WO2025087901A1 - Alliage d'aluminium - Google Patents

Alliage d'aluminium Download PDF

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Publication number
WO2025087901A1
WO2025087901A1 PCT/EP2024/079827 EP2024079827W WO2025087901A1 WO 2025087901 A1 WO2025087901 A1 WO 2025087901A1 EP 2024079827 W EP2024079827 W EP 2024079827W WO 2025087901 A1 WO2025087901 A1 WO 2025087901A1
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scandium
zirconium
less
aluminium alloy
hafnium
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Inventor
Rory Hans Jacob ROSE
Farsad FORGHANI
Shohreh Khorsand
Charles Nicholas PEARSON
Onuh John ADOLE
Dylan Nesta HALL
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Alloyed Ltd
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Alloyed Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y70/00—Materials specially adapted for additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0408—Light metal alloys
    • C22C1/0416—Aluminium-based alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent

Definitions

  • AlSiOlMg is an aluminium alloy comprising about 10 wt.% silicon and about 0.5 wt.% magnesium. This alloy is well suited to additive manufacturing and exhibits little spatter. However, the high-temperature (300°C) yield strength and ultimate tensile strength are disappointing at about 70 MPa.
  • Scalmalloy has very high room temperature yield strength and ultimate tensile strength after T5 aging (e.g. at 325°C for Scalmalloy ) conducted for a few hours (e.g. 4 hours). The microcracking performance of this alloy during additive manufacturing is reasonable, however the alloy suffers from poor spatter performance. Additionally, the high-temperature yield strength and ultimate tensile strength are disappointing. Scalmalloy has less than 0.2 wt.% iron, about 0.3 wt.% zirconium, about 0.7 wt.% scandium, and about 5 wt.% magnesium with a very small addition of silicon.
  • the present invention relates to an aluminium alloy which has a unique balance of high- temperature strength combined with resistance to microcracking during additive manufacturing and spatter performance.
  • the present invention provides an aluminium alloy comprising (or consisting of): 0.45 to 1.1 wt.% iron; at least two of erbium, hafnium, niobium, titanium, scandium, zirconium in an amount of up to 0.6wt% each; and erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.4 to 1.2wt; 0.5 to 2.5 wt.% magnesium; 0.9 to 3.0 sum of one or more of the elements selected from the list: manganese, chromium, molybdenum, vanadium, cobalt; 0.0 to 0.45 sum of one or more of the elements selected from the list: silicon, copper, calcium, nickel; the balance being aluminium and unavoidable impurities with a total of less than 0.5 wt.%.
  • the alloy comprises 2.0 wt.% or less magnesium, preferably 1.9 wt.% or less magnesium, more preferably 1.8 wt.% or less magnesium, even more preferably 1.6 wt.% or less magnesium and most preferably 1.5 wt.% or less magnesium.
  • Such an alloy is more resistant to spatter.
  • the alloy comprises 0.55 wt.% or more magnesium, preferably 1.0 wt.% or more magnesium, more preferably 1.35 wt.% or more magnesium, most preferably 1.4 wt.% or more magnesium.
  • Such an alloy has higher strength.
  • the alloy comprises 0.55 wt.% or less scandium, preferably 0.5wt.% or less scandium and more preferably 0.475 wt.% of scandium.
  • Such an alloy has higher high temperature strength after heat treatment.
  • the alloy comprises 0.55 wt.% of zirconium, preferably 0.5wt.% or less zirconium and more preferably 0.475 wt.% of zirconium.
  • zirconium preferably 0.55 wt.% of zirconium, preferably 0.5wt.% or less zirconium and more preferably 0.475 wt.% of zirconium.
  • Such an alloy has higher high temperature strength after heat treatment.
  • the alloy comprises 0.95 wt.% or less iron, preferably 0.9 wt.% or less iron, preferably 0.8 wt.% or less iron, more preferably 0.75 wt.% or less iron, most preferably 0.7 wt.% or less iron.
  • Such an alloy is more resistant to cold cracking.
  • the alloy comprises 1.0 wt.% or more of sum of one or more of the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt, preferably 1.1 wt.% or more sum of one or more of the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt, more preferably 1.5 wt.% or more sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt.
  • Such an alloy has increased strength.
  • the alloy comprises 2.5 wt.% or less sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt, preferably 2.25 wt.% or less sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt, more preferably 2.0 wt.% or less sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt, and most preferably 1.9 wt.% or less sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt.
  • Such an alloy increased ductility and so suffers even less from cold cracking.
  • the alloy comprises 0.2wt.% or more scandium, preferably 0.25 wt.% or more scandium, more preferably 0.3 wt.% or more scandium, more preferably 0.35 wt.% or more scandium, most preferably 0.4 wt.% for more scandium.
  • Such an alloy has increase strength without suffering an increase in cold cracking.
  • the alloy comprises 0.2wt% or more scandium, preferably 0.25 wt.% or more zirconium, more preferably 0.3 wt.% or more zirconium, more preferably 0.35 wt.% or more zirconium, most preferably 0.4 wt.% for more zirconium.
  • Such an alloy has increase strength without suffering an increase in cold cracking.
  • the alloy comprises 0.5 wt.% or more of iron, preferably 0.55 wt.% or more of iron, and most preferably 0.6 wt.% or more of iron. Such an alloy has increased strength.
  • the alloy comprises a sum of zirconium and scandium in wt.% of 0.4wt.% or more, preferably 0.6 wt.% or more, more preferably 0.8 wt.% or more and most preferably 0.85 wt.% or more.
  • Such an alloy has increased strength.
  • the alloy comprises scandium and zirconium. These are the most preferred elements to offer strengthening after heat treatment but which advantageously tend to stay mostly in solid solution during additive manufacture.
  • the alloy comprises at least two of erbium, hafnium, niobium, titanium, scandium, zirconium in an amount of 0.55wt.% or more each, preferably of 0.5wt.% or more each and most preferably of 0.475wt.% or more each. Such an alloy has increased strength.
  • the alloy comprises erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.5wt% or more, preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.6wt% or more, more preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.7wt% or more, more preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.8wt% or more, most preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.85wt% or more.
  • Such an alloy has increased strength.
  • the alloy comprises erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 1.1 wt% or less, preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 1.0wt% or less, more preferably containing erbium, hafnium, niobium, titanium, scandium, zirconium in total sum of 0.95wt% or less.
  • Such an alloy is less likely to suffer from significant A13X precipitation during additive manufacture.
  • At least two, preferably three are present in an amount of 0.25wt.% or more each, preferably wherein of those elements of erbium, hafnium, niobium, titanium, scandium and zirconium present, at least two, preferably three, are present in an amount of 0.3wt% or more each and most preferably wherein of those elements of erbium, hafnium, niobium, titanium, scandium and zirconium present, at least two, preferably three, are present in an amount of in an amount of 0.35wt% or more each.
  • Such an alloy has increased strength.
  • the microstructure of the alloy has a uniform dispersion of transition metal dispersoids, with the majority of any scandium, zirconium, erbium, hafnium, niobium and titanium in solid solution with optionally some primary precipitation of A13X where X is one or more of scandium, zirconium, erbium, hafnium, niobium and titanium.
  • transition metal dispersoids with the majority of any scandium, zirconium, erbium, hafnium, niobium and titanium in solid solution with optionally some primary precipitation of A13X where X is one or more of scandium, zirconium, erbium, hafnium, niobium and titanium.
  • the microstructure of the alloy comprises transition metal dispersoids and a dispersion of A13X precipitates homogeneously through the microstructure where X is one or more of scandium, zirconium, erbium, hafnium, niobium and titanium with optionally some primary precipitation of A13X where X is one or more of scandium, zirconium, erbium, hafnium, niobium and titanium.
  • Such an alloy has high temperature strength yet can be manufactured by additive manufacturing followed by heat treatment, without cold cracking.
  • Figure 1 is a graph showing a calculated strength index of aluminium alloys with addition of various elements in varying quantities
  • Figure 2 shows results showing the increase in yield strength (converted from hardness) with increasing iron content in an aluminium-iron alloy
  • Figure 3 is a micrograph showing a crack in an additively manufactured article from an aluminium alloy comprising 1.2 wt% iron, balance aluminium;
  • Figure 4 shows results showing the yield strength converted from hardness in a different alloys comprising aluminium, magnesium, scandium and zirconium.
  • the x axis represents the sum of scandium and zirconium in the alloy and the y axis the yield strength;
  • Figure 5 shows formation of primary A13X precipitates in an aluminium-0.7 wt.% Sc - 0.6 wt.% Zr (ABD-S420) in the as additive manufactured state;
  • Figure 6 shows results showing the increase in yield strength (converted from hardness) with increasing magnesium content in an aluminium-magnesium alloy;
  • Figure 7 shows the variation in solidus temperature for a series of aluminium alloys alloyed with different elements and in different amounts where 0 wt.% represents the composition in the range of example alloy 1 (M420) without any of the element.
  • M420 without magnesium has solidus around 650 °C and boiling point around 2500 °C;
  • Figure 8 shows the variation in boiling temperature of aluminium alloys when alloyed with different elements and in different amounts where 0 wt.% represents the composition in the range of example alloy 1 (M420) without any of the element as in figure 7;
  • Figure 9 shows on the y axis the influence on elongation in an aluminium alloy of several different elements in varying amounts on the x axis
  • Figure 10 shows results showing the increase in yield strength (converted from hardness) with increasing manganese content in an aluminium-manganese alloy
  • Figure 11 shows results showing the increase in yield strength (converted from hardness) with increasing cobalt content in an aluminium-cobalt alloy
  • Figure 12 shows experimental results of variation in yield strength with temperature for different alloys of aluminium in different heat-treated states.
  • High-temperature aluminium alloys for example aluminium alloys with a yield strength of above 175 MPa at 250°C are generally dispersion strengthened alloys in which micro-scale dispersoids are uniformly distributed in the microstructure. In the as formed state, this alloy has a uniform dispersion of sub-micron transition metal dispersoids through the meltpool.
  • These phases are characterised using scanning electron microscopy with mean (area) equivalent circle diameter of less than 1pm, preferably less than 500nm and more preferably less than 200nm. The majority of Sc and Zr are in solid solution with potentially some primary precipitation of A13X.
  • the dispersoids are slightly coarsened and there is a fine dispersion of nanoscale A13X precipitates homogeneously through the microstructure (i.e. these phases are characterised using scanning electron microscopy with mean (area) equivalent circle diameter of less than lOnm and more preferably less than 5nm). Mg is always in solid solution in both conditions.
  • Hot cracks can develop during solidification of deposited alloy and typically propagate between grains of the material. Hot cracks are primarily controlled by the solidification behaviour of the alloy including the solidification range and size of grains. Alloys with wide solidification ranges and large grains tend to suffer more from hot cracking. Hot cracking can be prevented in the present alloy using conventional approaches. Cold cracks (sometimes called delayed cracks) on the other hand are less understood and develop after solidification, form as a result of residual stresses caused by thermal contraction and propagate between both grains and through grains. Cold cracks are particularly important for producing complex and large geometries as residual stresses build up as more material is printed and are exacerbated by sharp cross section changes which concentrate stress.
  • the present inventors have developed several insights in aluminium alloy design to enable a high-temperature aluminium alloy to be formed by additive manufacturing with improved resistance to cracking and with lower chance of spatter.
  • the insights made by the inventors include:
  • Alloying elements are limited to avoid a large drop in ductility (which would otherwise result in cold cracking)
  • the inventors have devised a composition which utilises the above insights (which in some cases compete with each other) to develop the aluminium alloy of the present invention.
  • Figure l is a graph showing predicted strength index which was generated based on experimental results and literature data which considers microstructural characteristics of the alloys, indicating the relative strengthening effect of several common alloying elements, within the composition space considered, used to increase the strength of aluminium through the formation of dispersoids.
  • This graph and the results in figures 2,4,6,10 and 11 are for specimens prepared by casting and scanning a laser on the cast surface to imitate the process microstructure and cooling rate of additive manufacture
  • iron is a common alloying element in aluminium alloys.
  • Figure 2 shows how increasing amounts of iron at least up to 4% significantly increases the yield strength of an aluminium alloy.
  • a minimum amount of 0.45 wt.% iron is added to the alloy of the present invention to take advantage of iron’s strong influence on tensile strength.
  • iron is present in an amount of 0.50 wt% or more, and more preferably 0.55 wt% or more, or even 0.60 wt% or more, further to increase the tensile strength of the alloy. On the face of it therefore, increasing the iron content of the aluminium alloy is advantageous.
  • Table 2 confirms that for alloy Al-1.2Fe, a reasonable high-temperature yield strength and ultimate tensile strength is achieved for an alloy with 1.2wt.% iron.
  • the present inventors have found that increasing the amount of iron in the alloy can result in cracking due to the formation of dispersoids during the additive manufacturing process which leads to the reduction in ductility. Iron was also found to increase in the thermal expansion coefficient; increasing residual stresses.
  • Figure 3 is micrograph of a cold crack which developed in an aluminium alloy comprising 1.2 wt.% iron (example Al-1.2Fe of tables 1 and 2) additively manufactured.
  • the amount of iron is limited to 1.1 wt% or less at which level microcrack due to cold cracking are not expected to form.
  • Example alloy ABD-M420 which has an amount of iron of 0.72 wt.%, is shown in Table 2 to achieve an acceptable level of microcrack tolerance (0.8).
  • the amount of iron is preferably reduced further to a maximum of 0.95 wt.% or less or even 0.8wt.% or less or 0.75 wt.% or less.
  • the present inventors have sought ways further to increase the high-temperature yield strength and ultimate tensile strength and in order to do this, the inventors investigated adding further alloying elements to add to the aluminium-iron alloy.
  • Figure 1 scandium and zirconium strongly increase the strength of an aluminium alloy, particularly at low concentrations.
  • Figure 4 shows the measured yield strength of various aluminium-magnesium-zirconium-scandium alloys plotted against the sum of scandium and zirconium content. This shows a more or less linear increase in yield strength with sum of scandium and zirconium, due to dispersoid formation.
  • the inventors have found that if scandium and zirconium are each limited to 0.6 wt%, A13X type precipitates do not appear to be stable during the additive manufacturing process (the metastable state is that scandium and zirconium remain in solid solution). This means that the aluminium alloy can be formed into a product using additive manufacturing without precipitation of scandium and zirconium dispersoids, thereby meaning that scandium and zirconium do not contribute to a reduction in ductility during additive manufacturing.
  • the scandium and zirconium can then be formed into nanoscale precipitates during T5 heat treatment (e.g. 400 C for 4h for ABD-M420). That is, the metastable state at concentrations of up to 0.6 wt.% of scandium and up to 0.6wt.% of zirconium appears to be solid solution.
  • T5 heat treatment e.g. 400 C for 4h for ABD-M420.
  • scandium is present in an amount of 0.55 wt.% or less or 0.5wt.% or less and/or zirconium is preferably present in an amount of 0.55 wt.% or less or 0.5wt.% or less.
  • scandium is limited to 0.475 wt.% or less and/or zirconium is limited to 0.475 wt.% or less.
  • the aluminium alloy comprises a sum of zirconium and scandium in wt.% of 0.6 wt.% or more, preferably 0.8 wt.% or more and most preferably 0.85 wt.% or more.
  • the alloy contains at least two of erbium, hafnium, titanium, scandium, niobium and zirconium in an amount of up to 0.6wt% each, and a sum of erbium, hafnium, titanium, scandium, niobium and zirconium in of 0.4 to 1.2wt.%.
  • the alloy contains at least two of erbium, hafnium, titanium, scandium and zirconium in an amount of up to 0.6wt% each, and a sum of erbium, hafnium, titanium, scandium and zirconium in of 0.4 to 1.2wt.%.
  • Scandium and zirconium are the most preferred of those alloying elements. The best properties are achieved by Sc and Zr due to a core shell type precipitate where advantage is taken of the combination of very high nucleation rate from Sc and a low growth rate due to the Zr shell.
  • At least two, preferably three are present in an amount of 0.25wt.% or more each, preferably 0.3wt% or more each and most preferably in an amount of 0.35wt% or more each.
  • at least two, preferably three are present in an amount of 0.25wt.% or more each, preferably 0.3wt% or more each and most preferably in an amount of 0.35wt% or more each.
  • the aluminium alloy comprises a sum of erbium, hafnium, titanium, scandium, niobium and zirconium in wt.% of 0.5 wt.% or more, preferably 0.6 wt.% or more, more preferably 0.7wt/% or more, more preferably 0.8 wt.% or more and most preferably 0.85 wt.% or more.
  • the aluminium alloy comprises a sum of erbium, hafnium, titanium, scandium and zirconium in wt.% of 0.5wt.% or more, preferably 0.6 wt.% or more, more preferably 0.7wt/% or more, more preferably 0.8 wt.% or more and most preferably 0.85 wt.% or more. As the sum increases, the high temperature strengthening effect after heat treatment increases.
  • the aluminium alloy contains aluminium alloy contains at least two of erbium, hafnium, titanium, scandium, niobium zirconium in an amount of 0.55wt.% or more each, preferably of 0.5wt.% or more each and most preferably of 0.475wt.% or more each.
  • the aluminium alloy contains aluminium alloy contains at least two of erbium, hafnium, titanium, scandium, zirconium in an amount of 0.55wt.% or more each, preferably of 0.5wt.% or more each and most preferably of 0.475wt.% or more each.
  • the aluminium alloy contains erbium, hafnium, titanium, scandium, niobium, zirconium in total sum of 1.1 wt% or less, preferably containing erbium, hafnium, titanium, scandium, niobium, zirconium in total sum of 1.0wt% or less, more preferably containing erbium, hafnium, titanium, scandium, niobium, zirconium in total sum of 0.95wt% or less.
  • the aluminium alloy contains erbium, hafnium, titanium, scandium, zirconium in total sum of 1.1 wt% or less, preferably containing erbium, hafnium, titanium, scandium, zirconium in total sum of 1.0wt% or less, more preferably containing erbium, hafnium, titanium, scandium, zirconium in total sum of 0.95wt% or less.
  • Such alloys have reduced propensity to for A13X type primary precipitates. The formation of such precipitates is preferably avoided as they tend to use up these elements and so reduce the precipitation of fine A13X precipitates after heat treatment.
  • titanium can be present in a sum of 0.2wt% or less, preferably in a sum of erbium, hafnium, niobium, titanium of 0.1 wt% or less, more preferably in a sum of erbium, hafnium, niobium, titanium of 0.05wt% or less, and in an embodiment even being substantially free of erbium, hafnium, niobium and titanium.
  • hafnium is expensive and as mentioned elsewhere, the combination of zirconium and scandium achieves very fine precipitates.
  • the alloy is substantially free of niobium except the extent to which it is present as an unavoidable impurity.
  • erbium, hafnium titanium can be present in a sum of 0.2wt% or less, preferably in a sum of erbium, hafnium, titanium of 0.1 wt% or less, more preferably in a sum of erbium, hafnium, titanium of 0.05wt% or less, and in an embodiment even being substantially free of erbium, hafnium and titanium.
  • Figure 1 shows the beneficial effect of magnesium on the ultimate tensile strength and it provides strength without sacrificing ductility. Many commercial aluminium alloys contain magnesium because of this effect.
  • Figure 6 shows experimentally the increase in yield strength (based on a conversion from measured hardness) achieved by adding increasing amounts of magnesium into aluminium.
  • the present invention contains at least 0.5 wt.% magnesium in order to take advantage of its good strengthening properties.
  • Magnesium also has the effect of reducing the solidus and increasing the work hardening rate of the alloy, which is beneficial in avoiding cold-cracking.
  • excessive amounts of magnesium have been found by the present inventors to result in poor spatter performance. This can be seen in Table 2 in the case of AlMgTy90 which contains 13.8 wt.% magnesium and in scalmalloy which contains 4.7 wt.% magnesium.
  • the inventors have determined that the mechanism for spatter appears to be the formation of vapour plumes and these result in spatter defects.
  • the vapour plumes occur due to the lowering of the boiling temperature of the alloy resulting from the addition of magnesium.
  • the effect of reduction in boiling point by magnesium compared to other alloying elements for ABD-M420 is illustrated in Figure 8 which is generated using CALPHAD predictions of the temperature for 1% of Gas phase assuming equilibrium conditions.
  • magnesium avoids the difficulty with spatter.
  • magnesium is limited to 2.0 wt.% or less. It can be seen from Figure 8 that reducing the magnesium content even further will further increase the boiling point of the alloy, thereby reducing the chance of spatter. Therefore, reducing the magnesium content to 1.9 wt.% or less or 1.8 wt.% or less or even 1.6 wt.% or less will have advantages in reducing the chance of spatter.
  • magnesium is limited to 1.5 wt.% or less. As can be seen in Figure 8, at such a concentration the deleterious effect of magnesium in lowering the boiling temperature of the alloy is the same as that of the other main alloying elements used in the present invention.
  • Figure 7 shows the reducing effect magnesium has on the solidus temperature.
  • the inventors have found that magnesium has an even greater effect on reducing the non- equilibrium solidus temperature than the equilibrium solidus illustrated in figure 7. This appears to be the result of the change and shape of the Sheil curve. This lowers the residual stress in the additively manufactured product, thereby resulting in less cold-cracking.
  • magnesium is present in an amount of 0.5 wt.% or more. Adding more magnesium further increases those effects so that preferably magnesium is added in an amount of 0.55 wt.% or more and more preferably 1.0 wt.% or more. In an embodiment magnesium is added in an amount of 1.35 wt.% or more to make the most of the advantages in reducing cold-cracking offered by magnesium additions.
  • Figure 9 shows the negative impact of elongation (a ductility drop) of the concerned elements. This index is generated by combining experimental and literature data to account for the effect of microstructural characteristics on elongation utilising CALPHAD predicted non-equilibrium microstructures. A drop in ductility is to be avoided as it can lead to cold cracking.
  • Figure 9 shows that silicon has the least impact on ductility although it is clear from Figure 1 that silicon also has the least impact on strength. Therefore, the present invention allows an amount of silicon of up to 0.45 wt%, although this is not preferred.
  • silicon is present in 0.1 wt.% or less and most preferably is excluded from the alloy because it can react with scandium and zirconium and decreasing the strengthening effect of these elements by stopping the formation of the beneficial A13X precipitates during ageing.
  • Nickel is also shown as having a low impact on reduction in ductility in Figure 9. However, like silicon, nickel has a small impact on an increase in strength. Therefore, nickel is allowed up to a maximum of 0.45 wt%, preferably of 0.05 wt% or less, and most desirably the alloy is nickel free.
  • manganese is more preferred than cobalt because cobalt, similar to molybdenum, has been found to increase the melting point of the aluminium alloy greatly. Increasing the melting point of the alloy makes it much harder to atomise an electrode of the alloy in the process for making the powder used in additive manufacturing.
  • Molybdenum is shown in figure 9 to have a low impact on elongation, along with manganese and cobalt.
  • molybdenum is not as strong a strengthening element as either manganese or cobalt (figure 1) and is therefore not preferred.
  • Chromium has a relatively large impact on reducing ductility ( Figure 9) whereas its effect on increasing strength is relatively limited. Therefore, chromium is the least preferred of the group of elements, manganese, chromium, molybdenum, vanadium and cobalt which are present in some in an amount of 3.0wt.% in sum or 2.5 wt% in sum or less.
  • the sum of one or more the elements in the list: manganese, chromium, molybdenum, vanadium, cobalt is 2.25 wt.% or less, even 2.0 wt.% or less and more preferably 1.9 wt.% or less.
  • the sum of manganese, chromium, vanadium, cobalt and molybdenum is preferably 0.9 wt% or more in order to achieve a minimum strengthening effect on the alloy.
  • the sum of those elements is 1.0 wt% or more, preferably 1.1 wt% or more and in one embodiment even 1.5 wt% or more.
  • manganese is chosen from the group of those five elements and is present in an amount of 0.7 wt% or more and/or 2.0 wt% or less.
  • Figures 10 and 11 show the effect on yield strength of manganese and cobalt additions to aluminium. Generally, it shows increasing strength with increasing additions. However, the additions of those elements are limited due to their effect on reducing ductility as explained with reference to Figure 9.
  • the alloy may contain small amounts of other incidental impurities of any element not listed in the above section.
  • these impurities may be unavoidable impurities which are difficult to remove from aluminium.
  • Such impurities may be present with a total amount of less than 0.5 wt.%.
  • Table 1 is a list of the alloys with their composition and Table 2 shows the yield strength, tensile strength and elongation at room-temperature and where measured at high-temperature. The occurrence or not of microcracks and spatter defects is also shown.
  • Alloy ABD-M420 is an alloy of the present invention and exhibits high room temperature YS and UTS, very good high temperature YS and UTS and acceptable elongation at both room temperature and high temperature. The occurrence of microcracks during additive manufacture is limited and the spatter performance is good. None of the other alloys listed in the table perform as well in all those areas.
  • Table 2 Properties of assessed commercial and experimental alloys Table 3 below lists the limits of the present inventive alloy and preferred limits in wt.% for the main alloying elements, with Ti, V, Si, Cu, Ca and Ni being present in sum up to 0.45wt.%, but the alloys are preferably sum less then 0.1 wt.% and most preferably free of Si, Cu, Ca and Ni and in one embodiment free of all six elements. Table 4 lists the even more preferred limits.
  • Table 3 Table 4: Table 5 lists the limits of another specific preferred alloy.

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Abstract

L'invention concerne un alliage d'aluminium comprenant : en pourcentage en poids : 0,45 à 1,1 % en poids de fer; au moins deux éléments parmi l'erbium, l'hafnium, le niobium, le titane, le scandium, le zirconium dans une quantité allant jusqu'à 0,6 % en poids chacun; une somme totale de l'erbium, de l'hafnium, du titane, du scandium, du zirconium comprise entre 0,4 et 1,2 % en poids; de 0,5 à 2,5 % en poids de magnésium; une somme comprise entre 0,9 et 3,0 % d'un ou plusieurs des éléments choisis dans la liste : manganèse, chrome, molybdène, vanadium, cobalt; une somme comprise entre 0,0 et 0,45 d'un ou plusieurs des éléments choisis dans la liste : silicium, cuivre, calcium, nickel; le reste étant de l'aluminium et des impuretés inévitables avec un total inférieur à 0,5 % en poids.
PCT/EP2024/079827 2023-10-24 2024-10-22 Alliage d'aluminium Pending WO2025087901A1 (fr)

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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004057047A1 (fr) * 2002-12-19 2004-07-08 Nippon Light Metal Company, Ltd. Plaque en alliage d'aluminium pour boitier de batterie a section transversale rectangulaire

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Publication number Priority date Publication date Assignee Title
CN109487126B (zh) * 2018-12-19 2020-06-02 中车工业研究院有限公司 一种可用于3d打印的铝合金粉末及其制备方法和应用

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004057047A1 (fr) * 2002-12-19 2004-07-08 Nippon Light Metal Company, Ltd. Plaque en alliage d'aluminium pour boitier de batterie a section transversale rectangulaire

Non-Patent Citations (1)

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Title
LI ZHEN ET AL: "Improvement in the mechanical properties and creep resistance of Al-Mn-Mg 3004 alloy with Sc and Zr addition", MATERIALS SCIENCE, vol. 729, 18 May 2018 (2018-05-18), AMSTERDAM, NL, pages 196 - 207, XP093243243, ISSN: 0921-5093, DOI: 10.1016/j.msea.2018.05.055 *

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