FR2972127A1 - Method for producing metal reinforced leading edge or trailing edge of blade of e.g. turbomachine, involves hot isostatic pressing of metal staples for causing agglomeration of metal staples so as to obtain reinforced metal part - Google Patents

Abstract

The present invention relates to a method for producing a metal part such as a turbomachine blade metal reinforcement successively comprising: a step of positioning a plurality of metal staples (301) on a removable frame (610), so that said metal staples (301) are suspended from the removable frame (610); a step of positioning said removable frame (610) in a housing (450) arranged in a form tool (400) having a die (440) and a punch (420); a hot isostatic pressing step of said plurality of metal staples (301 ') positioned in said shaped tool causing agglomeration of said metal staples (301 ") to obtain said metal piece.

Description

PROCESS FOR PRODUCING A METAL PIECE SUCH AS A TURBOMACHINE BLADE REINFORCEMENT

The present invention relates to a method of producing a metal part such as a composite blade metal reinforcement or metal turbomachine. More particularly, the invention relates to a method for producing a leading edge metal reinforcement or turbomachine blade trailing edge.

The field of the invention is that of turbomachines and more particularly that of the fan blades, made of composite or metallic material, of a turbomachine and whose leading edge comprises a metallic structural reinforcement. However, the invention is also applicable to the production of a metal reinforcement intended to reinforce a leading edge or a blade trailing edge of any type of turbomachine, whether terrestrial or aeronautical, and in particular a helicopter turbine engine or an airplane turbojet engine, but also propellers such as propellers of double uncontrolled contra-rotating fans ("open rotor" in English).

The invention is also applicable to the production of all massive metal parts and complex geometric shape. It is recalled that the leading edge corresponds to the front part of an airfoil which faces the airflow and which divides the airflow into an intrados airflow and a flow of air. extrados air.

The trailing edge corresponds to the posterior part of an aerodynamic profile where the intrados and extrados flows meet. The turbomachine blades, and in particular the fan blades, undergo significant mechanical stress, particularly related to the speed of rotation, and must meet strict conditions of weight and bulk. Therefore, blades made of composite materials are used which are lighter. It is known to equip the fan blades of a turbomachine, made of composite materials, with a metallic structural reinforcement extending over the entire height of the blade and beyond their leading edge as mentioned in EP1908919. Such a reinforcement makes it possible to protect the composite blading during an impact of a foreign body on the blower, such as, for example, a bird, hail or pebbles. In particular, the metallic structural reinforcement protects the leading edge of the composite blade by avoiding risks of delamination, fiber breakage or damage by fiber / matrix decohesion. In a conventional manner, a turbomachine blade has an aerodynamic surface extending, in a first direction, between a leading edge and a trailing edge and, in a second direction substantially perpendicular to the first direction, between a foot and a dawn summit. The metallic structural reinforcement follows the shape of the leading edge of the aerodynamic surface of the blade and extends in the first direction beyond the leading edge of the aerodynamic surface of the blade to match the profile of the blade. the intrados and the upper surface of the dawn and in the second direction between the foot and the top of the dawn. In known manner, the metal structural reinforcement is a titanium metal part made entirely by milling from a block of material. However, the metal reinforcement of a blade leading edge is a complex piece to achieve, requiring many rework operations and complex tools involving significant realization costs. In this context, the invention aims to solve the problems mentioned above by proposing a method for producing a leading edge metal reinforcement or turbomachine blade trailing edge to significantly reduce the costs of production. of such a piece and to simplify the manufacturing range. To this end, the invention proposes a method for producing a metal part, such as a turbomachine blade metal reinforcement, comprising successively: a step of positioning a plurality of metal staples on a removable frame, so that said metal clips are suspended from the removable frame; a step of positioning said removable frame in a housing arranged in shaped tooling having a die and a punch, a step of hot isostatic pressing of said plurality of metal clips positioned in said form tool causing the agglomeration of said metal staples so as to obtain said metal part. The term "staple" means a metal piece bent or folded so as to form, for example, a substantially U-shaped or V-shaped piece. Thanks to the invention, the metal piece, such as, for example, a metallic structural reinforcement comprising two curvatures according to two distinct planes (or a twisting along an axis), is made quickly and simply from a plurality of metal staples, obtained by a simple operation of shaping metal sections, such as wire, and a Hot Isostatic Pressing (HIP) process to obtain a compact, porosity-free part by the combination of plastic deformation, creep and diffusion welding. The metal staples are advantageously formed by the folding of metal sections from a die which may be of circular, square, hexagonal, and so on. The metal staples thus produced can easily be positioned in embedding means arranged in a frame advantageously formed by the combination of two rails by using the elastic property of the staples, so as to produce pieces of complex geometry such as blade reinforcements. . This production method thus makes it possible to dispense with the complex realization of the blade reinforcement by machining in the mass, of the milling, broaching type, from flats requiring large volume of material of implementation and consequently of the costs. important in raw material supply. The method also makes it easy to produce metal reinforcements that meet strict requirements of mass and / or geometric. Advantageously, the metal part is a metal reinforcement of the leading edge or trailing edge of the turbomachine fan blade. The method for producing a metal part according to the invention may also have one or more of the following characteristics, considered individually or in any technically possible combination: said method is a method of producing a metal reinforcement on board etching or trailing edge, turbomachine blade or a helical metal reinforcement so that said metal part obtained during said isostatic pressing step is a metal reinforcement; said removable frame is formed by two rails so that during the step of positioning said removable frame, each of said rails of said removable frame is adapted to be inserted into a notch arranged in said shaped tool, said notches forming said housing of said tooling of form; said notches are arranged in the matrix of said tooling so that said removable frame is positioned in said matrix during said positioning step; said notches are arranged in the punch of said tool so that said removable frame is positioned in said punch during said positioning step; - Said step of positioning said plurality of staples having two branches is formed by a recess of each of said branches in said recess means arranged in said removable frame, said recess being formed by elastic deformation of said branches; said step of positioning said plurality of staples, comprising two branches presenting at their free end a shoulder, is made such that each clip is suspended on said removable frame by said shoulders; said step of positioning said plurality of staples is made staple by staple; said step of positioning said plurality of staples is carried out by bundles of staples previously assembled into a metal structure; said method comprises a step of producing said metal staples by cold forming of metal sections initially of rectilinear shape. Other characteristics and advantages of the invention will emerge more clearly from the description which is given below, by way of indication and in no way limiting, with reference to the appended figures, in which: FIG. 1 is a side view of a blade comprising a metallic leading edge structural reinforcement obtained by means of the embodiment method according to the invention; - Figure 2 is a partial sectional view of the blade shown in Figure 1 according to a cutting plane AA; FIG. 3 is a block diagram showing the main steps for producing a turbomachine blade leading edge metallic structural reinforcement of the embodiment method according to the invention; FIG. 4 illustrates a view of the turbomachine blade leading edge metal reinforcement during the first step of the process illustrated in FIG. 3; FIG. 5 illustrates a view of the turbomachine blade leading edge metal reinforcement according to a first embodiment of the second step of the method illustrated in FIG. 3; FIG. 6 illustrates a view of the turbomachine blade leading edge metal reinforcement according to a second embodiment of the second step of the method illustrated in FIG. 3; FIG. 7 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement according to the first embodiment described in FIG. 5 of the third step of the method illustrated in FIG. 3; FIG. 8 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement according to the second embodiment described in FIG. 6 of the third step of the method illustrated in FIG. 3; FIG. 9 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement according to a first embodiment of the fourth step of the method illustrated in FIG. 3; - Figure 10 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement according to a second embodiment of the fourth step of the method illustrated in Figure 3; FIG. 11 illustrates a sectional view of a turbomachine blade leading edge metal reinforcement during the fifth step of the production method illustrated in FIG. 3. In all the figures, the common elements bear the same reference numbers unless otherwise specified. FIG. 1 is a side view of a blade comprising a metallic leading edge structural reinforcement obtained by means of the embodiment method according to the invention. The blade 10 illustrated is for example a mobile blade of a fan of a turbomachine (not shown). The blade 10 has an aerodynamic surface 12 extending in a first axial direction 14 between a leading edge 16 and a trailing edge 18 and in a second radial direction 20 substantially perpendicular to the first direction 14 between a foot 22 and a top 24. The aerodynamic surface 12 forms the extrados face 13 and intrados 11 of the blade 10, only the extrados face 13 of the blade 10 is shown in Figure 1. The intrados 11 and the extrados 13 form the side faces of the blade 10 which connect the leading edge 16 to the trailing edge 18 of the blade 10. In this embodiment, the blade 10 is a composite blade typically obtained by shaping the blade. a woven fibrous texture. By way of example, the composite material used may be composed of an assembly of woven carbon fibers and a resinous matrix, the assembly being formed by molding using an RTM type resin injection process. (for "Resin Transfer Molding") or VARTM (for Vccum Resin Transfer Molding). The blade 10 has a metal structural reinforcement 30 bonded at its leading edge 16 and extends both along the first direction 14 beyond the leading edge 16 of the aerodynamic surface 12 of the blade. dawn 10 and in the second direction 20 between the foot 22 and the apex 24 of the dawn. As represented in FIG. 2, the structural reinforcement 30 matches the shape of the leading edge 16 of the aerodynamic surface 12 of the blade 10 that it extends to form a leading edge 31, said leading edge of the reinforcement . Conventionally, the structural reinforcement 30 is a one-piece piece comprising a substantially V-shaped section having a base 39 forming the leading edge 31 and extended by two lateral flanks 35 and 37 respectively fitting the intrados 11 and extrados 13 of the aerodynamic surface 12 of the dawn. Flanks 35, 37 have a tapered or thinned profile towards the trailing edge of the blade. The base 39 has a rounded internal profile 33 capable of conforming to the rounded shape of the leading edge 16 of the blade 10. The structural reinforcement 30 is metallic and preferably based on titanium. This material has indeed a high energy absorption capacity due to shocks. The reinforcement is glued on the blade 10 by means of adhesive known to those skilled in the art, such as an epoxy adhesive.

This type of metal structural reinforcement 30 used for the turbomachine composite blade reinforcement is more particularly described in the patent application EP1908919. The method according to the invention makes it possible to produce in particular a structural reinforcement as illustrated in FIG. 2, FIG. 2 illustrating the reinforcement 30 in its final state. FIG. 3 represents a block diagram illustrating the main steps of a method for producing a metal part 200 making it possible, for example, to produce a metal structural reinforcement 30 for a blade leading edge 10, as illustrated in FIGS. and 2.

The first step 210 of the production method 200 is a step of cutting a plurality of metal sections 301 from a continuous wire, for example from a die, each section length 301 is determined according to the final piece to realize. Metal sections 301 thus cut are illustrated in FIG.

Each metal section 301 may therefore have a specific length depending on the portion of the metal reinforcement 30 that it represents, the overlap length of the sidewalls 35, 37 of the reinforcement 30 varying in the second direction 20 between the foot 22 and the top 24. of dawn.

The diameter of the metal sections 301 may vary according to the needs of the user, and the material thickness necessary for the production of the part. The determination of the diameter of the sections is made according to a compromise between flexibility and material thickness required in the tooling.

The metal section is typically formed from a wire of circular section but may equally well be formed from a metal profile of square, rectangular, hexagonal, etc. The second step 220 of the manufacturing method 200 is a step of cold forming or shaping the metal sections 301 cut in the first step 210. This second step is illustrated in Figure 5. This second step 220 allows the cold forming (ie at room temperature) of each metal section 301 rectilinear plastic deformation. This step therefore makes it possible to obtain a preformed metal section 301 ', hereinafter referred to as a staple, the geometry of which is determined as a function of the final part to be produced and in particular as a function of the shape of the compaction tool used for the production. of the final piece. The staples 301 'are made by deformation of the rectilinear metal sections 301 by means of a simple tool that can be operated manually, the individual deformation of each section does not require hydraulic means therefore to achieve the deformation of the metal section Advantageously, the deformation tooling is a conventional deformation tool that can be automated and calibrated both in the final shape of the metal clips 301 'and in pressure force according to the needs of the metal. 'user. Thus, the staples 301 'can be formed individually or in a package made up of a plurality of metal sections 301. The step 220 of deformation of the sections thus makes it possible to pass from a metal section 301 of rectilinear shape to a metal section 301 'forming a staple 301', comprising two branches substantially rectilinear 302 and 303 joined together at one of their end by a junction element 304 having undergone at least one deformation. The lengths of the branches 302 and 303 may be different for the same staple 301 '. The metal section 301 can also be completely or partially crushed (for example for a restriction of local thickness) during the deformation step.

In the context of the realization of a turbomachine blade metal reinforcement, the staples 301 'are advantageously U-shaped or V-shaped. According to a second embodiment, the cold forming step 220 comprises an additional operation. forming the ends 405, 406 of the legs 402, 403 of the clips 401 ', so as to create staples 401' having at their free ends shoulders 407 as illustrated in Figure 6. The third step 230 of the method of embodiment 200 is a step of positioning a plurality of staples 301 'on a frame 610 formed by two rails 611 and 612, illustrated in FIGS. 7 and 8. The shape of the rails 611, 711 and 612, 712 follows the neutral fiber of the part to be produced, such as the complex neutral fiber of the blade reinforcement. The positioning of the plurality of staples 301 ', 401' is made staple by staple or by staple bundle previously positioned and held together by securing means. For example, the staples 301 ', 401' are held in bundles, so as to form a three-dimensional metal structure, by welding, or by gluing, of metal strips, said metal foils cut beforehand into a metal foil of low thickness. The spacing between each staple 301 ', 401' (i.e. pitch) is defined according to the thickness of the staple 301 ', 401' and the material requirements of the workpiece to be made. According to the first embodiment illustrated in FIG. 7, the rails 611 and 612 of the frame 610 comprise embedding means 622, such as orifices, making it possible to hold the staples 301 'in position while using the elastic property of the branches. 302, 303 of the staples 301 '. The staples 301 'are then held in position by exerting pressure against the walls of the recessing means 622 by elastic return of the branches 302 and 303 previously deformed to allow their insertion into the recessing means 622. Advantageously and to guarantee a good holding in position of the staples 301 'on the frame 610, shaping of the staples during the second step 220 is performed in order to obtain, in the rest position (ie without external stress), a spacing between the two branches 302, 303 of the clips 301 'greater or less than the spacing between two embedding means 622 located respectively on each of the rails 611 and 612 of the frame 610. Thus, when the spacing of the branches 302, 303 in the position of rest is greater than the spacing of two recessing means 622 located on each of the rails 611 and 612, the staples 301 'are held recessed by elastic return of the branches 302, 303 exerting a pressing force against the walls of the embedding means 622, in a direction illustrated by the arrows referenced F, in order to return to their rest position. Conversely, when the spacing of the legs 302, 303 in the rest position is less than the spacing of two recessing means 622 located on each of the rails 611 and 612, the staples 301 'are held recessed by elastic return of branches 302, 303 which exert a pressing force against the walls of the embedding means 622, in the direction opposite to the direction illustrated by the arrows referenced F, in order to return to their rest position. In this third step 230 of the production method 200, several layers of staples 301 ', as illustrated in FIG. 5, may be superimposed in order to respect the thicknesses of material necessary for producing the part. For this purpose, the rails 611 and 612 of the frame comprise several rows of embedding means 622. In Figure 7 showing a sectional view of the frame 610, two rows of embedding means 622 are shown on each rail 611 and 612 610. The shape of the staples 301 ', of the various superposed layers, can also be dependent on the localized material needs which are necessary for the realization of the metal reinforcement 30. Of course, the shape and the length of the staples 301' of the different layers may also be adjusted according to the material requirements necessary for the realization of the metal reinforcement 30. According to the second embodiment illustrated in Figure 8, the clips 401 'are held in position on the frame 710 by the shoulders 407 located both sides of the V-shape or U-shape of the staple 401 '. Thus, the two shoulders 407 of the clip allow to hold it suspended on the frame 710 by resting on each of the rails 711, 712 of the frame 710. According to this second embodiment, several layers of staples 401 'can also be superimpose in order to respect the thicknesses of material necessary for the realization of the piece.

The staples 301 'and 401' of the various layers are mainly made from titanium metal wires. However, it is also possible to incorporate among the staples 301 ', 401' of titanium positioned on the frame 610, 710, metal staples based on silicon carbide and titanium (SiC-Ti), son coated with Boron (SiC-Boron yarn) or Silicon Carbide (SiC-SiC yarn) insofar as the radius of curvature of the staples 301 ', 401' allows deformation of these yarns, called "composite yarns", without reaching their limit. a break. The clips 301 ', 401' are made from metal sections 10 with a thickness varying substantially from 0.1 mm to 5 mm. The step 230 for positioning the staples 301 ', 401' can also include a sub-step of inserting an insert between two successive layers of staples 301 ', 401' so as to provide, for example, a larger local stock allowance. of material, a specific reinforcement 15 made of a different material or to make a hollow metal reinforcement. By way of example, the insert may be a solid insert made by a forging, machining or casting process. or an insert woven by means of metal threads, for example with titanium threads and / or silicon carbide and titanium (SiC-Ti), aluminum (SIC-AI) -based threads in the case of aluminum alloy staples, and / or boron-coated yarns (SiC-Bore), or silicon carbide (SiC-SiC). Whatever the nature of the material used for producing the insert inserted between the different layers of staples 301 ', 401', it is necessary that this material be compatible with the nature of the material used for producing the metal staples. 301 ', 401' and has properties for superplastic forming and diffusion welding. For the production of a hollow metal reinforcement (not shown), the insert is a fugitive insert made of a material different from the material used for producing the metal staples 301 ', 401'. The term "fugitive insert" means an insert which is not intended to be permanent and which is only necessary for the realization of the leading edge hollow metal reinforcement. The fugitive insert is not present in the metal reinforcement in its final state and does not participate in any mechanical characteristics of the metal reinforcement. The fugitive insert is for example made of a material capable of withstanding a high temperature, of the order of 900 ° C, a high pressure, of the order of 1000 bar, and which is compatible with the materials of metal staples 301 ', 410' so as not to create impurities or oxidation. The material of the fugitive insert must also be chemically etchable by dissolution using a chemical agent. Advantageously, the fugitive insert is made of copper, or quartz or silica.

The shape of the fugitive insert incorporated in the stack of staple layers 301 ', 401' is dependent on the shape of the desired final internal cavity. The fourth step 240 of the production method 200 is a positioning step of the frame 610, 710 comprising the plurality of staples 301 ', 401' in a form tool 400, 500. The tool 400, 500 comprises a die 440, 540 having a recess 410 corresponding to the final external shape of the metal reinforcement 30 and a punch 420, 520 corresponding to the final internal shape of the leading edge metal reinforcement.

This step 240 of the production method 200 is illustrated in FIGS. 9 and 10 with the frame 610 of the first embodiment described in FIGS. 5 and 7. However, this step is also applicable to the frame 710 and to the staples 401 'of the second embodiment of FIG. embodiment according to a first exemplary embodiment illustrated in FIG. 9, the positioning of the frame 610 is carried out in the die 440 of the shape tool 400. For this purpose, the die 440 of the tooling of form 400 has in its upper part two notches 450, located on either side of the cavity 410, forming a housing adapted to receive the frame 610. The shape of the notches 450 is complementary to the shape of the frame 610 so that the frame 610 is placed in the notches 450 simply by interlocking. The staples 301 'having the complementary shape of the cavity 410, the positioning of the frame 610 comprising the plurality of staples 301' is simply realized and thus makes it possible to obtain a deposit of metal material matching the complex shape of the cavity 410 having two curvatures in two distinct planes. According to a second exemplary embodiment illustrated in FIG. 10, the positioning step 240 is performed by the positioning of the frame 610 on the punch 520 of the shaped tooling 500. For this purpose, the shaped screen 500 comprises a 540 matrix having an imprint 410 similar to the first embodiment, and a punch 520, corresponding to the final internal shape of the leading edge metal reinforcement. The punch 520 has in its upper part two notches 550 located on either side of the V-shape corresponding to the final internal shape of the metal reinforcement. In a similar manner to the previous embodiment, the notches 550 form a housing adapted to receive the frame 610 in which the clips 301 'are embedded. The shape of the notches 550 is also complementary to the shape of the rails 611, 612 forming the frame 610, so that the frame 610 is placed in the notches 550 simply by interlocking. In this embodiment, each of the rails 611, 612 of the frame 610 is held in a notch 550 of the punch 520 for example by a cold assembly using or not pins, by screwing means, or by other means classic keeping. In a similar manner to the previous embodiment, the staples 301 'having the complementary shape of the cavity 410 of the matrix 540, the positioning of the frame 610 is simply carried out and thus makes it possible to obtain a deposit of metal material conforming to the complex shape punch 520 having two curvatures in two separate planes. The fifth step 250 of the production method 200, illustrated in FIG. 11, is a hot isostatic pressing (HIP) step of the stack formed by the various layers of staples 301 ', 401 positioned in shape tooling 400, 500. Hot isostatic pressing is a widely used manufacturing method known to reduce the porosity of metals and affect the density of many materials such as pre-compacted powder. The isostatic pressing process also makes it possible to improve the mechanical properties and the exploitability of the materials. Isostatic pressing is carried out at high temperature (conventionally between 400 ° C. and 1400 ° C., and of the order of 1000 ° C. for titanium) and at isostatic pressure. Thus, the application of heat combined with the internal pressure eliminates the voids of the stack, as well as the microporosities by means of a combination of plastic deformation, creep, and diffusion welding to form a massive piece 430. The massive piece 430 resulting from the isostatic pressing step comprises the inner and outer profiles of the metal reinforcement 30. The solid piece 430 is then demolded from the tool 400, 500. The isostatic pressing step is carried out under vacuum advantageously under secondary vacuum is in a welded tool in which the secondary vacuum is made, or in autoclave bag, the choice of the method depending on the number of part to be produced. The secondary vacuum makes it possible to avoid the presence of oxygen molecules in the tooling and at the level of the fibrous structure, during the titanium isostatic pressing step. According to a second exemplary embodiment, hot pressing may also be an isothermal forging process in a press in a vacuum chamber.

Tooling 400, 500 is made of a mechanical alloy called superalloy or high performance alloy. The rails 611, 711 and 612, 712 of the frame 610, 710 may be made of the same material as the staples 301 ', 401' (i.e. titanium), or else in a mechanical alloy identical to the form tooling. If the rails 611, 711 and 612, 712 of the frame 610, 710 are of titanium, the step 250 of isostatic pressing will compact the rails 611, 711 and 612, 712 of the frame 610, 710 at the same time as the staples 302, 401 'so as to form a massive piece having two massive shoulders. In this embodiment, an additional operation of recovery will be necessary in order to trim, for example by machining, the surplus of material brought the rails 611, 711 and 612, 712. The step 250 of isostatic pressing can comprise previously a step cleaning, degreasing and / or etching the metal staples 301 ', 401' so as to remove residual impurities from the various staple layers. Advantageously, the step of cleaning the impurities is carried out by dipping all the staples 301 ', 401' positioned on the frame 610, 710 in a bath of cleaning agent or chemical agent before it is placed in the tooling. 400, 500 form.

In the context of manufacturing a hollow metal reinforcement, the method according to the invention may comprise an additional step of chemical etching of the insert, introduced between the various layers of staples 301 ', 401', and forming an integral part compacted solid piece 430.

The chemical attack is carried out by means of a chemical agent capable of attacking the material in which the insert is made. The chemical attack of the fugitive insert dissolves the fugitive insert so that the space released by the dissolved insert forms the internal cavity of the hollow metal reinforcement. Advantageously, the etching step is carried out by dipping the solid piece 430 in a bath comprising the chemical agent capable of dissolving the insert. The chemical agent is for example an acid or a base. Advantageously, the chemical agent is capable of dissolving copper, quartz or silica. In association with these main production steps, the method 200 according to the invention may also include a finishing step and machining of the massive piece 430 obtained at the output of the tool so as to obtain the reinforcement 30. This recovery step comprises: - a recovery step of the profile of the base 39 of the reinforcement 30 so as to refine it and in particular the aerodynamic profile of the leading edge 31; a step of recovery of the flanks 35, 37; this step consisting in particular of trimming the flanks 35, 37 and the thinning of the intrados and extrados flanks; - A finishing step to obtain the required surface condition. In association with these main production steps, the method according to the invention may also comprise non-destructive testing steps of the reinforcement 30 making it possible to ensure the geometrical and metallurgical conformity of the assembly obtained. By way of example, the non-destructive tests can be carried out by an X-ray method. The present invention has been mainly described with the use of titanium-based metal wires; however, the production method is also applicable with any metal material having properties for superplastic forming and / or diffusion welding.

The invention has been particularly described for producing a metal reinforcement of a composite turbomachine blade; however, the invention is also applicable for producing a metal reinforcement of a turbomachine metal blade. The invention has been particularly described for producing a metal reinforcement of a turbomachine blade leading edge; however, the invention is also applicable to the production of a metal reinforcement of a trailing edge of a turbomachine blade or to the production of a metallic helical reinforcement composite or metal. The other advantages of the invention are in particular the following: reduction of implementation costs; - reduction of the production time; - simplification of the manufacturing range; - reduction of material costs.20

Claims (10)

REVENDICATIONS1. Method for producing (200) a metal part (30), such as a turbomachine blade metal reinforcement, comprising successively: a step (230) for positioning a plurality of metal staples (301 ', 401 ') on a removable frame (610, 710), so that said metal clips (301', 401 ') are suspended from the removable frame (610, 710); a step (240) for positioning said removable frame (610, 710) in a housing (450, 550) arranged in a form tool (400, 500) having a die (440, 540) and a punch (420, 520); a step (250) of hot isostatic pressing of said plurality of metal staples (301 ', 401') positioned in said shaped tool causing said metal staples (301 ', 401') to agglomerate in such a manner as to obtain said metal piece (30). 2. Method of producing (200) a metal part (30) according to claim 1 characterized in that said method is a method of producing a leading edge metal reinforcement, or trailing edge, of turbomachine blade or a helical metal reinforcement so that said metal piece obtained during said step (240) of isostatic pressing is a metal reinforcement. 3. A method of producing (200) a metal part (30) according to one of claims 1 to 2 characterized in that said removable frame (610, 710) is formed by two rails (611, 612, 711, 712 ) so that during the step (240) of positioning said removable frame (610, 710), each of said rails (611, 612, 711, 712) of said removable frame (610, 710) is adapted to be inserted into a notch (450, 550) arranged in said form tool (400, 500), said notches (450, 550) forming said housing of said form tool (400, 500). 4. Method of producing (200) a metal part (30) according to claim 3 characterized in that said notches (450) are arranged in the die (440) of said tool (400) so that said removable frame (610 , 710) is positioned in said die (440) during said positioning step (240). 5. A method of producing (200) a metal part (30) according to claim 3 characterized in that said notches (550) are arranged in the punch (520) of said tool (500) so that said removable frame (610 , 710) is positioned in said punch (520) during said positioning step (240). 6. A method of producing (200) a metal part (30) according to one of claims 1 to 5 characterized in that said step (230) for positioning said plurality of staples (301 ') having two branches ( 302, 303) is made by embedding each of said legs (303, 303) in said embedding means (622) arranged in said removable frame (610), said embedding being made by elastic deformation of said legs (302, 303) . 7. Method of producing (200) a metal part (30) according to one of claims 1 to 5 characterized in that said step (230) for positioning said plurality of staples (401 '), comprising two branches (402, 403) having at their free end a shoulder (407), is formed such that each clip (401 ') is suspended on said removable frame (710) by said shoulders (407). 8. Method of producing (200) a metal part (30) according to one of claims 1 to 7 characterized in that said step (230) for positioning said plurality of staples (301 ', 401') is carried staple by staple. 10 9. Method of producing (200) a metal part (30) according to one of claims 1 to 7 characterized in that said step (230) for positioning said plurality of staples (301 ', 401') is made by bundles of staples previously assembled into a metal structure. 10. A method of producing (200) a metal part (30) according to one of claims 1 to 9 characterized in that said method comprises a step (220) for producing said metal staples (301 ') by forming to cold metal sections (301) initially of rectilinear shape.