• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for manufacturing a part (20) comprising the formation of successive solid metal layers (201 ... 20n), superimposed on each other, each layer describing a pattern defined from a digital model. (M), each layer being formed by the deposition of a metal (25), said filler metal, the filler metal being subjected to a supply of energy so as to melt and to constitute, in solidifier, said layer, in which the filler metal takes the form of a powder (25), the exposure of which to an energy beam (32) results in a fusion followed by solidification so as to form a solid layer (201 ... 20n), the method being characterized in that the filler metal (25) is an aluminum alloy comprising at least the following alloying elements: - Ni, according to a mass fraction of 1% to 6%, preferably 2 to 5.5%; - Cr, according to a mass fraction of 1% to 7%, preferably from 3 to 6.5%; - Zr, according to a mass fraction of 0.5 to 4%, preferably from 1 to 3%; - Fe, according to a mass fraction less than or equal to 1%, preferably from 0.05 to 0.5%, more preferably from 0.1 to 0.3%; - If, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.5%. The invention also relates to a part obtained by this method. The alloy used in the additive manufacturing process according to the invention makes it possible to obtain parts with remarkable characteristics.
    公开号:FR3083478A1
    申请号:FR1870822
    申请日:2018-07-09
    公开日:2020-01-10
    发明作者:Bechir Chehab
    申请人:C Tec Constellium Technology Center SAS；
    IPC主号:
    专利说明:

    Description
    Title of the invention: Method of manufacturing an aluminum alloy part
    Technical field The technical field of the invention is a method of manufacturing an aluminum alloy part, using an additive manufacturing technique. Prior art [0002] Since the 1980s, additive manufacturing techniques have developed. They consist in shaping a part by adding material, which is the opposite of machining techniques, which aim to remove material. Formerly confined to prototyping, additive manufacturing is now operational for mass production of industrial products, including metal parts.
    The term "additive manufacturing" is defined, according to French standard XP E67-001, as a set of methods for manufacturing, layer by layer, by adding material, a physical object from a digital object. ASTM E2792 (January 2012) also defines additive manufacturing. Different additive manufacturing methods are also defined and described in ISO / ASTM 17296-1. The use of additive manufacturing to produce an aluminum part, with low porosity, has been described in document WO2015 / 006447. The application of successive layers is generally carried out by applying a so-called filler material, then melting or sintering the filler material using an energy source of the laser beam, electron beam type, plasma torch or electric arc. Whatever the additive manufacturing method applied, the thickness of each added layer is of the order of a few tens or hundreds of microns.
    An additive manufacturing means is the melting or sintering of a filler material taking the form of a powder. It can be fusion or sintering by an energy beam.
    We know in particular selective laser sintering techniques (selective laser sintering, SLS or direct metal laser sintering, DMLS), in which a layer of metal powder or metal alloy is applied to the workpiece and is selectively sintered according to the digital model with thermal energy from a laser beam. Another type of metal forming process includes selective laser melting (SLM) or electron beam melting (EBM), in which the thermal energy supplied by a laser or a directed electron beam is used to selectively melt (instead of sinter) the metal powder so that it fuses as it cools and solidifies.
    Also known is laser melting deposition (LMD) in which the powder is sprayed and melted by a laser beam simultaneously.
    Patent application WO2016 / 209652 describes a method for manufacturing aluminum with high mechanical strength comprising: the preparation of an atomized aluminum powder having one or more approximate powder sizes desired and an approximate morphology; sintering the powder to form a product by additive manufacturing; dissolution; quenching; and the income from additively produced aluminum.
    Patent application EP2796229 discloses a method for forming a metallic aluminum alloy reinforced by dispersion comprising the steps consisting in: obtaining, in powder form, an aluminum alloy composition which is capable of '' acquire a microstructure reinforced by dispersion; directing a low energy density laser beam onto a part of the powder having the composition of the alloy; removing the laser beam from the portion of the powdered alloy composition; and cooling the portion of the powdered alloy composition at a speed greater than or equal to about 10 6 ° C per second, thereby forming the dispersion-reinforced aluminum metal alloy. The method is particularly suitable for an alloy having a composition according to the following formula: Al comp Fe a SibX c , in which X represents at least one element chosen from the group consisting of Μη, V, Cr, Mo, W, Nb and Ta ;
    "A" ranges from 2.0 to 7.5 atom%; "B" ranges from 0.5 to 3.0 atom%; "C" ranges from 0.05 to 3.5 atom%; and the balance is aluminum and accidental impurities, provided that the ratio [Fe + Si] / Si is in the range of about 2.0: 1 to 5.0: 1.
    Patent application US2017 / 0211168 discloses a process for manufacturing a light and resistant alloy, performing at high temperature, comprising aluminum, silicon, and iron and / or nickel.
    Patent application EP3026135 describes a molding alloy comprising 87 to 99 parts by weight of aluminum and silicon, 0.25 to 0.4 parts by weight of copper and 0.15 to 0.35 parts by weight of a combination of at least two elements among Mg, Ni and Ti. This molding alloy is adapted to be sprayed with an inert gas to form a powder, the powder being used to form an object by additive laser manufacturing, the object then undergoing a tempering treatment.
    The publication "Characterization of Al-Fe-V-Si heat-resistant aluminum alloy components fabricated by selective laser melting", Journal of Material Research, Vol. 30, No. 10, May 28, 2015, describes the manufacture by SLM of heat-resistant components of composition, in% by weight, Al-8.5Fe-l.3V-l.7Si.
    The publication "Microstructure and mechanical properties of Al-Fe-V-Si aluminum alloy produced by electron beam melting", Materials Science & Engineering A659 (2016) 207-214, describes parts of the same alloy as in the previous article obtained by EBM.
    There is a growing demand for high strength aluminum alloys for the SLM application. 4xxx alloys (mainly AllOSiMg, A17SiMg and A112SÎ) are the most mature aluminum alloys for the SLM application. These alloys offer a very good suitability for the SLM process but suffer from limited mechanical properties.
    The Scalmalloy® (DE102007018123A1) developed by APWorks offers (with a post-production heat treatment of 4 hours at 325 ° C) good mechanical properties at room temperature. However, this solution suffers from a high cost in powder form linked to its high scandium content (~ 0.7% Sc) and to the need for a specific atomization process. This solution also suffers from poor mechanical properties at high temperature, for example greater than 150 ° C.
    The Addalloy ™ developed by NanoAl (W0201800935A1) is an Al Mg Zr alloy. This alloy suffers from limited mechanical properties with a hardness peak of around 130 HV.
    The mechanical properties of the aluminum parts obtained by additive manufacturing depend on the alloy forming the filler metal, and more precisely on its composition, on the parameters of the additive manufacturing process as well as on the heat treatments applied. The inventors have determined an alloy composition which, used in an additive manufacturing process, makes it possible to obtain parts having remarkable characteristics. In particular, the parts obtained according to the present invention have improved characteristics compared to the prior art (in particular an 8009 alloy), in particular in terms of hot hardness (for example after 1 h at 400 ° C.).
    STATEMENT OF THE INVENTION A first object of the invention is a method of manufacturing a part comprising the formation of successive solid metal layers, superimposed on each other, each layer describing a pattern defined from a digital model, each layer being formed by the deposition of a metal, called filler metal, the filler metal being subjected to an energy supply so as to enter into fusion and to constitute, by solidifying, said layer , in which the filler metal takes the form of a powder, the exposure of which to an energy beam results in a fusion followed by a solidification so as to form a solid layer, the method being characterized in that the metal filler is an aluminum alloy comprising at least the following alloying elements:
    - Ni, according to a mass fraction of 1% to 6%, preferably from 2 to 5.5%;
    - Cr, according to a mass fraction of 1% to 7%, preferably from 3 to 6.5%;
    - Zr, according to a mass fraction of 0.5 to 4%, preferably from 1 to 3%;
    - Fe, according to a mass fraction less than or equal to 1%, preferably from 0.05 to 0.5%, more preferably from 0.1 to 0.3%;
    - If, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.5%.
    It should be noted that the alloy according to the present invention can also include:
    - impurities according to a mass fraction of less than 0.05% each (ie 500 ppm) and less than 0.15% in total;
    - the rest being aluminum.
    Preferably, the alloy according to the present invention comprises a mass fraction of at least 85%, more preferably of at least 90% of aluminum.
    The melting of the powder can be partial or total. Preferably, from 50 to 100% of the exposed powder melts, more preferably from 80 to 100%.
    Optionally, the alloy may also include Cu in a mass fraction of 0 to 8%, preferably 0 to 6%.
    Optionally, the alloy can also include at least one element chosen from: Ti, W, Nb, Ta, Y, Yb, Nd, Er, Mn, Hf, Ce, Sc, V, Co, La and / or mischmetal, according to a mass fraction less than or equal to 5%, preferably less than or equal to 3% each, and less than or equal to 15%, preferably less than or equal to 12%, even more preferably less than or equal to 5% in total. However, in one embodiment, the addition of Sc is avoided, the preferred mass fraction of Sc then being less than 0.05%, and preferably less than 0.01%.
    These elements can lead to the formation of dispersoids or fine intermetallic phases to increase the hardness of the material obtained.
    Optionally, the alloy can also comprise at least one element chosen from: Sr, Ba, Sb, Bi, Ca, P, B, In and / or Sn, according to a mass fraction less than or equal to 1%, of preferably less than or equal to 0.1%, even more preferably less than or equal to 700 ppm each, and less than or equal to 2%, preferably less than or equal to 1% in total. However, in one embodiment, the addition of Bi is avoided, the preferred mass fraction of Bi then being less than 0.05%, and preferably less than 0.01%.
    Optionally, the alloy can also comprise at least one element chosen from: Ag according to a mass fraction of 0.06 to 1%, Li according to a mass fraction of 0.06 to 1%, and / or Zn according to a mass fraction of 0.06 to 1%. These elements can act on the resistance of the material by hardening precipitation or by their effect on the properties of the solid solution.
    Optionally, the alloy can also comprise Mg according to a mass fraction of at least 0.06% and at most 0.5%. However, the addition of Mg is not recommended and the Mg content is preferably kept below an impurity value of 0.05% by mass.
    Optionally, the alloy can also comprise at least one element for refining the grains and avoiding a coarse columnar microstructure, for example AlTiC or A1TÎB2 (for example in AT5B or AT3B form), in an amount less than or equal to 50 kg / tonne, preferably less than or equal to 20 kg / tonne, even more preferably less than or equal to 12 kg / tonne each, and less than or equal to 50 kg / tonne, preferably less than or equal to 20 kg / tonne in total.
    According to one embodiment, the method may include, following the formation of the layers:
    - dissolution followed by quenching and tempering, or
    - a heat treatment typically at a temperature of at least 100 ° C and at most 400 ° C,
    - and / or hot isostatic compression (CIC).
    The heat treatment can in particular allow a dimensioning of the residual stresses and / or an additional precipitation of hardening phases.
    The CIC treatment can in particular make it possible to improve the elongation properties and the fatigue properties. Hot isostatic compression can be performed before, after or in place of the heat treatment.
    Advantageously, the hot isostatic compression is carried out at a temperature of 250 ° C to 550 ° C and preferably from 300 ° C to 450 ° C, at a pressure of 500 to 3000 bars and for a period of 0, 5 to 10 hours.
    Heat treatment and / or hot isostatic compression makes it possible in particular to increase the hardness of the product obtained.
    According to another embodiment, suitable for structural hardening alloys, it is possible to carry out a solution followed by quenching and tempering of the formed part and / or hot isostatic compression. The hot isostatic compression can in this case advantageously replace the dissolution. However, the process according to the invention is advantageous because it preferably does not require a solution treatment followed by quenching. Dissolution can have a detrimental effect on the mechanical resistance in certain cases by participating in a magnification of the dispersoids or of the fine intermetallic phases.
    According to one embodiment, the method according to the present invention also optionally comprises a machining treatment, and / or a chemical, electrochemical or mechanical surface treatment, and / or a tribofinishing. These treatments can be carried out in particular to reduce the roughness and / or improve the corrosion resistance and / or improve the resistance to the initiation of fatigue cracks.
    Optionally, it is possible to carry out mechanical deformation of the part, for example after additive manufacturing and / or before the heat treatment.
    A second object of the invention is a metal part, obtained by a method according to the first object of the invention.
    A third object of the invention is a powder comprising, preferably consisting of, an aluminum alloy comprising at least the following alloying elements:
    - Ni, according to a mass fraction of 1% to 6%, preferably from 2 to 5.5%;
    - Cr, according to a mass fraction of 1% to 7%, preferably from 3 to 6.5%;
    - Zr, according to a mass fraction of 0.5 to 4%, preferably from 1 to 3%;
    - Fe, according to a mass fraction less than or equal to 1%, preferably from 0.05 to 0.5%, more preferably from 0.1 to 0.3%;
    - If, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.5%.
    It should be noted that the alloy according to the present invention may also include:
    - impurities according to a mass fraction of less than 0.05% each (ie 500 ppm) and less than 0.15% in total;
    - the rest being aluminum.
    The aluminum alloy of the powder according to the present invention can also include:
    Optionally Cu in a mass fraction of 0 to 8%, preferably 0 to%; and / or optionally at least one element chosen from: Ti, W, Nb, Ta, Y, Yb, Nd, Er, Mn, Hf, Ce, Sc, V, Co, La and / or mischmetal, depending on a mass fraction less than or equal to 5%, preferably less than or equal to 3% each, and less than or equal to 15%, preferably less than or equal to 12%, even more preferably less than or equal to 5% in total. However, in one embodiment, the addition of Sc is avoided, the preferred mass fraction of Sc then being less than 0.05%, and preferably less than 0.01%. ; and / or optionally at least one element chosen from: Sr, Ba, Sb, Bi, Ca, P, B, In, and / or Sn, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.1%, even more preferably less than or equal to 700 ppm each, and less than or equal to 2%, preferably less than or equal to 1% in total. However, in one embodiment, the addition of Bi is avoided, the preferred mass fraction of Bi then being less than 0.05%, and preferably less than 0.01%. ; and / or optionally, at least one element chosen from: Ag according to a mass fraction of 0.06 to 1%, Li according to a mass fraction of 0.06 to 1%, and / or Zn according to a mass fraction of 0.06 to 1%; and / or optionally, Mg according to a mass fraction of at least 0.06% and at most 0.5%. However, the addition of Mg is not recommended and the Mg content is preferably kept below an impurity value of 0.05% by mass; and / or optionally at least one element chosen to refine the grains and avoid a coarse columnar microstructure, for example AlTiC or A1TÎB2 (for example in AT5B or AT3B form), in an amount less than or equal to 50 kg / tonne, preferably less than or equal to 20 kg / tonne, even more preferably less than or equal to 12 kg / tonne each, and less than or equal to 50 kg / tonne, preferably less than or equal to 20 kg / tonne in total.
    Other advantages and characteristics will emerge more clearly from the description which follows and from nonlimiting examples, and shown in the figures listed below.
    Brief description of the drawings [fig. 1] is a diagram illustrating an additive manufacturing process of the SLM, or EBM type.
    [Fig.2] shows a micrograph of a cross section of a sample A110Si0.3Mg after surface scanning with a laser, cut and polished with two Knoop impressions in the recast layer.
    Description of the invention [0050] In the description, unless otherwise indicated:
    - the designation of aluminum alloys conforms to the nomenclature established by The Aluminum Association;
    - the contents of chemical elements are designated in% and represent mass fractions.
    Figure 1 generally describes an embodiment, in which the additive manufacturing method according to the invention is implemented. According to this process, the filler material 25 is in the form of an alloy powder according to the invention. An energy source, for example a laser source or an electron source 31, emits an energy beam for example a laser beam or an electron beam 32. The energy source is coupled to the filler material by an optical system or electromagnetic lenses 33, the movement of the beam can thus be determined as a function of a digital model M. The energy beam 32 follows a movement along the longitudinal plane XY, describing a pattern depending on the digital model M The powder 25 is deposited on a support 10. The interaction of the energy beam 32 with the powder 25 generates a selective melting of the latter, followed by solidification, resulting in the formation of a layer 20i ... 20 n . When a layer has been formed, it is covered with powder 25 of the filler metal and another layer is formed, superimposed on the layer previously produced. The thickness of the powder forming a layer can for example be from 10 to 100 μm. This mode of additive manufacturing is typically known as selective laser melting (SLM) when the energy beam is a laser beam, the process in this case being advantageously carried out at atmospheric pressure, and under the name of electron beam melting (EBM) when the energy beam is an electron beam, the process being in this case advantageously carried out at reduced pressure, typically less than 0.01 bar and preferably less at 0.1 mbar.
    In another embodiment, the layer is obtained by selective laser sintering (selective laser sintering, SLS or direct metal laser sintering, DMLS), the layer of alloy powder according to the invention being selectively sintered according to the digital model chosen with thermal energy supplied by a laser beam.
    In yet another embodiment not described in Figure 1, the powder is sprayed and melted simultaneously by a generally laser beam. This process is known as laser melting deposition.
    Other methods can be used, in particular those known under the names of direct energy deposition (Direct Energy Deposition, DED), direct metal deposition (Direct Metal Deposition, DMD), direct laser deposition (Direct Laser Deposition, DLD), Laser Deposition Technology, Laser Metal Deposition, Laser Engineering Net Shaping (LENS), plating technology laser (Laser Cladding Technology, LCT), or laser freeform manufacturing technology (LEMT).
    In one embodiment, the method according to the invention is used for the production of a hybrid part comprising a part 10 obtained by conventional methods of rolling and / or spinning and / or molding and / or optional forging followed by machining and an integral part 20 obtained by additive manufacturing. This embodiment can also be suitable for repairing parts obtained by conventional methods.
    One can also, in one embodiment of the invention, use the method according to the invention for the repair of parts obtained by additive manufacturing.
    At the end of the formation of the successive layers, a raw part or part in the raw manufacturing state is obtained.
    The metal parts obtained by the method according to the invention are particularly advantageous because they have a hardness in the raw state of manufacture lower than that of a reference in 8009, and at the same time a hardness after a higher heat treatment. to that of a reference in 8009. Thus, unlike alloys according to the prior art such as alloy 8009, the hardness of the alloys according to the present invention increases between the raw state of manufacture and the state after a heat treatment . The lower hardness in the raw state of manufacture of the alloys according to the present invention compared to an alloy 8009 is considered to be advantageous for the suitability for the SLM process, by inducing a lower level of stresses during the SLM manufacture and thus lower sensitivity to hot cracking. The higher hardness after a heat treatment (for example 1 h at 400 ° C.) of the alloys according to the present invention compared to an alloy 8009 provides better thermal stability. The heat treatment could be a post-fabrication SLM hot isostatic compression (CIC) step. Thus, the alloys according to the present invention are softer in the raw state of manufacture but have better hardness after heat treatment, hence better mechanical properties for the parts in service.
    The Knoop hardness HK0.05 in the raw state for manufacturing the metal parts obtained according to the present invention is preferably from 150 to 300 HK, more preferably from 160 to 280 HK. Preferably, the Knoop hardness HK0.05 of the metal parts obtained according to the present invention, after a heat treatment of at least 100 ° C and at most 550 ° C and / or a hot isostatic compression, for example after Ih at 400 ° C, is 160 to 330 HK, more preferably 170 to 330 HK. The Knoop hardness measurement protocol is described in the examples below.
    The powder according to the present invention may have at least one of the following characteristics:
    - average particle size from 5 to 100 µm, preferably from 5 to 25 µm, or from 20 to 60 µm. The values given mean that at least 80% of the particles have an average size in the specified range;
    - spherical shape. The sphericity of a powder can for example be determined using a morphogranulometer;
    - good flowability. The flowability of a powder can for example be determined according to ASTM B213 or ISO 4490: 2018. According to ISO 4490: 2018, the flow time is preferably less than 50 s;
    - low porosity, preferably from 0 to 5%, more preferably from 0 to 2%, even more preferably from 0 to 1% by volume. The porosity can in particular be determined by scanning electron microscopy or by helium pycnometry (see standard ASTM B923);
    - absence or small quantity (less than 10%, preferably less than 5% by volume) of small particles (1 to 20% of the average size of the powder), called satellites, which stick to the larger particles.
    The powder according to the present invention can be obtained by conventional methods of atomization from an alloy according to the invention in liquid or solid form or, alternatively, the powder can be obtained by mixing primary powders before l exposure to the energy beam, the different compositions of the primary powders having an average composition corresponding to the composition of the alloy according to the invention.
    It is also possible to add infusible, insoluble particles, for example oxides or TiB 2 particles or carbon particles, to the bath before the powder is atomized and / or during the deposition of the powder and / or when mixing the primary powders. These particles can be used to refine the microstructure. They can also be used to harden the alloy if they are nanometric in size. These particles may be present in a volume fraction of less than 30%, preferably less than 20%, more preferably less than 10%.
    The powder according to the present invention can be obtained for example by atomization by gas jet, plasma atomization, atomization by water jet, atomization by ultrasound, atomization by centrifugation, electrolysis and spheroidization, or grinding and spheroidization.
    Preferably, the powder according to the present invention is obtained by gas jet atomization. The gas jet atomization process begins with the casting of molten metal through a nozzle. The molten metal is then reached by jets of neutral gases, such as nitrogen or argon, and atomized into very small droplets which cool and solidify as they fall inside an atomization tower . The powders are then collected in a can. The gas jet atomization process has the advantage of producing a powder having a spherical shape, in contrast to the water jet atomization which produces a powder having an irregular shape. Another advantage of atomization by gas jet is a good powder density, in particular thanks to the spherical shape and the distribution of particle size. Yet another advantage of this method is good reproducibility of the particle size distribution.
    After its manufacture, the powder according to the present invention can be steamed, in particular in order to reduce its humidity. The powder can also be packaged and stored between its manufacture and its use.
    The powder according to the present invention can in particular be used in the following applications:
    - selective laser sintering (Selective Laser Sintering or SLS);
    - direct metal sintering by laser (Direct Metal Laser Sintering or DMLS in English);
    - selective sintering by heating (Selective Heat Sintering or SHS);
    - selective laser melting (Selective Laser Melting or SLM in English);
    - electron beam fusion (Electron Beam Melting or EBM in English);
    - Laser Melting Deposition in English;
    - direct deposit by energy supply (Direct Energy Deposition or DED in English);
    - direct metal deposition (Direct Metal Deposition or DMD in English);
    - direct laser deposition (DLD in English);
    - Laser deposition technology (LDT);
    - net shape engineering by laser (Laser Engineering Net Shaping or LENS);
    - laser cladding technology (LCT in English);
    - laser freeform manufacturing technology (LEMT in English);
    - deposit by laser fusion (Laser Metal Deposition or LMD in English);
    - cold spraying (Cold Spray Consolidation or CSC in English);
    - additive friction manufacturing (Additive Eriction Stir or ALS);
    - plasma spark sintering or flash sintering (Eield Assisted Sintering Technology, EAST or spark plasma sintering in English); or
    - rotary friction welding (Inertia Rotary Eriction Welding or IREW.
    The invention will be described in more detail in the example below.
    The invention is not limited to the embodiments described in the description above or in the examples below, and can vary widely within the scope of the invention as defined by the claims appended to this description .
    Examples [0070] Two alloys according to the present invention, called Innovl and Innov2, and an alloy 8009 of the prior art were cast in a copper mold using an Induthem VC 650V machine to obtain 130 mm ingots high, 95 mm wide and 5 mm thick. The composition of the alloys is given as a percentage by mass fraction in the following table 1.
    [Tables 1]
    alloys Yes Fe V Or Zr Cr Reference(8009) 1.8 8.65 1.3 - - - Innovl - 0.17 - 3 2 4 Innov2 - 0.21 - 5 2 6
    The alloys as described in table 1 above were tested by a rapid prototyping method. Samples were machined for scanning the surface with a laser, in the form of plates of dimensions 60 × 22 × 3 mm, from the ingots obtained above. The wafers were placed in an SLM machine and scans of the surface were performed with a laser following the same scanning strategy and process conditions representative of those used for the SLM process. It has in fact been found that it is possible in this way to assess the suitability of the alloys for the SLM process and in particular the surface quality, the sensitivity to hot cracking, the hardness in the raw state and the hardness. after heat treatment.
    Under the laser beam, the metal melts in a bath 10 to 350 pm thick. After the laser has passed, the metal cools quickly as in the SLM process. After laser scanning, a thin surface layer 10 to 350 µm thick was melted and then solidified. The properties of the metal in this layer are close to the properties of the metal at the heart of a part manufactured by SLM, because the scanning parameters are carefully chosen. The laser scanning of the surface of the various samples was carried out using a selective laser fusion machine ProX300 from 3DSystems. The laser source had a power of 250 W, the vector deviation was 60 µm, the scanning speed was 300 mm / s and the diameter of the beam was 80 µm.
    Knoop hardness measurement Hardness is an important property for alloys. Indeed, if the hardness in the layer remelted by scanning the surface with a laser is high, a part manufactured with the same alloy will potentially have a high breaking limit.
    To evaluate the hardness of the remelted layer, the wafers obtained above were cut in the plane perpendicular to the direction of the laser passes and were then polished. After polishing, hardness measurements were made in the remelted layer. The hardness measurement was carried out with a Durascan model device from Struers. The Knoop hardness method 50 g with the large diagonal of the impression placed parallel to the plane of the recast layer was chosen to keep enough distance between the impression and the edge of the sample. 15 cavities were positioned halfway through the recast layer. Ligure 2 shows an example of the hardness measurement. Reference 1 corresponds to the recast layer and reference 2 corresponds to a Knoop hardness imprint.
    The hardness was measured according to the Knoop scale with a load of 50 g after laser treatment (in the raw state) and after an additional heat treatment at 400 ° C for variable durations, making it possible in particular to evaluate the 'ability of the alloy to harden during a heat treatment and the effect of a possible CIC treatment on the mechanical properties.
    The Knoop hardness values HK0.05 in the raw state and after different durations at 400 ° C are given in Table 2 below (HK0.05).
    [Tables!]
    Alloy Gross state After Ih at 400 ° C After 4h at400 ° C After 10h at 400 ° C Reference(8009) 316 145 159 155 Innovl 200 221 175 179 Innov2 263 307 290 313
    The alloys according to the present invention (Innovl and Innov2) showed a Knoop hardness HK0.05 in the raw state lower than that of the reference alloy 8009, but, after a heat treatment at 400 ° C, higher to that of the reference alloy 8009.
    On the other hand, the Knoop hardness HK0.05 of the alloy according to the present invention can be increased by the heat treatment of Ih, or even 4h and lOh. On the contrary, the Knoop hardness HK0.05 of the reference in 8009 has been reduced by the heat treatment. The response of the alloy according to the present invention to a heat treatment is thus improved compared to that of a reference alloy in 8009.
    Table 2 above clearly shows the better thermal stability of the alloys according to the present invention compared to the reference alloy 8009. In fact, the hardness of alloy 8009 dropped sharply from the start of the heat treatment, then reached a plateau. On the contrary, the hardness of the alloys according to the present invention first increased and then gradually decreased.
    Finally, it has been found, but not shown here, that the addition of Cu in the alloy according to the present invention can make it possible to further increase the hardness HK0.05 while retaining good thermal stability.
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    claims [Claim 1] Method for manufacturing a part (20) comprising the formation of successive solid metal layers (20i ... 20 n ), superimposed on each other, each layer describing a pattern defined from a digital model (M), each layer being formed by the deposition of a metal (25), called filler metal, the filler metal being subjected to an energy supply so as to enter into fusion and to constitute, by solidifying, said layer , in which the filler metal takes the form of a powder (25), the exposure of which to an energy beam (32) results in a fusion followed by solidification so as to form a solid layer (20L .. 20J, the method being characterized in that the filler metal (25) is an aluminum alloy comprising at least the following alloying elements - Ni, according to a mass fraction of 1% to 6%, preferably 2 at 5.5%; - Cr, according to a mass fraction of 1% to 7%, preferably from 3 to 6.5%; - Zr, salt a mass fraction of 0.5 to 4%, preferably 1 to 3%; - Fe, according to a mass fraction less than or equal to 1%, preferably from 0.05 to 0.5%, more preferably from 0.1 to 0.3%; - If, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.5%. [Claim 2] The method of claim 1, wherein the aluminum alloy also comprises Cu in a mass fraction of 0 to 8%, preferably 0 to 6%. [Claim 3] Method according to any one of the preceding claims, in which the aluminum alloy also comprises at least one element chosen from: Ti, W, Nb, Ta, Y, Yb, Nd, Er, Mn, Hf, Ce, Sc , V, Co, La and / or mischmetal, according to a mass fraction less than or equal to 5%, preferably less than or equal to 3% each, and less than or equal to 15%, preferably less than or equal to 12%, even more preferably less than or equal to 5% in total. [Claim 4] Method according to any one of the preceding claims, in which the aluminum alloy also comprises at least one element chosen from: Sr, Ba, Sb, Bi, Ca, P, B, In and / or Sn, according to a fraction
    mass less than or equal to 1%, preferably less than or equal to 0.1%, even more preferably less than or equal to 700 ppm each, and less than or equal to 2%, preferably less than or equal to 1% in total. [Claim 5] Process according to any one of the preceding claims, in which the aluminum alloy also comprises at least one element chosen from: Ag according to a mass fraction of 0.06 to 1%, Li according to a mass fraction of 0.06 to 1%, and / or Zn according to a mass fraction of 0.06 to 1%. [Claim 6] Process according to any one of the preceding claims, in which the aluminum alloy also comprises at least one element for refining the grains, for example AlTiC or A1TÎB2, in an amount less than or equal to 50 kg / tonne, preferably less or equal to 20 kg / tonne, even more preferably less than or equal to 12 kg / tonne each, and less than or equal to 50 kg / tonne, preferably less than or equal to 20 kg / tonne in total. [Claim 7] Process according to any one of the preceding claims, comprising, following the formation of the layers (20i .. .20 n ): - dissolution followed by quenching and tempering, or - heat treatment typically at a temperature of at least 100 ° C and at most 400 ° C, - and / or hot isostatic compression. [Claim 8] Metal part (20) obtained by a process which is the subject of any one of the preceding claims. [Claim 9] Powder comprising, preferably consisting of, an aluminum alloy comprising:- Ni, according to a mass fraction of 1% to 6%, preferably from 2 to 5.5%;- Cr, according to a mass fraction of 1% to 7%, preferably from 3 to 6.5%;- Zr, according to a mass fraction of 0.5 to 4%, preferably from 1 to 3%;- Fe, according to a mass fraction less than or equal to 1%, preferably from 0.05 to 0.5%, more preferably from 0.1 to 0.3%;- If, according to a mass fraction less than or equal to 1%, preferably less than or equal to 0.5%.
    1/1
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3083479A1|2020-01-10|PROCESS FOR PRODUCING AN ALUMINUM ALLOY PART
    FR3086873A1|2020-04-10|PROCESS FOR MANUFACTURING AN ALUMINUM ALLOY PART
    FR3086872A1|2020-04-10|PROCESS FOR MANUFACTURING AN ALUMINUM ALLOY PART
    FR3077524A1|2019-08-09|PROCESS FOR MANUFACTURING ALUMINUM ALLOY AND CHROME ALLOY
    WO2020152427A1|2020-07-30|Method for manufacturing a part from aluminium alloy, the alloy comprising at least zirconium and magnesium
    EP3821049A1|2021-05-19|Process for manufacturing an aluminum alloy part
    EP3622095B1|2021-04-14|Aluminum alloy part and process for manufacturing thereof
    EP3924124A1|2021-12-22|Method for manufacturing an aluminum alloy part
    FR3082763A1|2019-12-27|PROCESS FOR MANUFACTURING AN ALUMINUM ALLOY PART
    WO2020002813A1|2020-01-02|Process for manufacturing an aluminum alloy part
    WO2020095009A2|2020-05-14|Method for manufacturing an aluminum alloy part
    WO2020058646A1|2020-03-26|Process for manufacturing an aluminum alloy part
    FR3110095A1|2021-11-19|Manufacturing process of an aluminum alloy part
    FR3110097A1|2021-11-19|Manufacturing process of an aluminum alloy part
    FR3103123A1|2021-05-21|Manufacturing process of an aluminum alloy part
    同族专利:
    公开号 | 公开日
    WO2020012098A1|2020-01-16|
    EP3821049A1|2021-05-19|
    US20210269896A1|2021-09-02|
    FR3083478B1|2021-08-13|
    CN112384636A|2021-02-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPS6247449A|1985-08-26|1987-03-02|Toyo Alum Kk|Heat resistant aluminum alloy for powder metallurgy and its manufacture|
    EP0341714A1|1988-05-12|1989-11-15|Sumitomo Electric Industries, Ltd.|Method of forming large-sized aluminum alloy product|
    US20170016096A1|2015-07-16|2017-01-19|Hamilton Sundstrand Corporation|Method of manufacturing aluminum alloy articles|
    DE102007018123B4|2007-04-16|2009-03-26|Eads Deutschland Gmbh|Method for producing a structural component from an aluminum-based alloy|
    US9267189B2|2013-03-13|2016-02-23|Honeywell International Inc.|Methods for forming dispersion-strengthened aluminum alloys|
    KR20160028469A|2013-07-10|2016-03-11|알코아 인코포레이티드|Methods for producing forged products and other worked products|
    TWI530569B|2014-11-21|2016-04-21|財團法人工業技術研究院|Alloy casting material and method for manufacturing alloy object|
    WO2016209652A1|2015-06-15|2016-12-29|Northrop Grumman Systems Corporation|Additively manufactured high-strength aluminum via powder bed laser processes|
    US10294552B2|2016-01-27|2019-05-21|GM Global Technology Operations LLC|Rapidly solidified high-temperature aluminum iron silicon alloys|
    CN106055162B|2016-06-30|2019-05-03|京东方科技集团股份有限公司|Display component and display device|DE102020208086A1|2020-06-30|2021-12-30|Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung eingetragener Verein|Component made of an aluminum-nickel alloy as well as the process for its manufacture and its use|
    CN113293316A|2021-04-16|2021-08-24|中国科学院金属研究所|Method for efficiently improving refining capacity of Al-5Ti-1B intermediate alloy|
    法律状态:
    2019-07-25| PLFP| Fee payment|Year of fee payment: 2 |
    2020-01-10| PLSC| Search report ready|Effective date: 20200110 |
    2020-07-27| PLFP| Fee payment|Year of fee payment: 3 |
    2021-07-26| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1870822A|FR3083478B1|2018-07-09|2018-07-09|METHOD OF MANUFACTURING AN ALUMINUM ALLOY PART|FR1870822A| FR3083478B1|2018-07-09|2018-07-09|METHOD OF MANUFACTURING AN ALUMINUM ALLOY PART|
    CN201980046235.5A| CN112384636A|2018-07-09|2019-07-08|Method for manufacturing aluminum alloy parts|
    EP19790618.3A| EP3821049A1|2018-07-09|2019-07-08|Process for manufacturing an aluminum alloy part|
    PCT/FR2019/051685| WO2020012098A1|2018-07-09|2019-07-08|Process for manufacturing an aluminum alloy part|
    US17/258,652| US20210269896A1|2018-07-09|2019-07-08|Process for manufacturing an aluminum alloy part|
    [返回顶部]