Improved method of manufacturing a component by additive manufacturing

Abstract

The invention relates to a method for manufacturing an aeronautical part by additive manufacturing, the part to be manufactured extending around a central axis (X) and comprising at least two walls (20, 42) which are angled with respect to each other and connected to each other by at least one connecting section (S) which is comprised in a connecting plane (R) perpendicular to the central axis (X), the method comprising: - providing a digital model (1) of the part to be manufactured, - orienting the digital model (1) with respect to a vertical build direction (Z) of the part so that the central axis (X) of the part has an angle β with respect to the build direction (Z) of between 0.1° and 1°, preferably between 0.3° and 0.8°, - manufacturing the part by additive manufacturing according to the digital model (1) obtained in the orientation step.

Description

Technical Field

[0001] This invention relates to a method for manufacturing components using additive manufacturing, which can particularly improve the surface condition of the resulting components. Such additive manufacturing methods are particularly suitable for manufacturing complex components specifically designed for use in the aerospace field. Background Technology

[0002] Additive manufacturing methods are now known, particularly in the aerospace field, for producing certain parts with fine or complex geometries.

[0003] A common example of additive manufacturing is the use of high-energy beams to melt or sinter powder particles. Among these high-energy beams, laser beams and electron beams are particularly noteworthy.

[0004] Selective laser melting (SLM), also known as the "laser beam melting" (LBM) method, refers to a method characterized by the following key features, see reference [link to relevant documentation]. Figure 9 The Figure 9 The illustration shows a conventional apparatus for manufacturing parts by selectively melting or selectively sintering a powder bed using a laser beam.

[0005] For example, a first layer 110a of material powder is deposited on a construction plate 121 using a paving tool 120 (e.g., a roller or scraper). This plate may be a separate plate or on a solid support, part of another component, or a support grid used to facilitate the construction of certain components.

[0006] The powder is poured from the supply tray 122 during the forward movement of the roller 120, and then scraped and possibly slightly compacted during one (or more) return movements of the roller 120. The powder consists of particles 111. Excess powder is collected in a recovery bin 123 adjacent to the construction bin 124, in which the construction plate 121 moves vertically.

[0007] A laser beam generator 130 and a steering system 132 are also used, which can guide the laser beam 131 to any area of ​​the construction plate 121 to scan any area of ​​the previously deposited powder layer. The shaping of the laser beam 131 and the variation of its diameter on the focal plane are accomplished by a beam expander or focusing system 133 and a beam expander 134, which together constitute the optical system.

[0008] Subsequently, by scanning with laser beam 131, the region of the first powder layer 110a is brought to a temperature above the melting point of the powder.

[0009] Such additive manufacturing methods can use any high-energy beam instead of a laser beam 131, particularly an electron beam, as long as the energy of the beam is sufficient to melt the powder particles and a portion of the material on which the particles are resting.

[0010] For example, this scanning of the laser beam is performed by a galvanometer head belonging to the control system 132. This control system, for example, includes at least one directional mirror 135 on which the laser beam 131 is reflected before reaching the powder layer. Each point on the surface of the directional mirror 135 is always at the same height relative to a focusing lens included in the focusing system 134. The angular position of the mirror is controlled by the galvanometer head such that the laser beam scans over at least one region of the first powder layer, and thus follows a pre-established contour of the part. For this purpose, the galvanometer head is controlled based on information contained in a database of computer tools used for computer-aided design and manufacture of the part to be manufactured.

[0011] Therefore, the powder particles 111 in this region of the first layer 100a are melted and formed into a first integral element 112a, which is then fixed to the construction plate 121. During this stage, several separate regions of the first layer may also be scanned with a laser beam to form several separate first elements 120a after the material has melted and solidified.

[0012] The structural plate 121 reduces the height (20 μm to 100 μm, and typically 30 μm to 50 μm) corresponding to the thickness of the first powder layer 110a.

[0013] Then, a second powder layer 110b is deposited on the first layer 110a and on the first integral or solidified element 112a, and then... Figure 9 In the case shown, by being exposed to the laser beam 131, a region of the second layer 110b located partially or completely above the first integral or solidified element 112a is heated, causing the powder particles in that region of the second layer 110b to melt together with at least a portion of the element 112a, forming the second integral or solidified element 112b. Figure 9 In the case shown, the components 112a and 112b are assembled into a single block.

[0014] Therefore, this type of additive manufacturing technology ensures good control over the geometry of the parts to be manufactured and can produce extremely complex parts.

[0015] However, in the production of components with complex geometries, particularly cylindrical components such as bearing supports, some walls of the component are angled relative to each other and connect to each other at junction areas, for example, curved into arcs. Although the junction sections between these walls are thin in the radial direction, the surface occupied by these sections can be large, as long as they can extend over the entire circumference of the component. However, when the layer that allows these walls to connect is melted, the junction sections end at the “downskin” structure, that is, temporarily in a severely cantilevered state, or without any support other than the large amount of uncured powder below, and therefore at risk of settling or collapsing. This “downskin” structure also involves parameters that differ from those used for the preceding layers, known as the standard core layer.

[0016] Therefore, during delamination, the presence of this settlement, involving irregularities and extending throughout the connecting section, creates a "wall" effect that causes slight vibrations in the scraper as it passes through. This vibration causes jumps on adjacent surfaces of the component, particularly on the outer layer, thus resulting in surface defects. In the case of a layer thickness of 40 μm, these defects, characterized by three-dimensional optical microscopy, can cause jumps reaching heights of approximately 250 μm.

[0017] These defects can be problematic because they are difficult to remove, especially on the complex surfaces of the components as described above. Furthermore, they can be sources of localized stress concentration, which can be detrimental from the perspective of determining component dimensions.

[0018] Therefore, there is a real need for a method of manufacturing parts by additive manufacturing that can overcome at least some of the above-mentioned disadvantages and thus improve the surface condition of the resulting parts. Summary of the Invention

[0019] This invention relates to a method for manufacturing an aerospace component by additive manufacturing, the component to be manufactured extending about a central axis and including at least two walls angled to each other and connected to each other by at least one connecting section comprising a connecting plane perpendicular to the central axis, the method comprising:

[0020] - Provide a digital model of the part to be manufactured.

[0021] - A digital model oriented relative to the vertical construction direction of the component, such that the central axis of the component has an angle β between 0.1° and 1°, preferably between 0.3° and 0.8°, relative to the construction direction.

[0022] - The component is manufactured using additive manufacturing based on the digital model obtained in the orientation step.

[0023] In this invention, the construction direction refers to the direction in which the component is built, that is, the direction in which the powder layers or manufacturing layers are stacked on top of each other. For example, when a component is manufactured on a construction plate, the construction direction corresponds to a direction orthogonal to the construction plate, and is therefore perpendicular.

[0024] Furthermore, in this specification, the terms "axial," "radial," "inner," "outer," "circumferential," and their derivatives are defined with respect to the central axis of a component. The terms "above" and "below" are understood according to the construction direction.

[0025] All components constituting the part, particularly the two walls at an angle to each other, are integrally manufactured and made from the same material through additive manufacturing. The "connection section" between the two walls at an angle to each other should be understood as the first layer of material that can be connected between the two walls during the additive manufacturing process.

[0026] In other words, at layer n in the additive manufacturing process, the two walls are separated by a thin gap. The next layer n+1 can deposit and incorporate material that fills this gap and thus connects the two walls together. Therefore, the connecting section is the portion of layer n+1 that can fill the gap present at layer n. When the connecting section bends, it thus extends radially along a dimension corresponding to the width of the gap and circumferentially around a central axis.

[0027] Once the connecting section is formed at layer n+1, a continuous layer specifically supported on the connecting section is formed integrally to form a connecting area between the two walls. However, apart from the volume of the uncured powder below, the first layer (that is, the connecting section) that can connect these walls does not rest on any solid layer.

[0028] According to the invention, the fact that the central axis of the component is tilted relative to the construction direction by an angle β during the model orientation step also allows the connecting plane, including the connecting section, to be tilted by the same angle β. The tilt angle β defined above is sufficient to allow the connecting section to be formed not in one layer, but in several layers; in other words, formed during multiple passes of the scraper. Preferably, the number of layers required to form the connecting section is between 10 and 40.

[0029] The fact that connecting sections are formed in several layers limits cantilever surfaces at each of these layers, or limits the unsupported volume of uncured powder below, thus limiting settling. Therefore, for each channel of the scraper required to form the connecting sections, the scraper will encounter fewer cantilever surfaces, thus limiting vibrations generated on the scraper. Therefore, this tilt can limit or even eliminate jumps present on the final part, thereby improving the surface condition of the final part.

[0030] In some embodiments, the component to be manufactured is axially symmetrical about a central axis.

[0031] In some embodiments, the connecting segment extends along an arc centered on the central axis.

[0032] Given this shape, most of the components constituting the part, especially the walls that are angled relative to each other, are also axially symmetrical. Therefore, the connecting sections between these inclined walls have a circular shape around the central axis of the part. During manufacturing, the inclination of the part can form these connecting sections over several layers; in other words, the circular gap existing between the two walls is closed in several channels of the scraper.

[0033] In some embodiments, the step of orienting the digital model includes adding an inclined wedge to the digital model between a horizontal construction plane and a plane including the lower end of the part to be manufactured, such that the central axis is tilted at an angle β relative to the vertical construction direction.

[0034] The construction plane is a plane orthogonal to the construction direction and substantially parallel to the construction plate. By tilting the plane, including the lower end of the part to be manufactured, relative to the horizontal construction plane using a tilting wedge, the entire part can be tilted by an angle β without changing its geometry.

[0035] In some embodiments, during additive manufacturing, the tilting wedge is made of the same material as the part to be manufactured.

[0036] In other words, a wedge is a piece of material added to the lower end of a component that orients the component's central axis at an angle β relative to the construction direction during manufacturing. Therefore, the surface condition of the final component can be improved by simply adding material below it without altering its overall geometry.

[0037] In some embodiments, the inclined wedge is configured such that, in a plane including the lower end of the part to be manufactured, the first radial end of the part to be manufactured has a height ε relative to a second radial end opposite to the first radial end.

[0038] The height ε that allows the component to tilt at an angle β is very low, preferably from a few tenths of a millimeter to 20 millimeters. Therefore, the surface condition of the final component can be improved by simply adding a small amount of material below the component, thereby particularly limiting the resulting costs.

[0039] In some embodiments, the component to be manufactured includes a basic cylindrical housing, the housing including a lower end and first and second radial ends, the first and second radial ends being radially opposite to each other.

[0040] "Basic cylindrical" should be understood as an inner shell having a cylindrical or cylinder-like shape despite the presence of local irregularities (e.g., local thinning of its cross-section) or fastening devices. Therefore, the component can be tilted at an angle β by simply raising the radial end of the outer shell by a height ε.

[0041] In some embodiments, ε = D × arctan(β), where D is the diameter of the housing of the part to be manufactured.

[0042] Therefore, for a given value D of the shell diameter and thus the component diameter, the height value ε required to obtain a predetermined inclination angle β can be determined. It will be noted that the angle β can be predetermined based on the desired number of layers required to connect two walls at an angle to each other.

[0043] In some embodiments, the method includes a step of removing the tilting wedge after the manufacturing step, wherein the tilting wedge used to tilt the part during the manufacturing process of the part is removed to obtain the final part.

[0044] The tilting wedge is therefore a temporary change in the geometry of the part, used only to tilt the central axis of the part during manufacturing. Thus, once the tilting wedge is removed, the resulting part has the desired geometry and the surface condition of the final part is improved.

[0045] In some embodiments, the tilted wedge is removed by machining.

[0046] In other words, the radial end of the lower part of the obtained component is machined at a height corresponding to the height ε to remove the portion corresponding to the inclined wedge, or in other words, to flatten the lower end of the component. Thus, after machining, when the lower end of the component is placed on a horizontal support, the central axis of the component is vertical and no longer inclined.

[0047] In some embodiments, the component to be manufactured is a turbojet engine bearing support. Attached Figure Description

[0048] The invention and its advantages will be better understood after reading the following detailed description of various embodiments of the invention given by way of non-limiting examples. Reference is made to the accompanying drawings, on which:

[0049] Figure 1 This is a side view of a first example of a digital model of a part to be manufactured using the method of the present invention.

[0050] Figure 2 It is along section plane A Figure 1 Cross-sectional view of the model.

[0051] Figure 3 It shows Figure 2A detailed cross-sectional view illustrating the connection section between the two inclined walls of the part to be manufactured.

[0052] Figures 4A and 4B show two continuous layers with additive manufacturing. Figure 3 Top view of the component.

[0053] Figure 5 The steps of locating the digital model of the component are shown in a simplified manner. Figure 1 The model,

[0054] Figures 6A to 6D, in top views of the component, show the connection section formed between two inclined walls at the continuous layer of additive manufacturing.

[0055] Figure 7 This is a diagram illustrating the different steps of the method of the present invention.

[0056] Figure 8 This is a side view of a second example of a digital model of a part to be manufactured using the method of the present invention.

[0057] Figure 9 An overview of an additive manufacturing apparatus that selectively melts a powder bed is shown. Detailed Implementation

[0058] Please refer to the rest of the instruction manual. Figures 1 to 7 The first example of an embodiment of the present invention is explained below. It will be noted that in the remainder of this description, the construction direction Z is the direction in which the component is constructed, that is, the direction in which powder layers or manufacturing layers are stacked on top of each other. Therefore, the construction direction Z is orthogonal to the construction plane P, which specifically includes the construction plate on which the component is to be manufactured. Furthermore, in the remainder of the specification, the terms “axial,” “radial,” “lateral,” “inner,” “outer,” “above,” or “below,” and their derivatives, are defined with respect to the central axis X of the component 1 to be manufactured.

[0059] In this example, the component to be manufactured is a bearing support intended for use in a turbine engine, specifically a bearing support at the engine exhaust cylinder. The turbine output bearing support can particularly support the bearings of the rotating shaft that connects the high-pressure compressor and the high-pressure turbine. Figure 1 A side view of the component is shown. More specifically, Figure 1 This is a side view of the digital model 1 of the part to be manufactured. For convenience, the digital model of the part will be simply referred to as "part 1" in the remainder of the specification. Part 1 is symmetrical about the central axis X. The construction plane P corresponds to the horizontal plane and represents the construction plate on which part 1 is to be manufactured.

[0060] Section plane A includes the central axis X and is perpendicular to the construction plane P. Figure 2 It shows Figure 1 The sectional side view of component 1 shown along section plane A illustrates the different elements constituting component 1. Component 1 specifically includes a cylindrical or substantially cylindrical housing 10. Plane B includes the lower end 12 of the housing 10.

[0061] A truncated conical flange 20 is fastened to the inner side of the housing 10. The flange 20 is configured to carry multiple support portions 30, 40, and 50 on the inner side of the housing, each support portion having a cylindrical inner surface. The diameter of each of these cylindrical inner surfaces is different from the others. These support portions 30, 40, and 50 are used to support rolling bearings, which guide the rotation of the turbojet engine shaft.

[0062] Each of these support portions 30, 40, and 50 is carried by the flange 20 via connecting portions 32, 42, and 52, respectively. It will be noted that each of these elements (flange 20, support portions 30, 40, and 50, connecting portions 32, 42, and 52) is symmetrical about the central axis X-axis. Each connecting portion 32, 42, and 52 connects to the inner surface of the flange 20 at a connecting area, which is formed by... Figure 2 The circle is positioned within the circle.

[0063] The wall of flange 20 forms an angle with respect to the central axis X, for example, between 40° and 60°. The walls of connecting portions 32, 42, and 52 also form an angle with respect to the central axis X, said angle being opposite to the angle of the wall of flange 20 and, for example, between 40° and 60°. Therefore, each connecting portion 32, 42, and 52 forms an angle with respect to the wall of flange 20.

[0064] Figure 3 express Figure 2 A detailed view of the component at the connection between the connecting portion 42 and the flange 20. The hollow fastening cylinder 22, which secures component 1 to the turbojet engine components, can also be seen. Figure 3 The view shows component 1 during the additive manufacturing process, immediately after the powder layer depositing and melting to form the connecting section S. The connecting section S is a first material layer that fills the gap I between the two walls in the previous layer (Fig. 4A) and forms a connection between the connecting portion 42 and the flange 20. The connecting section S is included in the connecting plane R perpendicular to the central axis X. Furthermore, the connecting section S extends in an arc around the central axis X.

[0065] Figure 4A shows a top view of the section Sn formed between the connecting portion 42 and the flange 20 at step n, that is, at layer n of the additive manufacturing process, just before the material that can connect the connecting portion 42 and the flange 20. In other words, at this stage, there is no suitable connecting section yet, and the connecting portion 42 and the flange 20 are radially spaced by a thin gap I between a few hundredths of a millimeter and about 1 mm, for example, 0.4 mm.

[0066] Figure 4B shows the connection segment Sn+1 between the connecting portion 42 and the flange 20, formed at step n+1, i.e., at layer n+1 of the additive manufacturing process. Without model orientation, a single layer (layer n+1) is therefore required to close the gap I present between the connecting portion 42 and the flange 20 at layer n. According to this configuration, the material that can close this gap I is not formed on any existing layer except for the unmelted powder below. In other words, none of the materials of the layers formed in the previous steps can support the connecting segment Sn+1 during its formation. Although the connecting segment Sn+1 is formed of the same material as the connecting portion 42 and the flange 20, the shaded line representing the connecting segment Sn+1 in Figure 4B differs from the shaded lines of the walls 20 and 42, indicating localized settlement in this segment.

[0067] The method according to the present invention described below overcomes this drawback.

[0068] The first step can provide a digital model of the part 1 to be manufactured (step S1), as described above. Then, the step of orienting the digital model is performed (step S2).

[0069] In this step, a wedge 80 is added to the digital model so that it is positioned between the horizontal construction plane P and the plane B, which includes the lower end 12 of component 1 (more precisely, the lower end 12 of housing 10), on which component 1 is manufactured. In other words, during manufacturing, the lower end 12 of housing 10 of component 1 does not rest directly on the construction plane P, taking into account the presence of the wedge 80 inserted between plane B and construction plane P.

[0070] The inclined wedge 80 includes a first end 81 for horizontal resting on the construction plane P and a second end 82 at an angle relative to the first end 81. The lower end 12 of the housing 10 rests on the second end 82 of the inclined wedge 80, such that the component 1 thus has an inclination relative to the construction plane P. Furthermore, the housing 10 has a cylindrical shape with an axis X, and the inclined wedge 80 further has a cylindrical shape with an axis Z, its top (second end 82) inclined relative to its bottom (first end 81).

[0071] According to the side view of component 1 ( Figure 5 The inclined wedge 80 has the shape of an inclined ramp. Considering this construction, the presence of the inclined wedge 80 causes the plane B of the lower end 12 of the housing 10, including component 1, to be inclined at an angle β relative to the construction plane P. Therefore, the central axis X is also inclined at an angle β relative to the construction direction Z.

[0072] According to this configuration, in the plane B including the lower end 12, the first radial end 14 of component 1 is raised by a height ε relative to the second radial end 16, the second radial end 16 being radially opposite to the first radial end 14, such that ε = D × arctan(β), where D is the diameter of the housing 10, and specifically the diameter of the lower end 12 of the component 1 to be manufactured. The tilt angle β and the height ε can vary depending on the diameter D of the component 1 to be manufactured. For example, for a diameter D of 400 mm, ε can include between 0.5 and 5 mm, and β can include between 0.1° and 1°.

[0073] After the inclined wedge 80 is added to the digital model, part 1 is manufactured by additive manufacturing (step S3). More specifically, the inclined wedge 80 is initially manufactured layer by layer on a construction plate extending along the construction plane P, and part 1 is manufactured in the continuity of the inclined wedge 80. In other words, during the manufacturing process, the inclined wedge 80 and part 1 form the same part and are made of the same material.

[0074] Considering the addition of the inclined wedge 80 in step S2, during the manufacturing of the wedge / component assembly along the vertical construction direction Z, the central axis X of component 1 has an inclination angle β relative to the construction direction Z. Therefore, the aforementioned connecting plane R of the connecting section S, including the connecting portion 42 and the flange 20, is also inclined at an angle β relative to the construction plane P. Thus, unlike the structures illustrated in Figures 4A and 4B without the inclined wedge 80, the connection between the connecting portion 42 and the flange 20 does not occur in one layer, but rather over several layers. Therefore, the connection between the connecting portion 42 and the flange 20 is progressive.

[0075] Figures 6A to 6D illustrate the formation of the connection segment S between the connection portion 42 and the flange 20 during additive manufacturing. Given the inclination of the connection plane R, several layers are required to form this connection segment S, in other words, to fill the gap I present between the connection portion 42 and the flange 20 at this stage of the manufacturing of part 1. Figure 6A illustrates the connection segment Sn at layer n of additive manufacturing. Figure 6B illustrates the connection segment Sn+1 at the next layer n+1 of additive manufacturing. Given the inclination of the connection plane R, a portion of the connection segment Sn+1 formed at layer n+1 can be at least partially supported on the material already formed in the previous layer n. This limits settlement and thus limits the presence of protrusions on the final part. Similarly, Figure 6C illustrates the connection segment Sn+2 at layer n+2 of additive manufacturing, and Figure 6D illustrates the connection segment Sn+3 at the next layer n+3 of additive manufacturing, each surface formed at one layer, which can rest on the surface formed in the previous layer.

[0076] Preferably, the number of layers required to fully form the connecting segment S is between 10 and 40. Preferably, the tilt angle β and height ε are determined such that the number of layers required to fully form the connecting segment S falls within this range.

[0077] It will be noted that, reference Figure 3 Up to 6D, the above description refers to the connection section S between the connecting portion 42 and the flange 20. However, this description is of course valid for other connecting surfaces to which the problem is described, particularly the connection section S between the connecting portions 32 and 52 and the flange 20.

[0078] When the manufacturing of part 1 is completed, the tilting wedge 80 that can tilt part 1 during the manufacturing process is removed (step S4). This removal can be performed by machining, for example, by removing an amount of material corresponding to the size of the tilting wedge 80, so that a final part 1 with the desired size and corresponding to the digital model that existed before the orientation step S2, in which the tilting wedge 80 was added, can be obtained.

[0079] Figure 8 A digital model of a second example of a component 1' to be manufactured is illustrated, on which the method according to the invention can be applied. In this example, the component 1' to be manufactured is an SP5NMA type bearing support for a turbojet engine, particularly for use in the exhaust cylinder of a UHBR DD ("Ultra-High Bypass Ratio Direct Drive") engine. Figure 8 The connection area between the walls that are at an angle to each other and involve the same problem as component 1 in the first example is located by circles, and the corresponding connection segment S' is also indicated.

[0080] Although the invention has been described with reference to specific embodiments, it will be apparent that modifications and changes can be made to these embodiments without departing from the general scope of the invention as defined by the claims. In particular, features of various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the specification and drawings should be considered illustrative rather than restrictive.

Claims

1. A method for manufacturing an aerospace component by additive manufacturing, the component to be manufactured extending about a central axis (X) and including at least two walls (20, 42) angled relative to each other and connected to each other by at least one connecting segment (S), the connecting segment (S) being included in a connecting plane (R) perpendicular to the central axis (X), the method comprising: - Provide a digital model of the part to be manufactured (1). - A digital model (1) oriented relative to the vertical construction direction (Z) of the component, such that the central axis (X) of the component has an angle β between 0.1° and 1° relative to the construction direction (Z). - Based on the digital model (1) obtained in the orientation step, the part is manufactured by additive manufacturing.

2. The method according to claim 1, wherein, The component to be manufactured is symmetrical about the central axis (X), and the connecting section (S) extends along an arc centered on the central axis (X).

3. The method according to claim 1, wherein, The steps of oriented digital model (1) include adding an inclined wedge (80) to the digital model between the horizontal construction plane (P) and the plane (B) that includes the lower end (12) of the part to be manufactured, so that the central axis (X) is inclined at an angle β relative to the vertical construction direction (Z).

4. The method according to claim 3, wherein, In the additive manufacturing process, the inclined wedge (80) is made of the same material as the part to be manufactured.

5. The method according to claim 3, wherein, The inclined wedge (80) is constructed such that, in the plane (B) including the lower end (12) of the part to be manufactured, the first radial end (14) of the part to be manufactured has a height ε relative to the second radial end (16) opposite to the first radial end (14).

6. The method according to claim 5, wherein, The component to be manufactured includes a basic cylindrical housing (10) including a lower end (12) and first and second radial ends (14, 16) that are radially opposite to each other.

7. The method according to claim 6, wherein, ε = D×arctan(β), where D is the diameter of the outer shell (10) of the part to be manufactured.

8. The method of claim 3, the method comprising the step of removing the tilting wedge (80) after the manufacturing step, wherein the tilting wedge (80) used to tilt the part during the manufacturing process of the part is removed to obtain the final part.

9. The method according to claim 8, wherein, The inclined wedge (80) is removed by machining.

10. The method according to claim 1, wherein, The digital model (1) is oriented relative to the vertical construction direction (Z) of the component, such that the central axis (X) of the component has an angle β between 0.3° and 0.8° relative to the construction direction (Z).

11. The method according to any one of claims 1 to 10, wherein, The component to be manufactured is the turbojet engine bearing support.

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