Component obtained by powder injection

Abstract

The invention relates to a component (50) obtained by injection molding, in particular from a mixture comprising an adhesive and a powder, the component having a plurality of protrusions (40) protruding from a main surface (241) of the component (50), the plurality of protrusions (40) comprising at least one first rib (41) and at least one second rib (42) intersecting at an intersection point (400) comprising a midpoint (44) of the component (50).

Description

Technical Field

[0001] This invention relates to a powder injection molding method, particularly a powder injection molding method for the aerospace industry. Specifically, this invention relates to the manufacture of components, such as gas turbine engine blades, using this powder injection molding method. Background Technology

[0002] Metal powder injection technology for "Metal Injection Moulding (MIM)" consists of injection molding using a mixture of metal powder and polymer binder.

[0003] The powder can be a metal (such as a titanium or aluminum alloy) or a ceramic. The mixture forms granules (also called "raw material"), which are extruded and then cut into sheets (also called "granules") for receiving and molding in an injection molding machine.

[0004] This technology enables the manufacture of metal products with high productivity, good repeatability, and reproducibility.

[0005] Some parts made by metal powder injection molding may deform, crack and / or exhibit defects after the parts are sintered, especially when the parts have complex and / or elongated geometries.

[0006] Therefore, it is difficult to apply metal powder injection molding technology to the manufacture of gas turbine engine blades. Summary of the Invention

[0007] Therefore, one object of the present invention is to improve powder injection molding, particularly for manufacturing gas turbine engine blades by powder injection.

[0008] To this end, a first aspect of the invention provides a component obtained by injection molding, in particular, from a mixture comprising an adhesive and a powder, the component including a plurality of protrusions projecting from the main surface of the component. More specifically, the plurality of protrusions include at least one first rib and at least one second rib intersecting at an intersection that includes the midpoint of the component.

[0009] Specifically, the powder includes metals and / or ceramics. Components may include gas turbine engine blades, each blade comprising a root, a tenon, and an airflow region extending between the root and the tenon. If desired, each protrusion may project from the main surface of the airflow region.

[0010] In addition, multiple protrusions may include: - At least one third rib, wherein the first, second, and third ribs coincide at their intersection; and / or - At least two ribs, which are connected to each other by an arched portion that preferably has a bend, which advantageously forms one of a plurality of protrusions, the bend having a curvature away from the main surface.

[0011] It can be configured such that at least one of the protrusions, preferably a rib, includes an upper edge having at least one flat region. Specifically, the upper edge is opposite to the main surface. Furthermore, the flat region may take the form of a recess created in the upper edge. Preferably, the flat region is configured to mate with a device for processing the component.

[0012] The component may also include at least one gating gate, which extends from the outer surface of the component opposite to the main surface (typically the outer surface of the airflow region opposite to the main surface) in particular along a direction orthogonal to the outer surface, typically along a direction orthogonal to the airflow region.

[0013] In addition, the following settings can be configured: - Two adjacent surfaces of a protrusion and / or two adjacent surfaces of a component (preferably, two adjacent surfaces of the root of a blade or a tenon) are connected by at least one rounded edge; - Two adjacent surfaces (especially two adjacent inner surfaces) of a component (preferably the root or tenon of a blade) oriented at an acute angle to each other are connected by at least one radius portion; - Multiple protrusions include at least one reinforcing member extending between the first rib and the second rib; -The reinforcement extends from the intersection; - The reinforcement joins the first surface of the first rib to the second surface of the second rib, the second surface extending opposite to the first surface; and / or - The component includes at least one extended weight and / or at least one boss, the at least one extended weight preferably forming one of a plurality of protrusions, the at least one extended weight extending from the end portion of the component, typically extending from the root or tenon of the blade, the at least one boss preferably forming one of a plurality of protrusions, the at least one boss being connected to the end portion of the component, typically connected to the root or tenon of the blade.

[0014] A second aspect of the invention provides a method for manufacturing components, particularly gas turbine engine blades, the method comprising a step of sintering at least one component according to a first aspect of the invention, during which the component abuts against a support by a plurality of protrusions.

[0015] In addition, the manufacturing method may include at least one finishing step, during which protrusions of the component are removed.

[0016] A third aspect of the invention provides a gas turbine engine blade, which is obtained by a manufacturing method according to a second aspect of the invention.

[0017] A fourth aspect of the invention provides a gas turbine engine comprising at least one blade according to a third aspect of the invention, particularly to which the blade is fixed.

[0018] A fifth aspect of the invention provides an aircraft comprising a gas turbine engine according to a fourth aspect of the invention, the gas turbine engine being fixed to the frame of the aircraft. Attached Figure Description

[0019] The invention will be better understood from the following detailed description, including illustrative and non-limiting embodiments, and with reference to the accompanying drawings. Further features, objects, and advantages will become apparent. This detailed description serves to complete the understanding of the invention and the disclosure of embodiments thereof, and, where appropriate, helps to define the invention. In the accompanying drawings: Figure 1 This is a schematic top view of the aircraft; Figure 2 This is a schematic half-section view of an aircraft gas turbine engine; Figure 3 This is a schematic perspective view of gas turbine engine blades; Figure 4a and Figure 4b schematically shown Figure 3 The deformation zone of the blade; Figure 5 This is a schematic perspective view of a component obtained by injection molding according to the present invention; Figure 6 yes Figure 5 A schematic front view of the component; Figures 7a to 8d yes Figure 5 Detailed views of the various parts of the component shown; and Figure 9 This is a flowchart illustrating an embodiment of the method for manufacturing a gas turbine engine blade, specifically according to the present invention. Detailed Implementation

[0020] Figure 1 This is a schematic top view of aircraft 1. More specifically, aircraft 1 is a device constructed to ascend and move in the air, and may be, for example, a civilian or military aircraft, a helicopter, etc.

[0021] Based on an example, such as Figure 1As shown, aircraft 1 is an airplane, which includes: a frame 10 consisting of a fuselage, a wing system including two wings, a tail assembly, flight control surfaces, and landing gear. Aircraft 1 also includes a propulsion system 100 to provide the thrust required to lift the aircraft 1 and move it in the air.

[0022] Of course, the aircraft 1 may include multiple propulsion systems 100, for example, according to Figure 1 The aircraft 1 shown as an example has a propulsion system 100 for each wing.

[0023] Figure 2 This is a schematic half-section view of the gas turbine engine 111 of the propulsion system 100 of the aircraft 1.

[0024] Specifically, the propulsion system 100 includes a gas turbine engine 111 having a main direction extending along the longitudinal axis X. Figure 1 In the case of an aircraft, the gas turbine engine 111 is configured to be fixed to the frame 10 of the aircraft 1 via a pylon, for example, to the wing. The gas turbine engine 111 may also be mounted at the rear of the fuselage, or even integrated into the fuselage of the aircraft 1.

[0025] The gas turbine engine 111 can be a dual-body, dual-flow, ducted, and direct-drive engine, as described below, but it can also have different numbers of bodies and / or flows, and / or it can be another type of turbojet engine, such as a ducted or non-ducted turbojet engine with a reduction gearbox or turboprop.

[0026] Unless otherwise stated, the terms "upstream" and "downstream" are used with reference to the overall direction of the airflow through the propulsion system 100 during operation. Similarly, the axial direction corresponds to the direction of the longitudinal axis X, and the radial direction is the direction orthogonal to and intersecting the longitudinal axis X.

[0027] Furthermore, the adjectives “inner” or “internal” and “outer” or “external” are used with reference to the radial direction, such that in the radial direction, the inner part of the element is closer to the longitudinal axis X than the outer part of the same element.

[0028] The gas turbine engine 111 includes a fan 1112, a main body, a combustion chamber 1115, and a turbine section from upstream to downstream in the direction of gas flow. The main body includes a compression section, which includes a low-pressure compressor 1113 and a high-pressure compressor 1114. The turbine section includes a high-pressure turbine 1116 and a low-pressure turbine 1117.

[0029] The fan 1112 can be ducted, that is, housed in the housing 1111.

[0030] The fan can also be non-ducted, meaning it is not housed in a housing and takes the form of a propeller.

[0031] The airflow entering the gas turbine engine 111 due to the suction generated by the fan 1112 is divided into a main flow and a secondary flow. The main flow is configured to pass through the main body, and the secondary flow is configured to bypass the main body.

[0032] In addition, the gas turbine engine 111 includes a high-pressure shaft 1118 and a low-pressure shaft 1119. The high-pressure shaft 1118 is connected to the high-pressure turbine 1116 and is configured to drive the high-pressure compressor 1114. The low-pressure shaft 1119 is connected to the low-pressure turbine 1117 and is configured to drive the low-pressure compressor 1113 and the fan 1112.

[0033] The gas turbine engine 111 includes blades 22 configured to be mounted on a hub.

[0034] Figure 3 This is a schematic perspective view of the blade 22 of the gas turbine engine 111.

[0035] The blade 22 includes a root 23, a tenon 25, and an airfoil having an aerodynamic profile that defines an airflow region 24, i.e., a flow channel for airflow. The blade 22 also includes a leading edge 27 and a trailing edge 28.

[0036] Leading edge 27 corresponds to the upstream portion of the aerodynamic profile 24 facing the airflow. Leading edge 27 divides the airflow into an inner arc flow and an outer arc flow.

[0037] The trailing edge 28 corresponds to the downstream portion of the aerodynamic profile 24, where the inner and outer arc flows converge.

[0038] The root 23 is configured to be fixed to the hub of the moving wheel, and the tenon 25 forms a free end. In the case of a flow straightener, the root 23 of the blade 22 is configured, for example, to be fixed to the hub of the flow straightener, and the tenon 25 is configured to be mounted on the shroud of the flow straightener. This type of blade exists elsewhere in the gas turbine engine 111, for example, in the compression section and the low-pressure turbine 1117.

[0039] The blade 22 can be obtained by powder injection molding (MIM). The powder injection molding method includes a sintering stage. In particular, in the case of the blade 22, the shrinkage of the molded part (especially the blade 22) during sintering can be up to 15% of the part's volume.

[0040] However, it is important to precisely control the dimensions of this type of component.

[0041] In addition, sintering temperatures above 1200°C can typically lead to deformation or cracking.

[0042] The blade 22 is more sensitive to shrinkage and extreme temperatures during sintering because it has a generally asymmetrical structure. In particular, the thickness of the airflow region 24 can be 3.5 times the thickness of the root 23 and / or the tenon 25, which produces torsion and / or bending.

[0043] Figure 4a and Figure 4b schematically shown Figure 3 The deformation zone of blade 22. More specifically, Figure 4a and Figure 4b The stress zone of blade 22 during sintering is shown.

[0044] In addition, other phenomena may occur during sintering, such as friction between the components and the frame on which they are located.

[0045] In this specification, examples of the component 50 manufactured by powder injection molding may include blade 22, or even blade 22.

[0046] Figure 5 This is a schematic perspective view of a component 50 (particularly blade 22) obtained by injection molding according to the present invention.

[0047] The aim is to mold a component 50 having multiple protrusions 40, which serve as both reinforcements and supports on the frame during sintering, so that the component 50 (e.g., blade 22) deforms uniformly.

[0048] Each protrusion 40 protrudes from the main surface 241 of the component 50, and in the case of the blade 22, from the main surface 241 of the airflow region 24. Thus, during sintering, the component 50 rests against the frame by the multiple protrusions 40, rather than by a separate support member.

[0049] Furthermore, the protrusion 40 enables the reduction of thickness differences between various regions of the component 50, for example, reducing the thickness difference between the airflow region 24 and the root 23 and / or tenon 25 in the case of the blade 22.

[0050] The protrusion 40 can also limit the number of contact points between the component 50 and the frame, thereby reducing friction generated during sintering.

[0051] Figure 5 An example of a part 50 including protrusions 40, obtained by powder injection molding, is shown.

[0052] The protrusion 40 protrudes from the main surface 241 of the component 50, for example from the lower surface of the airflow region 24 in the case of the blade 22, but it may also extend from the upper surface of the airflow region 24.

[0053] The geometry and number of protrusions 40 can vary.

[0054] More specifically, each protrusion 40 has an end portion opposite to the main surface 241 of the component 50. The end portion of the protrusion 40 forms the upper edge 401 of the protrusion 40.

[0055] The upper edge 401 of the protrusion 40 can be dot-shaped or substantially dot-shaped (i.e. having the smallest surface area) or can be planar (i.e. having a substantially extended surface area).

[0056] More specifically, according to the invention, all upper edges 401 of the protrusion 40 extend in the same plane P, such as Figure 6 As shown.

[0057] This arrangement allows for the definition and formation of the contact surface between the frame and component 50 during sintering.

[0058] To limit bending and / or torsion of component 50, the plurality of protrusions 40 include at least one first rib 41 and one second rib 42. The first rib 41 and the second rib 42 may intersect at an intersection point 400. In particular, the intersection point 400 includes the midpoint 44 of component 50, especially in the case of blade 22, it includes the midpoint of airflow region 24. The intersection point 400 indicates the geometric intersection of the two volumes formed by the first rib 41 and the second rib 42. The intersection point 400 corresponds to a surface in space including the midpoint 44, particularly centered on the midpoint 44. Additionally, the midpoint 44 may correspond to the center of gravity of component 50.

[0059] Furthermore, this arrangement of the first rib 41 and the second rib 42 allows for consideration of a reference point, particularly the midpoint 44 which remains fixed throughout the sintering process. Therefore, considering the reference point of component 50 (especially the midpoint 44) means that the inherent shrinkage during sintering can be better controlled.

[0060] according to Figure 5 In one example shown, the first rib 41 and the second rib 42 intersect at an intersection 400, including the midpoint 44. The first rib 41 and the second rib 42 form two branches of a "cross" pattern. Therefore, the first rib 41 and the second rib 42 form an angle with each other. According to various embodiments, the first rib 41 and the second rib 42 can unfold or tighten depending on the bending and / or torsion experienced by the component 50 during sintering.

[0061] To further support the component 50, particularly the airflow region 24 in the case of the blade 22, the plurality of protrusions 40 may further include at least one third rib 43, which is different from the first rib 41 and the second rib 42.

[0062] The third rib 43 may intersect with the first rib 41 and the second rib 42, particularly at the intersection 400.

[0063] according to Figure 5 As shown in the example, the first rib 41, the second rib 42, and the third rib 43 overlap at the intersection 400 and form three branches of a "star" pattern.

[0064] Therefore, the first rib 41, the second rib 42, and the third rib 43 form an angle with each other. According to various embodiments, the first rib 41, the second rib 42, and the third rib 43 can unfold or tighten depending on the intensity of bending and / or torsion experienced by the component 50 during sintering.

[0065] The first rib 41, the second rib 42, and / or the third rib 43 may have multiple identical or different geometries. Furthermore, the first rib 41, the second rib 42, and / or the third rib 43 may be linear.

[0066] To further support the component 50, particularly the airflow region 24 in the case of the blade 22, the plurality of protrusions 40 may further include at least one reinforcement 45, preferably a plurality of reinforcements 45. Figure 8b An example of reinforcement 45 is shown.

[0067] The reinforcing member 45 extends, in particular, from the intersection 400 between the first rib 41 and the second rib 42. Specifically, the reinforcing member 45 connects the first surface 410 (in particular the first side surface 410) of the first rib 41 to the second surface 420 (in particular the second side surface 420) of the second rib 42.

[0068] The plurality of protrusions 40 may include at least one fourth rib 46 that is different from the first rib 41, the second rib 42 and the third rib 43.

[0069] according to Figure 5 In the example shown, the plurality of protrusions 40 include at least ten fourth ribs 46, particularly at least twelve fourth ribs 46, particularly sixteen fourth ribs 46.

[0070] In addition, such as Figure 7bAs shown, to further limit the sinking of component 50, the plurality of protrusions 40 may further include at least one arched portion 47 connecting the two ribs (particularly the two fourth ribs 46). In particular, the arched portion 47 has a bend 471 having a curvature opposite to the main surface 241. In particular, the curvature of the bend 471 may correspond to the concave hemispherical curvature of the arched portion 47.

[0071] In fact, the arch 47 allows some of the mass of the component 50, especially some of the mass of the airflow region 24 in the case of the blade 22, to be transferred to the protrusion 40.

[0072] Because the center of component 50 is significantly lowered, the arch 47 connects the two fourth ribs 46 located in the central portion of component 50. To transfer more mass of component 50 to the protrusions 40, the protrusions 40 may also include multiple arches 47.

[0073] according to Figure 5 As shown and Figure 7b In a more detailed example, component 50 includes a plurality of arched portions 47 distributed in an arc shape between the first rib 41, the second rib 42 and / or the third rib 43.

[0074] The arched portion 47 connects two adjacent fourth ribs 46, which are specifically arranged on a portion of the elliptical portion located between the first rib 41, the second rib 42 and / or the third rib 43.

[0075] According to another embodiment, the arch 47 can connect any of the protrusions 40 together.

[0076] In addition to issues related to the sintering of part 50, deformation may also occur once the "green" part is obtained, as the geometry of part 50 is not suitable for molding. This may also result in at least one of the following phenomena: - A series of pores caused material defects on component 50; - Difficulty in filling the mold, resulting in areas of mechanical stress concentration in part 50, and / or Localized variations in the shrinkage rate of component 50 are commonly referred to as “black spots” or “segregation”.

[0077] Therefore, in order to improve the filling of the mold and / or the uniform cooling of the component 50, according to the present invention, two adjacent surfaces of the protrusion 40 and / or two adjacent surfaces of the component 50 (e.g., in the case of the blade 22, two adjacent surfaces of the root 23 or the tenon 25) can be connected by at least one circular edge 48.

[0078] For example, such as Figure 7a and Figure 7bAs shown, therefore the circular edge 48 can be replaced by: - The protruding edge formed by the two adjacent surfaces 221, 222 of the tenon 25; and / or -The protruding edge formed by the two adjacent surfaces 461, 462 of the fourth rib 46.

[0079] Furthermore, it can be configured that two adjacent inner surfaces of the component 50 oriented at an acute angle to each other (e.g., two adjacent inner surfaces of the root 23 or tenon 25 in the case of blade 22) are also connected by at least one radius portion 52.

[0080] Figure 8a An example of a radius portion 52 connecting two adjacent surfaces 231, 232 of the tenon 25 is shown.

[0081] Preferably, the radius portion 52 and the circular edge 48 may have a connection radius between 0.2 mm and 2 mm. The protrusion 40 may also have a thickness between 1 mm and 8 mm.

[0082] Component 50 may also include at least one boss 60, which is connected to the end portion of component 50. An example of a boss is shown in... Figure 8c As shown in the diagram. In the case of blade 22, boss 60 may also be connected to root 23 and / or tenon 25.

[0083] Of course, component 50 may include a plurality of bosses 60 connected to the end portion of component 50, particularly in the case of blade 22, connected to root 23 and / or tenon 25.

[0084] In addition to affecting the geometry of part 50, it can also affect the injection direction of the mixture to improve mold filling.

[0085] For this purpose, component 50 may include a gating gate 70 that extends from the outer surface 242 of component 50 opposite to the main surface 241 (such as the outer surface 242 of airflow region 24 opposite to the main surface 241) in particular in a direction orthogonal to the outer surface 242.

[0086] By way of examples Figure 6 An example of a gating gate 70 is further shown on component 50, wherein the gating gate 70 protrudes from the main surface 241 of component 50 and extends orthogonally, particularly from the outer arc portion in the case of blade 22.

[0087] In the example shown, the gating gate 70 is centered at the midpoint 44. However, the gating gate 70 can be offset relative to the midpoint 44.

[0088] To avoid the formation of a series of holes within component 50, component 50 may further include at least one extended weight 80, which extends from an end portion of component 50, particularly from the root 23 and / or tenon 25 in the case of blade 22. The series of holes then moves into the extended weight 80 and is no longer retained within component 50.

[0089] Figure 8d An example of the extended weight 80 located at the tenon 25 of the blade 22 is shown.

[0090] Figure 9 This is a flowchart of a method for implementing a method for manufacturing a blade 22, particularly for a gas turbine engine 111, according to the present invention.

[0091] The manufacturing method includes at least one mixing step E1, during which the mixture is injected into a mold.

[0092] At the end of mixing step E1, a component, sometimes referred to as the "green" component, is obtained. The component obtained from mixing step E1 is held in place by adhesive.

[0093] The manufacturing method then includes at least one debonding step E2, during which the adhesive is removed. The debonding step E2 can be carried out in various ways, particularly by water, heat, or chemicals.

[0094] At the end of the debonding step E2, a component, sometimes referred to as the "brown" component, is obtained.

[0095] The part obtained from the debonding step E2 (in which almost all the adhesive has been removed) is very fragile, especially since the part consists of about 40% air and is only bonded by the residual adhesive.

[0096] The manufacturing method includes at least one sintering step E3, during which the component obtained from the debinding step E2 is sintered. During the sintering step E3, the component obtained from the debinding step E2 is subjected to a temperature close to the melting point of the powder. This temperature allows the grains to weld together to form a solid.

[0097] At the end of sintering step E3, a part, sometimes referred to as a "grey" part, is obtained.

[0098] The part obtained from sintering step E3 consists only of powder and has shrunk relative to the volume injected during molding due to the space left by the binder.

[0099] The manufacturing method includes at least one finishing step E4, during which protrusions 40 on part 50 are removed, for example, by machining. The outer weight 80 and the gating gate 70 are also removed.

[0100] To facilitate removal, particularly by machining, the positioning of part 50 can be improved by providing a flat region 403 in the upper edge 401 of at least one of the protrusions 40. More specifically, due to the flat region, a rough machining stage is no longer required. Therefore, the blade is manufactured faster and cheaper.

[0101] Compared to the end portions of component 50 (such as the root 23 and tenon 25 in the case of blade 22), the main surface 241 of component 50 (especially the main surface 241 of the airflow region 24 in the case of blade 22) has a large support surface.

[0102] Furthermore, the use of the main surface 241 for positioning makes it possible to limit the deformation of the component 50, for example, by distributing the pressure applied to the component 50 by the vise more evenly.

[0103] Therefore, the flat region 403 in the upper edge 401 of at least one of the protrusions 40 is configured to cooperate with a device for handling the part 50 (particularly a vise in the case of machining) so that the main surface 241 can be utilized during positioning.

[0104] According to an exemplary embodiment, particularly as Figure 7a As shown, the flat region 403 forms a recess in the upper edge 401 of the protrusion 40. In other words, the flat region 403 extends in a plane that is not coplanar with the plane in which the upper edge 401 of the protrusion 40 (or even multiple protrusions 40, optionally all protrusions 40) extends. Therefore, the distance between the plane in which the flat surface 403 extends and the main surface 241 of the airflow region 24 is less than (or greater if the flat surface 403 is convex) the distance between the plane in which the upper edge 401 of the protrusion 40 (or even multiple protrusions 40, optionally all protrusions 40) extends and the main surface 241 of the airflow region 24.

[0105] In addition, a flat area 403, as many as the required contact points, can be provided to facilitate the positioning of component 50.

[0106] exist Figure 5 In the example shown, each of the four fourth ribs 46 on component 50 has a flat region 403. Therefore, the four contact points obtained by the flat regions 403 form a flat support. Thus, due to the flat regions 403, through the component 50 (e.g., as shown in the example), Figure 6 and Figure 7a As shown in the case of blade 22, additional contact points are provided at the leading edge 27 and tenon 23, eliminating only three degrees of freedom.

[0107] Therefore, the blade 22 according to the invention is suitable for gas turbine engines and has the same macroscopic shape and size as blades manufactured using prior art methods.

[0108] However, the microstructure of the blade 22 according to the present invention is different. Therefore, the blade 22 has a larger average particle size than the blades obtained by prior art methods.

[0109] Furthermore, the blade 22 according to the invention provides improved creep resistance.

Claims

1. A component (50) obtained by injection molding from a mixture comprising an adhesive and a powder, said component (50) comprising: - Gas turbine engine blades (22), the blades including a root (23), a tenon (25), and an airflow region (24) extending between the root (23) and the tenon (25); and - A plurality of protrusions (40) protruding from the main surface (241) of the airflow region (24), the plurality of protrusions (40) including two ribs (46) and an arch (47), the arch (47) connecting the two ribs (46) together and having a bend (471) having a curvature away from the main surface (241).

2. The component (50) according to claim 1, wherein, One of the plurality of protrusions (40) includes an upper edge (401) having a flat region (403).

3. A component (50) obtained by injection molding from a mixture comprising an adhesive and a powder, said component (50) comprising: - Gas turbine engine blades (22), the blades including a root (23), a tenon (25), and an airflow region (24) extending between the root (23) and the tenon (25); and - A plurality of protrusions (40) protruding from the main surface (241) of the airflow region (24), one of the plurality of protrusions (40) including an upper edge (401) having a flat region (403).

4. The component (50) according to claim 3, wherein, The plurality of protrusions (40) include two ribs (46) and an arch (47) that connects the two ribs (46) together and has a bend (471) that has a curvature away from the main surface (241).

5. The component according to any one of claims 1 to 4, wherein, The plurality of protrusions (40) include a first rib (41) and a second rib (42) that intersect at an intersection (400) including the midpoint (44) of the component (50).

6. The component (50) according to claim 5, wherein, The plurality of protrusions (40) include a third rib (43), wherein the first rib (41), the second rib (42) and the third rib (43) coincide at the intersection (400).

7. The component (50) according to any one of claims 1 to 6, wherein, The component also includes a casting port (70), which preferably extends from the outer surface (242) of the component (50) opposite to the main surface (241) in a direction orthogonal to the outer surface (242).

8. The component (50) according to any one of claims 1 to 7, wherein, Two adjacent surfaces (461, 462) of one of the plurality of protrusions (40) and / or two adjacent surfaces (221, 222) of the component (50) are connected by at least one rounded edge (48).

9. The component (50) according to any one of claims 1 to 8, wherein, The two adjacent inner surfaces (231, 232) of the component (50) oriented at an acute angle to each other are connected by at least one radius portion (52).

10. The component (50) according to any one of claims 5 to 9, wherein, The plurality of protrusions (40) include at least one reinforcement (45), which preferably extends from the intersection (400) between the first rib (41) and the second rib (42), and preferably, the reinforcement (45) connects a first surface (410) of the first rib (41) to a second surface (420) of the second rib (42), the second surface extending opposite to the first surface (410).

11. The component (50) according to any one of claims 1 to 10, wherein, The component also includes an extension weight (80) and / or a boss (60), the extension weight extending from an end portion of the component (50) and the boss being connected to the end portion of the component (50).

12. A method of manufacturing a component (50) according to any one of claims 1 to 11, the method comprising a sintering step (E3) during which the component (50) abuts against a support via the plurality of protrusions (40).

13. The manufacturing method according to claim 12, wherein, The manufacturing method includes a finishing step (E4) during which protrusions (40) of the component (50) are removed.

14. A gas turbine engine blade (22), said turbine engine blade being obtained by the manufacturing method according to claim 12 or 13.

15. A gas turbine engine (111) comprising the blades (22) according to claim 14.

16. An aircraft (1) comprising a gas turbine engine (111) according to claim 15.

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