METHOD FOR MANUFACTURED A COMPOSITE PART WITH AN INTEGRATED JOINT AND A COMPOSITE PART OBTAINED BY SUCH A METHOD

Abstract

The invention relates to a method for manufacturing (100) a part (1) made of fiber-reinforced composite material densified by a matrix for a turbomachine, equipped with at least one integrated seal (2) extending from a surface of the part. The method comprises the following steps: - supplying a preform (9) forming the fiber reinforcement comprising inorganic fibers, - supplying at least one seal, - placing the preform in a first cavity (51) of a mold (50), - placing a portion of the seal in a cavity (53) of the mold (50) by complementary shape, the seal being made of a material different from that of the composite part, - closing the mold (50) to apply the seal to a surface of the preform, - thermocompression of the preform and the seal to obtain the composite part with the integrated seal. Figure for the abstract: Fig. 2

Description

Title of the invention: METHOD FOR MANUFACTURED A COMPOSITE PART WITH AN INTEGRATED JOINT AND A COMPOSITE PART OBTAINED BY SUCH A METHOD Technical field of the invention

[0001] The present invention relates to the aeronautical field. It relates in particular to a method for manufacturing a part made of composite material with fiber reinforcement densified by a matrix. Technological background

[0002] Figure 1 shows an example of an aircraft turbomachine 01 comprising a cowling 02 centered on the longitudinal axis X of the turbomachine 01 and mounted downstream of a fan or propeller. This cowling 02 is also radially mounted around an annular ferrule 03. This cowling 02 is made, in a known manner, of a fiber-reinforced composite material densified in a matrix. Seals 04 are fixed to an external surface 05 of the composite cowling 02 to fill gaps and / or prevent fluid leaks. These seals, generally flexible to allow for deformation, are attached and fixed after the composite cowling 02 has been manufactured.

[0003] Such a configuration represents a cost and may present a risk of reduced quality.

[0004] There is a need to resolve all or part of the aforementioned drawbacks. Summary of the invention

[0005] The objective of the present invention is to provide a simple and economical solution for easily integrating a flexible element into a composite material.

[0006] We achieve this objective in accordance with the invention by means of a method for manufacturing a part made of fiber-reinforced composite material densified by a matrix for a turbomachine, equipped with at least one seal which is integrated and which protrudes from a surface of the part, the method comprising the following steps: - supply of a preform forming the fibrous reinforcement comprising non-organic fibers, - supply of at least one seal, - placement of the preform in a first cavity of a mold, - placement of at least a portion of the seal in a cavity of the mold by complementary shape, the seal being made of a material different from the composite material of the part made of composite material, - closing the mold so as to apply the seal to a surface of the preform, and - thermocompression of the preform and the seal so as to obtain the part in composite material with the integrated seal.

[0007] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, the composite part includes at least one integrated seal embedded in the fiber reinforcement and the matrix during the single thermocompression step. Therefore, it is no longer necessary to install the seal after manufacturing the composite part, resulting in time savings and reduced manufacturing costs. Furthermore, incorporating the seal during the thermocompression step improves the control of positioning tolerances on the composite part(s). Positioning tolerances are reduced, as is the number of additional components, since the seal(s) are already fixed.

[0008] The process also includes one or more of the following steps and / or features, taken alone or in combination when technically feasible:

[0009] - the seal comprises at least one functional portion intended to be installed in the cavity and allowing a seal, and at least one base intended to be integrated into the densified preform.

[0010] - the fibrous reinforcement comprises fibers selected from the group comprising, Kevlar fibers, glass fibers, carbon fibers.

[0011] - the process includes a step of injecting a polymer matrix into the preform.

[0012] - the preform fibers are pre-impregnated.

[0013] - the matrix is ​​chosen from thermosets, thermoplastics and vitrimers.

[0014] - the matrix comprises a predetermined charge of particles.

[0015] - the seal is made of an elastomer, a rubber or a silicone.

[0016] - the functional portion comprises a circular, V-shaped, arrow-shaped section, of lip with an inclination, or triangular.

[0017] - the base has a cross-section of rectilinear, arrow-shaped, triangular or trapezoidal.

[0018] - the base has holes.

[0019] — the joint includes a sealing gasket.

[0020] — the mold closing step includes a substep of moving a part of the mold so as to apply the seal to the preform.

[0021] — the mold comprises a first part and a second part, each first part and second part comprising an impression intended to receive the preform.

[0022] The invention also relates to a part made of composite material obtained by the manufacturing process as described above, the part made of composite material including the fibrous reinforcement densified by the matrix and at least one thermo-compressed joint with the fibrous reinforcement and the matrix, the base being configured so as to be extracted and replaced.

[0023] The invention further relates to a mold for molding a part in composite material with fiber reinforcement densified by a matrix and equipped with at least one seal for a turbomachine, the mold comprising a first part having a first impression and a second part having a second impression forming a space intended to receive a preform forming the fiber reinforcement and at least one cavity having a complementary shape with a portion of the seal. Brief description of the figures

[0024] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which: - Fig. 1 illustrates an axial section of an example of a turbomachine according to the prior art;

[0025] - Figure 2 schematically represents, in axial section, an example assembly between two parts of a turbomachine, one of the parts being made of a composite material and being equipped with an integrated flexible element according to the invention;

[0026] - Figure 3 is a flowchart of a manufacturing process for a part made of composite material with fiber reinforcement densified by a matrix;

[0027] - Figure 4 is a cross-sectional view of a manufacturing step of a composite material part intended to be installed in a turbomachine according to the invention;

[0028] - Figure 5 is a cross-sectional view of another manufacturing step of a composite material part intended to be installed in a turbomachine according to the invention;

[0029] - Figure 6 is a cross-sectional view of another manufacturing step of a composite material part intended to be installed in a turbomachine according to the invention;

[0030] - Figure [Fig. 7] is a cross-sectional view of an embodiment of an element flexible integrated into a part made of composite material according to the invention;

[0031] - Figure [Fig. 8] is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention;

[0032] - Figure [Fig. 9] is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention;

[0033] - Figure 10 is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention;

[0034] - Figure 11 is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention;

[0035] - Figure 12 is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention;

[0036] - Figure 13 is a cross-sectional view of another embodiment of a element integrated into a part made of composite material according to the invention.

[0037] - Figure 14 is a cross-sectional view of another embodiment of less an element integrated into a part made of composite material according to the invention. Detailed description of the invention

[0038] The [Fig. 1] has been described above.

[0039] In this description, identical or substantially identical elements and / or elements with the same functions are represented by the same numerical references.

[0040] Figure 2 shows a part 1 made of composite material equipped with a flexible element. By "flexible element," we mean an element that has a lower hardness than the composite material of part 1. In the following description, the flexible element advantageously includes a seal 2, which is not limiting. The seal shown in Figure 2 includes a sealing gasket, but the seal could be another type of gasket.

[0041] The sealing gasket 2 is disposed on the surface or around the periphery of the composite material part. Several sealing gaskets may be disposed on the surface or around the periphery. In the case of several sealing gaskets, these are arranged regularly around the surface or the periphery.

[0042] Advantageously, the composite material part 1 is made from a densified fibrous reinforcement in a matrix.

[0043] Advantageously, the composite material part 1 is intended to be mounted in an aircraft turbomachine (not shown). The aircraft comprises, for example, a fuselage and two wings extending on either side of the fuselage relative to the fuselage axis. Each wing can carry at least one turbomachine.

[0044] The turbomachine generally comprises, from upstream to downstream, a compressor assembly, a combustion chamber and a turbine assembly which preferably forms a gas generator.

[0045] The turbomachine 1 can be a turbojet or a turboprop.

[0046] The turbomachine 1 may include at least one rotating element, which may be a propeller or a fan. The propeller may be shrouded or unshrouded. The propeller is advantageously mounted upstream of the compressor assembly.

[0047] The composite material part 1 illustrated in [Fig.2] is, by no means limiting, a turbomachine hood which is preferably mounted downstream of the propeller.

[0048] The hood is advantageously annular and centered on a longitudinal axis X, which is here the axis of rotation of the turbomachine rotors. As shown, the hood is fixed to a ferrule 3, which is advantageously annular and centered on the longitudinal axis X. The fastening is advantageously achieved by means of fasteners 4. The fasteners 4 can be threaded elements such as screws and bolts. The hood is equipped with a seal 2, which is integrated into the composite material and extends outward from a radially internal surface 5 of the hood. The seal 2 is advantageously arranged radially between the hood and the ferrule 3 and bears against the ferrule 3. The seal 2 is compressed when the hood is tensioned by the fasteners 4 on the ferrule 3, thus ensuring a seal.

[0049] Alternatively, the sealing gasket 2 is mounted on a radially external surface 6 of the hood, and optionally the ferrule 3 is mounted radially outside the hood. According to yet another alternative, the sealing gasket 2 could extend from several surfaces of the composite material part, and in this case, the hood. According to yet another alternative, one or more sealing gaskets could extend from a side face or edge of the composite material part.

[0050] In this embodiment, the ferrule 3 includes a recess 7 which is formed in a radially external surface 8 of the ferrule 3. At least a portion of the sealing gasket is received in the recess 7.

[0051] Advantageously, the fibrous reinforcement of part 1 comprises inorganic fibers. For example, the fibers include mineral fibers, metallic fibers, thermoplastic polymers, thermosetting polymers, or a mixture of these fibers. The fibers of the fibrous reinforcement are selected, for example, from the group comprising Kevlar® fibers, glass fibers, and carbon fibers. Generally, these fibers have a fiber count between 100 tex and 2500 tex. The fibers may be continuous long fibers arranged in the form of stacked unidirectional (UD) webs or two-dimensional (2D) or three-dimensional (3D) weaves. The fibers may also be partially or entirely composed of discontinuous long fibers in the form of mats or batts of fibrous pieces or pieces of fabric. The fibers may also be short fibers.

[0052] The matrix or resin allows the fibrous reinforcement to be densified and bound in order to obtain the final rigid composite part. The terms "matrices" and "resins" The terms "resin" and "matrix" are used interchangeably in this description. The matrix may be selected from thermosetting, thermoplastic, and vitrimer polymers. Examples of thermoplastic resins include polyamide, polyetheretherketone, polyetherketoneketone, poly(phenylene sulfide), and polyaryletherketone. Thermosetting resins include, for example, epoxides and polyimides.

[0053] According to one embodiment, the matrix comprises particle fillers so as to enhance the mechanical properties of the composite material part, such as its mechanical strength. The particles may be microscopic, submicroscopic, or nanoscopic. For example, the matrix may be filled with glass microbeads, hollow microspheres, glass, thermoplastic nanonodules, carbon nanotubes, or graphene particles. The particles may have various shapes, such as spherical, filamentous, etc.

[0054] According to one embodiment, the fibers are advantageously pre-impregnated with the polymer matrix.

[0055] The sealing gasket 2 is advantageously made of a material different from the material of the composite part. The material of the sealing gasket 2 may include an elastomer, a rubber, a silicone, etc. The material of the sealing gasket has a resistance to a predetermined temperature higher than the thermocompression temperature of the composite material. For example, for a panel made of epoxy matrix composite consolidated at 180°C, the sealing gasket 2 may be made from rubber, silicones, or fluorocarbons.

[0056] Advantageously, the sealing gasket 2 has a hardness ranging from 10 Shore I to 200 Shore B (measured according to JIS K6253). Conversely, the hardness of the composite material can range from 20 to 80 Barcol. The hardness or flexibility of the sealing gasket 2 enables it to perform the sealing function with another part, in this case the ferrule 3. The gasket may also include fibers such as glass, polyester, polyethylene, Kevlar®, etc., in its internal structure, giving it higher tensile strength while still allowing it flexibility.

[0057] We will now describe in detail the process 100 for manufacturing such a part from composite material. This process is shown in [Fig.3].

[0058] The process 100 includes a step 110 of supplying a preform 9 forming the fibrous reinforcement. The preform 9 is formed, for example, by 2D or 3D weaving. Alternatively, the preform 9 is obtained by draping several layers of fibers.

[0059] The process 100 includes a step 120 of supplying at least one seal 2. In the remainder of the process description, the seal 2 includes, but is not limited to, a sealing gasket. The sealing gasket 2 is produced, for example, by casting, by injection, or even by extrusion. Its construction may involve bonding operations (joining between ends to form an annular or closed joint).

[0060] The process 100 includes a step of placing a preform 9 in a mold 50. Advantageously, the preform 9 forms the fibrous reinforcement.

[0061] According to one embodiment, the mold 50 comprises a first part 50a and a second part 50b. The first part 50a of the mold 50 advantageously comprises the first cavity 51 intended to form a first (internal) face of the preform 9. The second part 50b of the mold 50 advantageously comprises a second cavity 52 which opens onto an internal surface of the second part 50b. Advantageously, the preform 9 can be installed in the first cavity 51 or alternatively in the second cavity 52 of the mold.

[0062] In the present example, the second cavity 52 is oriented towards the preform 9 when the latter is installed in the first cavity 51. When the preform 9 is installed in the second cavity 52, the first cavity is advantageously positioned opposite the preform 9. The second cavity 52 has a complementary shape with a second (external) surface of the preform 9. The first cavity 51 and the second cavity 52 form a receiving space for the preform 9.

[0063] Advantageously, the second part 50b of the mold 50 is movable relative to the first part 50a, for example, between an open position and a closed position. The first part 50a moves in a non-limiting manner along at least one translation.

[0064] According to one embodiment, the mold 50 comprises at least one cavity 53 configured to receive at least part of a sealing gasket 2. The mold 50 may comprise several cavities 53 spaced apart. Advantageously, each cavity 53 opens into the second impression 52 of the second part 50b of the mold 50. Each cavity 53 has a complementary shape with at least part of the sealing gasket 2. Optionally, each cavity 53 is machined in the second part 50b of the mold 50. Alternatively, each cavity 53 is machined in the first part 50a of the mold. Each cavity 53 advantageously opens into the first cavity 51. According to yet another alternative, cavities are machined in the first part and the second part 50b of the mold 50, and preferably on either side of the boundary separating the first and second parts.

[0065] According to another embodiment, the cavity or each cavity 53 is obtained simultaneously during the manufacture of at least one of the first and second parts 50a, 50b of the mold 50 or of each of the first and second parts 50a, 50b of the mold 50. The first part 50a or the second part 50b of the mold 50 can be made by any technique known from the prior art, for example, casting, machining, additive manufacturing, forging, etc.

[0066] According to another embodiment, each first part and / or second part having one or more cavities 53, comprises two sub-parts which are assembled together to form the first part 50a or the second part 50b.

[0067] According to one embodiment, the mold includes at least one insert provided with the or each sealing gasket 2. The insert is fixed on the first part and / or the second part 50b of the mold 50.

[0068] The method 100 further comprises a step of placing at least a portion of the seal into a cavity 53 of the mold by complementary shape. Advantageously, but not limitingly, at least a portion of each sealing gasket 2 is placed by complementary shape of at least a portion into the cavity 53 of the mold, and preferably, into the cavity 53 formed in the second part 50b of the mold 50. In [Fig. 4], the cavity 53 has, without limitation, a circular cross-section. The cross-section or shape of the cavity 53 may, of course, be different.

[0069] The sealing gasket 2 advantageously, but not exclusively, comprises at least one functional portion 2a and at least one base 2b. In the example of [Fig. 4], the functional portion 2a has a circular cross-section and the base 2b has a straight cross-section, parallel to the radially internal surface of the part 1. The functional portion 2a is installed by complementary shape in the circular cavity 53. In other words, the cavity 53 has the same shape or cross-section as the functional portion 2a.

[0070] Optionally, each cavity 53 may have dimensions locally larger than the volume required to house the functional portion 2a. This may allow the passage of external tools. Optionally, each cavity 53 may have dimensions, at least locally, very slightly (on the order of 3%) smaller than the nominal volume of the functional portion 2a, so as to allow the sealing gasket 2 to be pinched at these points and thus be held with the tooling portion in which each cavity 53 is formed until the molding of the part 1.

[0071] The base 2b is advantageously integrated into the preform 9. The sealing gasket 2 has a shape in b or p in this non-limiting example. Of course, the sealing gasket 2 can have any shape. The hardness of the sealing gasket 2 facilitates the preferential insertion of the functional portion 2a into the cavity 53 of the mold 50. Furthermore, the hardness of the sealing gasket 2 ensures that it remains in the cavity 53.

[0072] The process advantageously includes a step 150 of closing the mold 50 so as to apply the sealing gasket 2 to a surface of the preform 9. Advantageously, but not exclusively, the closing step 150 includes a substep of moving a portion of the mold, preferably the second portion 50b of the mold 50, so as to apply the sealing gasket 2 to the preform 9. The movement substep is shown in [Fig. 4]. Advantageously, the movement is carried out in a vertical direction towards the preform 9.

[0073] The process 100 advantageously comprises a thermocompression step 160 of the preform 9 and the sealing gasket 2. During the thermocompression step, shown in [Fig. 5], a predetermined heat and a predetermined force are applied to the mold 50. For example, a temperature of 100°C to 180°C can be applied to the mold 50, allowing the consolidation of the composite material comprising the preform 9. For example, a force of 50,000 N to 5,000,000 N can be applied to the first and second parts 50a, 50b of the mold 50 over a surface area of ​​1 m², capable of producing a pressure of 0.5 MPa to 50 MPa on the preform 9. At the end of the relative movement phase between the tooling parts, the mold 50 is advantageously in the closed position, i.e., the contours peripherals of the first and second parts 50a and 50b press against each other at the level of their joint plane (or separation plane).This allows the preform 9 to be densified and the sealing gasket 2 to be fixed to the preform 9 in a single step. The finishing of the preform 9 during the closing of the mold 50 allows at least a portion of the sealing gasket 2 to be embedded in the preform 9. Pressurizing the sealing gasket 2 also advantageously makes the cavity 53 of the mold 50 watertight. The resin cannot enter the cavity 53.

[0074] Prior to the thermocompression step 160, the process 100 optionally includes a step of injecting a polymeric matrix into the preform 9, which is installed in the second cavity 52 of the second part 50b of the mold 50. The matrix is ​​injected in liquid form to impregnate and bind the fibers and the sealing gasket 2 together until the matrix hardens.

[0075] Preferably, the fibers are pre-impregnated. The preform 9 with the pre-impregnated fibers is compressed when the mold 50 is closed.

[0076] The process 100 advantageously comprises an opening step 170 of the mold 50, which is shown in [Fig. 6]. During this opening step 170, the second part 50b of the mold 50 advantageously moves vertically in the opposite direction to the closing step 150. The sealing gasket 2, which is embedded in the composite part, automatically disengages from the cavity 53 of the mold 50.

[0077] As described previously, the sealing gasket 2 can have any type of shape, as illustrated in Figures 7 to 14. Advantageously, but not limitingly, the functional portion 2a of the sealing gasket 2 ensures sealing with an adjacent part. The shape of the functional portion 2a can to be adapted according to the need. The functional portion 2a can advantageously have a cylindrical, X-shaped, V-shaped, double-lip shape, etc.

[0078] Advantageously, but not exclusively, the base 2b allows anchoring or embedding in the preform 9. The shape of the base 2b is also dependent on the need and allows for its interchangeability. In particular, the shape of the base 2b may allow for its removal and replacement with a new sealing gasket 2. The base 2b may, for example, have a trapezoidal, rectilinear, etc., cross-section.

[0079] Replacing a new seal 2 could be accomplished by extracting the seal from the cavity 53 and inserting a new seal into the cavity 53 in an inverted trapezoidal shape. Insertion is possible due to the significant deformation capacity of the seal in this area.

[0080] In [Fig. 7], the functional portion 2a has a circular cross-section. The functional portion 2a of the sealing gasket 2 projects from the densified preform 9. The base 2b has a substantially trapezoidal cross-section. The base 2b is integrated into the densified preform 9.

[0081] In [Fig. 8], the functional portion 2a is straight and inclined relative to the external surface of the preform 9 (or the composite part). The angle of the functional portion can be between 30° and 60°. The functional portion 2a is, for example, in the form of a lip. The base 2b is straight. The direction of the base is advantageously parallel to the external surface of the preform 9.

[0082] On [Fig.9], the functional portion 2a has a V-shaped section which extends outward from the surface of the preform 9. The base 2b has a trapezoidal cross-section.

[0083] In [Fig. 10], the functional portion 2a has a circular cross-section. The base 2b has an arrow-shaped, harpoon-shaped, or triangular cross-section. The arrow is optionally oriented in a direction opposite to the surface of the preform 9.

[0084] In [Fig. 11] and [Fig. 12], the functional portion 2a has a circular cross-section. The base 2b has an arrow-shaped, harpoon-shaped, or triangular cross-section. The arrow is optionally oriented in a direction opposite to the surface of the preform 9. In this embodiment, the sealing gasket 2 has through holes 10 on both sides of the base 2b. The holes 10 are preferably aligned in the same direction and transversely to the direction of the base 2b. During pressurization in the thermocompression step, the holes 10 will be filled by the die.

[0085] In [Fig. 13], the sealing gasket 2 is disposed on a lateral surface of the preform 9. The functional portion 2a has a triangular cross-section and Base 2b is straight. The direction of base 2b is parallel to the external surface of preform 9.

[0086] In [Fig. 14], the sealing gasket 2 comprises several functional portions 2a and several bases 2b. Advantageously, the bases 2b are connected to each other. A functional portion 2a' extends from the outer surface of the preform 9, and a functional portion 2a” projects from the lateral surface of the preform 9. The functional portion 2a' has a circular cross-section. The functional portion 2a'' has a triangular cross-section. A base 2b extends into the preform and transversely across its outer surface 9. Straight sections connect the functional portions 2a', 2a” and the base 2b. The straight sections cover at least a portion of the outer and lateral surfaces of the preform 9.

[0087] Of course, other combinations of shapes of functional portions 2a and bases 2b can be envisaged.

[0088] In this way, with such a manufacturing process, we obtain a part made of composite material with one or more seals 2 made of flexible material integrated(s) into the monolithic composite material part.

Claims

Demands

1. A method for manufacturing (100) a part (1) made of matrix-densified fiber-reinforced composite material for a turbomachine, equipped with at least one seal (2) which is integrated and extends outward from a surface of the part, the method comprising the following steps: - supplying (110) a preform (9) forming the fiber reinforcement comprising inorganic fibers, - supplying (120) at least one seal (2), - placing (130) the preform (9) in a first cavity (51) of a mold (50), - placing (140) at least a portion of the seal (2) in a cavity (53) of the mold (50) by complementary shape, the seal (2) being made of a material different from the composite material of the part made of composite material, - closing (150) the mold (50) so as to apply the seal (2) to a surface of the preform (9),- thermocompression (160) of the preform (9) and the seal (2) so as to obtain the part in composite material with the seal (2) integrated.

2. Manufacturing method (100) according to the preceding claim, characterized in that the seal (2) comprises at least one functional portion (2a, 2a', 2a”) intended to be installed in the cavity (53) and enabling sealing, and at least one base (2b) intended to be integrated into the densified preform (9).

3. Manufacturing method (100) according to claim 1 or 2, characterized in that the fibrous reinforcement comprises fibers selected from the group comprising Kevlar® fibers, glass fibers, carbon fibers.

4. Manufacturing method (100) according to any one of claims 1 to 3, characterized in that it comprises a step of injecting a polymeric matrix into the preform (9).

5. A manufacturing method (100) according to any one of claims 1 to 4, characterized in that the fibers of the preform (9) are pre-impregnated.

6. Manufacturing method (100) according to any one of claims 1 to 5, characterized in that the matrix is ​​selected from thermosets, thermoplastics and vitrimers.

7. A manufacturing method (100) according to any one of the preceding claims, characterized in that the matrix comprises a predetermined charge of particles.

8. A manufacturing method (100) according to any one of the preceding claims, characterized in that the seal (2) is made of an elastomer, a rubber or a silicone.

9. A manufacturing method (100) according to any one of claims 2 to 8, characterized in that the functional portion (2a, 2a', 2a”) comprises a circular, V-shaped, arrow-shaped, lip-shaped, triangular section.

10. A manufacturing method (100) according to any one of claims 2 to 9, characterized in that the base (2b) has a straight, arrow-shaped, triangular or trapezoidal cross-section.

11. Manufacturing method (100) according to the preceding claim, characterized in that the base (2b) has holes (10).

12. Composite material part obtained by the manufacturing process (100) according to any one of claims 1 to 11, characterized in that the composite material part comprises the fibrous reinforcement densified by the matrix and at least one thermo-compressed joint (2) with the fibrous reinforcement and the matrix, the base (2b) being configured so as to be extracted and replaced.

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