and the coordinates XI, X2, X3 and X4 are measured along an axial direction (DA) taking the leading edge (3a) as the origin, or - each fibrous portion (14) has a first fibrous stiffener (19e) extending along a radial direction (DR) and present in a region delimited by the planes (P5; P6) of equation X5 = 0.10*C and X6 = 0.40*C, a second fibrous stiffener (19f) extending along the radial direction and present in a region delimited by the planes (P7; P8) of equation X7 = 0.35*C and X8 = 0.65*C, and a third fibrous stiffener (19g) extending along the radial direction and present in a region delimited by the planes (P9; P10) of equation X9 = 0.60*C and X10 = 0.90*C, where C denotes the chord of the blade preform and the coordinates X5, X6, X7, X8, X9 and X10 being measured along an axial direction (DA) taking as origin the leading edge (3a). Fibrous preform (10) according to claim 1, in which the fibrous portions (14) are formed by three-dimensional weaving.Fibrous preform (10) according to claim 2, wherein said at least two fibrous stiffeners (19a-19h) are present on a debonding zone (190) on which the unidirectional layer(s) of yarns (191a-191d) are separated from the corresponding fibrous portion (14), and in which the yarns of this or these unidirectional layers are woven with the corresponding fibrous portion outside the zone of. unbinding.

4. Fibrous preform (10) according to any one of claims 1 or 2, in which said at least two fibrous stiffeners (19a-19h) are attached to each fibrous portion (14).

5. A fibrous preform (10) according to any one of claims 1 to 4, wherein said at least two fibrous stiffeners (19c; 19d) extend through the interior volume (16) from one fibrous portion (14) to the other fibrous portion (14).

6. A fibrous preform (10) according to any one of claims 1 to 5, wherein the fibrous preform is a preform of an outlet guide vane (1).

7. A turbomachine blade comprising a fiber preform according to any one of claims 1 to 6, and a matrix present in a porosity of the fiber preform.

8. Method for manufacturing a turbomachine blade (1) made of composite material, comprising at least: - the formation of a fiber preform (10) according to any one of claims 1 to 6, and - the formation of a matrix in a porosity of the fiber preform.

9. A method according to claim 8, wherein a shaping insert (18) of fugitive material is present in the interior volume of the preform, and the method comprising, after formation of the matrix, removing the shaping insert.

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