High-Performance Al-Zn-Mg-Zr-Based Aluminum Alloys for Welding and Additive Manufacturing

Abstract

Aluminum-zinc-magnesium-zirconium-based alloys and aluminum-zinc-magnesium-copper-zirconium-based alloys exhibiting ultra-high strength and excellent weldability, and methods for manufacturing them.

Description

[Technical Field]

[0001] [CROSS-REFERENCE TO RELATED APPLICATIONS]

[1001] This application claims priority to and the benefit of U.S. Provisional Patent Application No. 62 / 687,418, filed June 20, 2018, entitled "High-performance Al-Zn-Mg-Zr Base Aluminum Alloys for Welding and Additive Manufacturing," the disclosure of which is incorporated herein by reference in its entirety.

[0002] [Field]

[1002] This application relates to a group of Al-Zn-Mg and Al-Zn-Mg-Cu alloys, or 7000-series aluminum alloys, that, when processed by additive manufacturing techniques utilizing (i) conventional manufacturing techniques (e.g., sheet casting), (ii) powder metallurgy processes, or (iii) melt processes, can be formed into components with ultra-high strength, improved thermal stability, and weldability compared to other commercially available 7000-series aluminum alloys. [Background technology]

[0003]

[1003] The 7000 series aluminum alloys are among the highest strength alloys available. Due to this and other properties, they are often utilized in the automotive, aircraft, and aerospace industries. However, it is generally recognized by those skilled in the art that the 7000 series aluminum alloys are nearly impossible to weld, limiting their use in many applications. Therefore, it would be highly desirable to be able to provide weldable 7000 series aluminum alloys. Such materials would also be suitable for use in manufacturing processes such as additive manufacturing (i.e., 3D printing) to produce aluminum alloy components and products. Summary of the Invention [Means for solving the problem]

[0004]

[1004] Embodiments described herein relate to 7000 series aluminum-zinc-magnesium-based alloys containing one or more additional transition or rare earth metals and, optionally, copper. These aluminum alloys, which may further contain an inoculant (Sn, In, or Sb), are formable into feedstocks (i.e., sheets, wires, powders, etc.) suitable for use in manufacturing processes that may utilize welding, additive manufacturing processes that utilize wire or powder as a feedstock, or powder metallurgy processes. In various aspects, the present disclosure provides aluminum alloys comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % zirconium, and the balance aluminum. The alloys have been found to have strength-to-weight ratios at room temperature at least comparable to or greater than those of conventional 7000 series aluminum alloys. As a result of these beneficial properties, the aluminum alloys of the present disclosure can be used in welding processes without substantial liquation cracking and / or hot cracking, which can occur when using conventional 7000 series aluminum alloys in welding processes. Additionally, the aluminum alloys of the present disclosure do not contain intentionally added scandium.

[0005]

[1005] The present disclosure also provides a method for producing a weldable aluminum alloy, comprising melting recycled or virgin aluminum with the addition of an aluminum master alloy or pure elements at a temperature of about 700°C to about 1000°C to form a liquid mixture of components, the liquid mixture of components including about 4 to about 12 weight percent zinc, about 1 to about 4 weight percent magnesium, about 0.3 to about 2 weight percent zirconium or alternatively about 0.3 to about 2 weight percent titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, yttrium, lanthanum, cerium, praseodymium, neodymium, gadolinium, dysprosium, erbium, or ytterbium or combinations thereof, optionally up to about 3 weight percent copper, and the balance aluminum, wherein the liquid mixture of components does not include intentionally added scandium. The molten components can be cast in an ambient or chill casting mold to form a cast ingot and heat treated at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours to form a solution ingot comprising an Al-Zn-Mg solid solution dispersed with AlZr nanoscale precipitates of the L12 structure. The solution ingot can be hot formed and / or cold formed into sheet, foil, rod, wire, extrusions, or forgings.

[0006]

[1006] Further methods relate to the production of net-shape components, near-net-shape components, or billet-extruded components. These methods include subjecting the 7000 series aluminum alloys of the present disclosure to additive manufacturing or powder metallurgy processes to produce net-shape components, near-net-shape components, and, in the case of powder metallurgy, billet-extruded components. The components are thermally aged at a temperature of from about 100°C to about 180°C for a time period of from about 1 hour to about 48 hours to achieve a simultaneous dispersion of fine-scale Zn2Mg precipitates, primary precipitates (e.g., Al3Zr), and Al3Zr nanoscale precipitates, resulting in a component having strength at least as great as that of net-shape components, near-net-shape components, or billet-extruded components conventionally produced from conventional 7000 series aluminum alloys.

[0007]

[1007] The aluminum alloys of the present disclosure can also be used to repair or form protective coatings on components made from the aluminum alloy. This involves applying the aluminum alloy powder to a cold spray process, a thermal spray process, a laser-assisted cold spray process, or a laser cladding process to repair or form a protective coating on the component. The components made from the aluminum alloy can be heat treated at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours. In some cases, the components made from the aluminum alloy can be heat aged at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours after heat treating the component.

[0008]

[1008] An advantage of the 7000 series aluminum alloys disclosed herein is their weldability. Therefore, a method for producing a welded metal assembly is provided. The method includes joining two or more aluminum alloy components to a filler material via a welding process. The filler material joining the components can be a wire or rod formed from a 7000 series aluminum alloy. The two or more aluminum alloy components are each independently selected from the group consisting of an Al-Zn-Mg alloy, an Al-Zn-Mg-Cu alloy, an Al-Zn-Mg-Zr alloy, and an Al-Zn-Mg-Cu-Zr alloy. As noted, these alloys contain about 4 to about 12 weight percent zinc, about 1 to about 4 weight percent magnesium, about 0.3 to about 2 weight percent zirconium, and, when present, up to about 3% copper. Aluminum constitutes the balance of the composition, absent intentionally added scandium. [Brief explanation of the drawings]

[0009]

[1009] The drawings included herein are non-limiting examples of the microstructure of the metal alloys described herein, as well as examples of material properties that may be achieved by certain embodiments described herein.

[0010] [Figure 1]

[1010] Scanning electron micrograph of melt-spun ribbon of Al-11Zn-2.5Mg-1Cu (wt.%). The grains are large and span the width of the ribbon. [Figure 2]

[1011] Scanning electron micrograph of melt-spun ribbon of Al-11Zn-2.5Mg-1Cu-1.5Zr (wt.%). The grains are highly refined and many grains are contained in the ribbon. [Figure 3]

[1012] Optical micrograph of Al-11Zn-2.5Mg-1Cu (wt.%) melt-spun ribbon that was hot-consolidated and extruded, solution-heat treated, and artificially aged. Grains grew to hundreds of micrometers in size. [Figure 4]

[1013] Optical micrograph of Al-11Zn-2.5Mg-1Cu-1.5Zr (wt.%) melt-spun ribbon that was hot-consolidated and extruded, solution-heat-treated, and artificially aged. A highly refined grain microstructure was preserved. [Figure 5]

[1014] It is shown that conventionally cast Al-10Zn-3Mg alloy softens during conventional solution heat treatment at 450°C, whereas Al-10Zn-3Mg-1.2Zr exhibits a hardening response during the same solution treatment process due to the precipitation of Al3Zr nanoprecipitates. [Figure 6]

[1015] Conventionally cast Al-10Zn-3Mg alloys undergo grain growth during conventional solution heat treatment at 450°C, but Al-10Zn-3Mg-(0.6-1.2)Zr exhibits improved thermal stability and is shown to resist grain growth at elevated temperatures. [Figure 7]

[1016] A non-limiting example of an additive manufacturing (AM) process according to an embodiment is shown. [Figure 8]

[1017] A general powder metallurgy process including the steps of consolidation and sintering or heat treatment according to certain embodiments is shown. DETAILED DESCRIPTION OF THE INVENTION

[0011] [Detailed explanation]

[1018] Conventional 7000 series alloy metal powders consist primarily of zinc and magnesium, optionally with copper, with the remainder being aluminum. This combination of alloying elements constitutes the 7000 series aluminum alloys. These alloys are strengthened by the formation of Zn2Mg precipitates that occur in the solid alloy during post-process aging treatment. The addition of copper to the Al-Zn-Mg based system is known to improve the strength of the alloy, but it also reduces the corrosion resistance and weldability of the alloy. Weldability is an essential prerequisite for alloys used in additive manufacturing.

[0012]

[1019] In traditional manufacturing processes utilizing welding (e.g., sheet casting), two solid metal components are placed in contact with one another, the surfaces of the two components are locally melted using an energy source, and the liquid phases of the two components are convectively mixed. After solidification, the two components are metallurgically joined, and the chemical composition throughout the weld is often indistinguishable from that of the base material. In such processes, the energy source can be an electric current, a laser beam, or an electron beam. In certain processes, additional metal is added to the weld by feeding a wire or rod into the molten weld, and the added material is melted by the energy source and convectively mixed with the liquid phases of the two components. After solidification, the two components are metallurgically joined, and the chemical composition of the weld is often different from that of the base material. In these processes, the heat input from the energy source can change the chemistry and microstructure of the base material, resulting in a region of material (known as a heat-affected zone (HAZ)) that separates the weld from the base material. As such, welds can often be characterized by three distinct zones with significant differences in microstructure and mechanical properties: the weld or fusion zone (FZ), the HAZ, and the base material. Most notably, the microstructure and mechanical properties of the FZ will be similar to those of the cast alloy, but will often have significantly lower strength than the base material. The application of heat to the weld is sufficient to coarsen or recrystallize adjacent grains in the HAZ, thereby reducing the properties of this region below those of the base material. The base material is unaffected by the weld and maintains the properties of the starting material.

[0013]

[1020] When welding conventional 7000 series aluminum alloys, especially those with copper as an alloying element, grain growth is uncontrolled, phase separation leads to liquation cracking between the solid and liquid phases, and hot tearing occurs due to the inability of the non-refined grain structure to withstand the extreme internal stresses generated during the welding process. As a result, 7000 series aluminum alloys such as AA7050 and AA7075 are generally recognized by those skilled in the art as being unweldable.

[0014]

[1021] Additive manufacturing (commonly referred to as 3D printing) generally describes a method of additively forming net-shape or near-net-shape components, where material is deposited one layer at a time until the desired three-dimensional shape is achieved, resulting in very little waste material or scrap. This contrasts with traditional "subtractive manufacturing," where, for example, milling, material is removed from a larger preform until the final three-dimensional shape is achieved, and where such methods typically result in a lot of waste material and scrap.

[0015]

[1022] Metal additive manufacturing typically utilizes spherical metal alloy powders and uses a focused energy source, such as a laser beam or electron beam, to fuse the metal powder at specific locations to create near-net-shape components with high spatial resolution. Spherical metal powders are typically created by gas or plasma powdering, which naturally produce spherical powders, or by plasma spherization, which converts irregular particles into spherical powders. Typically, during such additive manufacturing techniques, the metal powder is sufficiently melted and rapidly solidified by an energy source so that it fuses to the underlying material, which can be an existing substrate or a previously deposited layer of powder material. To achieve a part with a desired relative density, i.e., >99%, multiple deposited material layers are typically remelted two or more times to ensure there is complete fusion between each deposited material layer. During such a process, the molten alloy rapidly melts and solidifies to within 10 3 ℃ / sec, and the cooling rate is much higher than 10 6 The solidification rate is typically about 10 °C / sec. 0 ~10 2 This is significantly faster than the rates seen during conventional molten alloy casting, which is on the order of °C / sec. Due to the very fast cooling rates inherent in additive manufacturing techniques, they are believed to be far from equilibrium, and conventional alloys optimized for equilibrium processing cannot be easily used in such methods.

[0016]

[1023] When conventional 7000 series aluminum alloys are processed by additive manufacturing, grain growth is uncontrolled, phase separation leads to liquation cracking between the solid and liquid phases, and hot tearing occurs due to the inability of the non-refined grain structure to withstand the extreme internal stresses generated during additive manufacturing. As a result, conventional 7000 series aluminum alloys, such as AA7050 and AA7075, are generally recognized by those skilled in the art as being nearly impossible to additively manufacture. The solution to both approaches is to refine the grain size in the solidified material.

[0017]

[1024] An attempt to address this challenge is made through the use of nanoparticles, which can be used to coat the surface of metal alloy powders and then incorporated into the molten alloy during additive manufacturing. These nanoparticles slow down dendrite growth, thereby inhibiting grain growth, effectively refining the grain size in the built solid, thereby avoiding liquation cracking and hot tearing and enabling the build of dense, defect-free components from otherwise difficult-to-process alloys. However, the process of coating metal alloy powders with nanoparticles adds cost and complexity to the production of metal alloy powders for additive manufacturing, and is therefore not considered an ideal technique for the large-scale, economical production of metal alloy powders for use in additive manufacturing.

[0018]

[1025] 7000 series aluminum alloy powders, which require scandium (Sc) in addition to optional other elements, have been prepared and utilized in additive manufacturing processes. See, for example, Lenczowski (U.S. Patent Application Publication No. 2017 / 0233857A1). However, scandium is known to be very expensive (approximately 10 times the price of silver) and its availability is limited. Therefore, the use of scandium dramatically increases the cost of the powder alloy, limiting its use in high-volume applications.

[0019]

[1026] Generally, there is a need for an improved method for refining the grain size (measured in accordance with ASTM E112) of welded or additively manufactured components fabricated from aluminum alloys, particularly 7000 series aluminum alloys, with desirable properties. Preferably, the method would be achievable through alloy chemistry and would not require a secondary step of incorporating nanoparticles into the welded or additively manufactured component. Additionally, the method should avoid the use of expensive scandium as an added metallic element.

[0020]

[1027] Additionally, it would be desirable not only to process 7000 series aluminum alloys by these methods, but also to have alloys that exceed the performance of existing alloys. In other words, while it would be desirable to adapt known 7000 series aluminum alloys such as AA7075 to overcome the challenges associated with welding and additive manufacturing, it would be even more desirable to achieve even higher performance from alloys based on the Al-Zn-Mg or Al-Zn-Mg-Cu systems.

[0021]

[1028] High-strength conventional 7000 series aluminum alloys are known to be typically unweldable. In contrast, the alloys of the present disclosure are advantageous for forming ultra-high-strength, weldable aluminum alloys that are weldable to components having the same alloy composition, with or without a filler material (i.e., welding feedstock or welding wire). The filler material may also have the same alloy composition as the base material. The alloys of the present disclosure are also particularly advantageous for, but not limited to, powder-based additive manufacturing techniques, such as laser powder bed fusion, directed energy deposition, laser-steered net shaping, and laser cladding, as well as wire-based additive manufacturing techniques, such as wire arc additive manufacturing. Processing 7000 series aluminum alloys by such methods is notoriously difficult, as these alloys are prone to failure due to liquation cracking and hot cracking resulting from their inweldability. The alloys of the present disclosure are specifically designed to overcome these challenges and be readily processed by such methods, where rapid melting and solidification are inherent. Additionally, because the disclosed alloys form secondary precipitation strengthening phases at high temperatures not found in conventional alloys, the disclosed alloys are advantageous for improving the strength and thermal stability (specifically defined as grain size stability) measured according to ASTM E8 / E8M of structural components fabricated from conventional 7000 series alloys in powder or fabricated form. This new phase contributes to increased strength and can resist recrystallization of the alloy at high temperatures. Finally, the disclosed alloys are advantageous for conventional powder metallurgy techniques, such as hot isostatic pressing, powder compaction, and extrusion. During these techniques, the disclosed alloys reprecipitate unconventional strengthening phases (e.g., Al3Zr) at high temperatures, thereby increasing the alloy's strength and resisting recrystallization to improve thermal stability. These unconventional precipitates are in addition to the conventional precipitates (e.g., Zn2Mg) that strengthen 7000 series aluminum alloys. As such, the disclosed alloys are advantageous for improving the performance of structural components in, for example, aerospace and automotive applications, sporting and leisure goods, and consumer products.

[0022] definition

[1029] As used herein, "conventional 7000 series aluminum alloys" refers to aluminum alloys in which zinc (Zn) is the primary alloying element and magnesium is present in smaller amounts. Other elements, such as copper, silicon, and iron, may also be added in small amounts. Conventional 7000 series aluminum alloys are characterized as being heat-treatable, high-strength materials. Examples of commonly known 7000 series aluminum alloys include AA7070 and AA7075.

[0023]

[1030] As used herein, "grain growth" means an increase in the size of grains in solid aluminum.

[0024]

[1031] As used herein, "liquation cracking" or "hot cracking" refers to the formation of shrinkage cracks during solidification of the weld metal.

[0025]

[1032] As used herein, "solid solution" refers to a solid mixture containing a minor component uniformly distributed within the crystal lattice of a major component, as distinguished from a mechanical mixture of two or more solids that have a complete or partial solubility gap in the solid state.

[0026]

[1033] As used herein, "component" means a net-shape or near-net-shape metallic structure formed from an aluminum alloy or aluminum alloy powder.

[0027]

[1034] As used herein, "additive manufacturing" (AM) refers to any process that results in a three-dimensional object and involves sequentially forming the shape of the object one layer at a time. For example, AM processes include three-dimensional printing (3DP) processes, laser net shape manufacturing, direct metal laser sintering (DMLS), direct metal laser melting (DMLM), plasma transferred arc, freeform fabrication, etc. Although not limited to a particular type, AM processes use an energy beam, e.g., an electron beam or electromagnetic radiation such as a laser beam, to sinter or melt powder materials. AM processes can use metal powder materials or wires as raw materials.

[0028]

[1035] Embodiments described herein relate to Al-Zn-Mg-based aluminum alloys that are further alloyed with transition or rare earth elements, and may include copper and / or inoculants (Sn, In, or Sb), such that the alloys have high strength, improved thermal stability, and excellent weldability. Thus, in some embodiments, the aluminum alloys of the present disclosure are heat treatable aluminum alloys.

[0029] Alloy composition

[1036] Some embodiments of the present disclosure provide an aluminum alloy comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % transition metal or rare earth element, and the balance aluminum, with the proviso that the alloy does not contain intentionally added scandium. In some embodiments, the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy can be used in welding processes without substantial liquation cracking and hot tearing, which can result from the use of conventional 7000 series aluminum alloys in welding processes. In some embodiments, the transition metal or rare earth metal is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the transition metal is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal is selected from the group consisting of Ti, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Zr, Hf, and V. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Gd, Dy, Er, and Yb.

[0030]

[1037] Some embodiments of the present disclosure provide an aluminum alloy consisting essentially of about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % transition metal or rare earth element, and the balance aluminum, with the proviso that the alloy contains no intentionally added scandium. In some embodiments, the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy is usable in welding processes without substantial liquation cracking and hot tearing, which can result from the use of conventional 7000 series aluminum alloys in welding processes. In some embodiments, the transition metal or rare earth metal is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the aluminum alloy includes about 0.3 to about 2 wt. % transition metal element. In some embodiments, the transition metal is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal is selected from the group consisting of Ti, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Zr, Hf, and V. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Gd, Dy, Er, and Yb.

[0031]

[1038] In some embodiments of the present disclosure, an aluminum alloy consisting essentially of about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % transition metal or rare earth element, and the balance aluminum (provided that the alloy does not contain intentionally added scandium) further comprises metal or metalloid impurities. In this context, impurities refer to metal or metalloid additions that do not affect other intended strengthening mechanisms or significantly degrade the material properties of the aluminum alloy. In some embodiments, the impurities in the aluminum alloys of the present disclosure are silicon and / or iron. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.5 wt. %. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.3 wt. %. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.1 wt. %. Without being bound by any particular theory, it has been found that high concentrations (i.e., concentrations greater than about 0.5 wt.%) of impurities or combinations of impurities (i.e., silicon and / or iron) form deleterious intermetallic phases in the aluminum matrix that adversely affect the mechanical properties of the aluminum alloys disclosed herein.

[0032]

[1039] Some embodiments of the present disclosure provide an aluminum alloy comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % transition metal elements, and the balance aluminum, with the proviso that the alloy does not contain intentionally added scandium. In some embodiments, the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy is usable in welding processes without substantial liquation cracking and hot tearing that can result from the use of conventional 7000 series aluminum alloys in welding processes. In some embodiments, the transition metal is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal is selected from the group consisting of Ti, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Zr, Hf, and V. In some embodiments, the transition metal is Zr.

[0033]

[1040] Some embodiments of the present disclosure provide an aluminum alloy comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % rare earth elements, and the balance aluminum, with the proviso that the alloy does not contain intentionally added scandium. In some embodiments, the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy is usable in welding processes without substantial liquation cracking and hot tearing, which can result from the use of conventional 7000 series aluminum alloys in welding processes. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Gd, Dy, Er, and Yb.

[0034]

[1041] In some embodiments, the amount of zinc in the alloys of the present disclosure is from about 4 to about 12 wt. % zinc, for example, about 4%, about 4.5%, about 5%, about 5.5%, about 6%, about 6.5%, about 7%, about 7.5%, about 8%, about 8.5%, about 9%, about 9.5%, about 10%, about 10.5%, about 11%, about 11.5%, or about 12 wt. % (including all ranges and values ​​therebetween). In some embodiments, the alloys of the present disclosure comprise from about 5 to about 12 wt% zinc, from about 6 to about 12 wt% zinc, from about 7 to about 12%, from about 8 to about 12%, from about 9 to about 12%, from about 10 to about 12%, from about 5 to about 11%, from about 6 to about 11%, from about 7 to about 11%, from about 8 to about 11%, from about 4 to about 10%, from about 5 to about 10%, from about 6 to about 10%, from about 7 to about 10%, from about 8 to about 10%, from about 4 to about 9%, from about 5 to about 9%, from about 6 to about 9%, from about 7 to about 9%, from about 4 to about 8%, from about 5 to about 8%, from about 6 to about 8%, from about 4 to about 7%, from about 5 to about 7%, or from about 4 to about 6 wt% zinc (including all ranges and values ​​therebetween). In some embodiments, the amount of zinc in the alloys of the present disclosure is from about 7 to about 12 wt% zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 7 to about 11 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 7 to about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 7 to about 9 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 8 to about 12 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 8 to about 11 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 8 to about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 11 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 9 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 8 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is from about 5 to about 7 wt.% zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is from about 6 to about 12 wt.% zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is from about 6 to about 11 wt.% zinc.In some embodiments, the amount of zinc in the alloys of the present disclosure is about 6 to about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 6 to about 9 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 6 to about 8 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 9 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 5 to about 8 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 10 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 11 wt. % zinc. In some embodiments, the amount of zinc in the alloys of the present disclosure is about 12 wt. % zinc.

[0035]

[1042] In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 1 to about 4 wt. % magnesium, e.g., about 1%, about 1.25%, about 1.5%, about 1.75%, about 2%, about 2.25%, about 2.5%, about 2.75%, about 3%, about 3.25%, about 3.5%, about 3.75%, or about 4 wt. % magnesium (including all ranges and values ​​therebetween). In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 1 to about 3 wt. % magnesium. In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 2 to about 4 wt. % magnesium. In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 1.5 wt. % magnesium. In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 2 wt. % magnesium. In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 2.5 wt. % magnesium. In some embodiments, the amount of magnesium in the alloys of the present disclosure is about 3 wt. % magnesium. In some embodiments, the amount of magnesium in the alloy of the present disclosure is about 3.5 wt.% magnesium. In some embodiments, the amount of magnesium in the alloy of the present disclosure is about 4 wt.% magnesium.

[0036]

[1043] In some embodiments, the transition metal or rare earth metal element in the aluminum alloy of the present disclosure is selected from the group consisting of titanium (Ti), hafnium (Hf), vanadium (V), niobium (Nb), tantalum (Ta), chromium (Cr), molybdenum (Mo), tungsten (W), manganese (Mn), yttrium (Y), lanthanum (La), cerium (Ce), praseodymium (Pr), neodymium (Nd), promethium (Pm), samarium (Sm), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm), ytterbium (Yb), and lutetium (Lu), or a combination thereof. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.3 to about 2 wt. % metal, e.g., about 0.3%, about 0.4%, about 0.5%, about 0.6%, about 0.7%, about 0.8%, about 0.9%, about 1.0%, about 1.1%, about 1.2%, about 1.3%, about 1.4%, about 1.5%, about 1.6%, about 1.7%, about 1.8%, about 1.9%, or about 2 wt. % metal (including all ranges and values ​​therebetween). In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.3 to about 1 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.3 to about 0.7 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 1 to about 2 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 1 to about 1.5 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 1.25 to about 1.75 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 1.4 to about 1.6 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 1.5 to about 2 wt. % metal.In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.1 to about 1 wt. % metal, e.g., about 0.1%, about 0.15%, about 0.2%, about 0.25%, about 0.3%, about 0.35%, about 0.4%, about 0.45%, about 0.5%, about 0.55%, about 0.6%, about 0.65%, about 0.7%, about 0.75%, about 0.8%, about 0.85%, about 0.9%, about 0.95%, or about 1 wt. % metal (including all ranges and values ​​therebetween). In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.1 to about 0.5 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the alloys of the present disclosure is from about 0.6 to about 1 wt. % metal. In some embodiments, the amount of transition metal or rare earth element present in the aluminum alloy of the present disclosure is greater than about 0.5 wt.% metal. In some embodiments, the amount of transition metal or rare earth element present in the aluminum alloy of the present disclosure is about 1.0 wt.% metal. In some embodiments, the amount of transition metal or rare earth element present in the aluminum alloy of the present disclosure is about 1.5 wt.% metal. In some embodiments, the amount of transition metal or rare earth element present in the aluminum alloy of the present disclosure is about 2.0 wt.% metal.

[0037]

[1044] In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu. In some embodiments, the rare earth metal is selected from the group consisting of La, Ce, Pr, Nd, Gd, Dy, Er, and Yb. In some embodiments, the amount of rare earth metal present in the alloys of the present disclosure is from about 0.3 to about 2 wt. %, e.g., about 0.3%, about 0.4%, about 0.5%, about 0.6%, about 0.7%, about 0.8%, about 0.9%, about 1.0%, about 1.1%, about 1.2%, about 1.3%, about 1.4%, about 1.5%, about 1.6%, about 1.7%, about 1.8%, about 1.9%, or about 2 wt. % rare earth metal (including all ranges and values ​​therebetween). In some embodiments, the amount of rare earth metal present in the alloys of the present disclosure is from about 1 to about 2 wt. % (including all ranges and values ​​therebetween). In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 0.3 to about 1 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 0.3 to about 0.7 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 1 to about 2 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 1 to about 1.5 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 1.25 to about 1.75 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 1.4 to about 1.6 wt. % metal. In some embodiments, the amount of rare earth element present in the alloys of the present disclosure is from about 1.5 to about 2 wt. % metal. In some embodiments, the amount of rare earth metal present in the alloys of the present disclosure is about 1.0 wt. %. In some embodiments, the amount of rare earth metal present in the alloys of the present disclosure is about 1.5 wt. %. In some embodiments, the amount of rare earth metal present in the alloys of the present disclosure is about 2.0 wt. %.

[0038]

[1045] In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Hf, V, Nb, Ta, Cr, Mo, W, Mn, and Y. In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is selected from the group consisting of Ti, Hf, and V. In some embodiments, the amount of transition metal present in the alloys of the present disclosure is from about 0.3 to about 2 wt. % transition metal, e.g., about 0.3%, about 0.4%, about 0.5%, about 0.6%, about 0.7%, about 0.8%, about 0.9%, about 1.0%, about 1.1%, about 1.2%, about 1.3%, about 1.4%, about 1.5%, about 1.6%, about 1.7%, about 1.8%, about 1.9%, or about 2 wt. % transition metal (including all ranges and values ​​therebetween). In some embodiments, the amount of transition metal present in the alloys of the present disclosure is from about 1 to about 2 wt. % transition metal (including all ranges and values ​​therebetween). In some embodiments, the amount of transition metal present in the alloys of the present disclosure is from about 0.3 to about 1 wt. % metal. In some embodiments, the amount of transition metal present in the alloys of the present disclosure is from about 0.3 to about 0.7 wt. % metal. In some embodiments, the amount of transition metal element in the alloys of the present disclosure is about 1 to about 2 wt. % metal. In some embodiments, the amount of transition metal element in the alloys of the present disclosure is about 1 to about 1.5 wt. % metal. In some embodiments, the amount of transition metal element in the alloys of the present disclosure is about 1.25 to about 1.75 wt. % metal. In some embodiments, the amount of transition metal element in the alloys of the present disclosure is about 1.4 to about 1.6 wt. % metal. In some embodiments, the amount of transition metal element in the alloys of the present disclosure is about 1.5 to about 2 wt. % metal. In some embodiments, the amount of transition metal present in the alloys of the present disclosure is about 1.0 wt. %. In some embodiments, the amount of transition metal present in the alloys of the present disclosure is about 1.5 wt. %. In some embodiments, the amount of transition metal present in the alloys of the present disclosure is about 2.0 wt. %.

[0039]

[1046] In some embodiments, the transition metal element in the aluminum alloy of the present disclosure is zirconium (Zr). In some embodiments, the amount of zirconium present in the alloy of the present disclosure is from about 0.3 to about 2 wt. % zirconium, e.g., about 0.3%, about 0.4%, about 0.5%, about 0.6%, about 0.7%, about 0.8%, about 0.9%, about 1.0%, about 1.1%, about 1.2%, about 1.3%, about 1.4%, about 1.5%, about 1.6%, about 1.7%, about 1.8%, about 1.9%, or about 2 wt. % Zr (including all ranges and values ​​therebetween). In some embodiments, the amount of zirconium present in the alloy of the present disclosure is from about 1 to about 2 wt. % zirconium (including all ranges and values ​​therebetween). In some embodiments, the amount of zirconium present in the alloy of the present disclosure is from about 0.3 to about 1 wt. % zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 0.3 to about 0.7 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1 to about 2 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1 to about 1.5 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1.25 to about 1.75 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1.4 to about 1.6 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1.5 to about 2 wt.% zirconium. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1.0 wt.% Zr. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 1.5 wt.% Zr. In some embodiments, the amount of zirconium present in the alloys of the present disclosure is about 2.0 wt. % Zr.

[0040]

[1047] In some embodiments, the alloys are distinguished from conventional 7000 series alloys by the addition of additional transition metal elements, rare earth elements, or lanthanides (excluding Sc). In some embodiments, the total addition of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Y, La, Ce, Pr, Nd, Gd, Dy, Er, Tm, Yb, Lu, or a combination thereof to the alloy is about 0.05 to about 0.8 atomic percent (at.%). In some embodiments, the total addition of Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Y, La, Ce, Pr, Nd, Gd, Dy, Er, Tm, Yb, Lu, or a combination thereof to the alloy is about 0.3 to about 0.5 at.%. As shown in Table 1, these concentrations significantly exceed the maximum equilibrium solubility limits of these elements in solid aluminum, which for most of these elements is less than about 0.1 at.%.

[0041] [Table 1]

[0042] Thus, in some embodiments, the present disclosure provides an aluminum alloy comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % zirconium, and the balance aluminum, with the proviso that the alloy does not contain intentionally added scandium (Sc). In some embodiments, the alloy has a strength-to-weight ratio at room temperature that is at least as good as or better than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy is usable in welding processes without substantially experiencing liquation cracking and hot cracking that can occur with the use of conventional 7000 series aluminum alloys in welding processes.

[0043]

[1049] In some embodiments, the present disclosure provides an aluminum alloy comprising about 4 to about 12 wt. % zinc, about 1 to about 4 wt. % magnesium, about 0.3 to about 2 wt. % titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium, or a combination thereof, and the balance aluminum, provided that the alloy does not contain intentionally added scandium (Sc). In some embodiments, the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the alloy is usable in welding processes without substantial liquation cracking and hot cracking, which can occur with the use of conventional 7000 series aluminum alloys in welding processes.

[0044]

[1050] In some embodiments, an aluminum alloy comprising: about 4 to about 12 wt. % zinc; about 1 to about 4 wt. % magnesium; about 0.3 to about 2 wt. % zirconium (further comprising about 0.1 to about 1 wt. % titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium, or a combination thereof); and the balance aluminum, wherein the alloy has a strength-to-weight ratio at room temperature at least equal to or greater than that of conventional 7000 series aluminum alloys; the alloy can be used in welding processes without substantial liquation cracking and hot cracking that can result from the use of conventional 7000 series aluminum alloys in welding processes; and the alloy does not contain intentionally added scandium. In some embodiments, the amount of titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium or a combination thereof is about 0.1%, about 0.15%, about 0.2%, about 0.25%, about 0.3%, about 0.35%, about 0.4%, about 0.45%, about 0.5%, about 0.55%, about 0.6%, about 0.65%, about 0.7%, about 0.75%, about 0.8%, about 0.85%, about 0.9%, about 0.95%, or about 1% by weight of the metal (including all ranges and values ​​therebetween).

[0045]

[1051] As described herein, the alloys of the present disclosure are scandium-free. In some embodiments, scandium is not intentionally added to the aluminum alloys disclosed herein. Thus, in some embodiments, the amount of scandium in the aluminum alloys of the present disclosure is less than about 0.05%, less than about 0.04%, less than about 0.03%, less than about 0.02%, less than about 0.01%, less than about 0.005%, or less than about 0.001% by weight of the total composition. In some embodiments, the amount of scandium in the aluminum alloy is less than about 0.1% by weight of the alloy composition. In some embodiments, the amount of scandium in the aluminum alloy is less than about 0.05% by weight of the alloy composition. In some embodiments, the amount of scandium in the aluminum alloy is less than about 0.02% by weight of the alloy composition. In some embodiments, the amount of scandium in the aluminum alloy is less than about 0.01% by weight of the alloy composition.

[0046]

[1052] In some embodiments, the aluminum alloys of the present disclosure include primary precipitates, such as AlZr, which are believed to further strengthen the alloy. In some embodiments, the primary precipitates have a diameter of about 0.05 to about 1.5 μm, e.g., about 0.05 μm, about 0.1 μm, about 0.15 μm, about 0.2 μm, about 0.25 μm, about 0.3 μm, about 0.35 μm, about 0.4 μm, about 0.45 μm, about 0.5 μm, about 0.55 μm, about 0.6 μm, about 0.65 μm, about 0.7 μm, about 0.75 μm, or about 0.85 μm.

[0023] In some embodiments, the primary precipitates have an average diameter of about 0.1 μm, about 0.8 μm, about 0.85 μm, about 0.9 μm, about 0.95 μm, about 1.00 μm, about 1.05 μm, about 1.1 μm, about 1.15 μm, about 1.2 μm, about 1.25 μm, about 1.3 μm, about 1.35 μm, about 1.4 μm, about 1.45 μm, or about 1.5 μm (including all ranges and values ​​therebetween). In some embodiments, the primary precipitates have an average diameter in the range of about 0.1 to about 1.5 μm. In some embodiments, the primary precipitates are Al-X primary precipitates. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, the primary precipitate is AlZr. In some embodiments, when multiple transition metals or rare earth metals are present in the aluminum alloy, the Al-X primary precipitates are Al-X1-X2, Al-X1-X2-X3, etc. primary precipitates, where X1, X2, X3, etc. each represent a different transition metal or rare earth metal.

[0047]

[1053] In some embodiments, the primary precipitates have a size of about 1 to about 100 nm, e.g., about 1 nm, about 2 nm, about 4 nm, about 6 nm, about 8 nm, about 10 nm, about 12 nm, about 14 nm, about 16 nm, about 18 nm, about 20 nm, about 22 nm, about 24 nm, about 26 nm, about 28 nm, about 30 nm, about 32 nm, about 34 nm, about 36 nm, about 38 nm, about 40 nm, about 42 nm, about 44 nm, about 46 nm, about 48 nm, about 50 nm, about 52 nm , about 54 nm, about 56 nm, about 58 nm, about 60 nm, about 62 nm, about 64 nm, about 66 nm, about 68 nm, about 70 nm, about 72 nm, about 74 nm, about 76 nm, about 78 nm, about 80 nm, about 82 nm, about 84 nm, about 86 nm, about 88 nm, about 90 nm, about 92 nm, about 94 nm, about 96 nm, about 98 nm, or about 100 nm (including all ranges and values ​​therebetween). In some embodiments, the nanoscale precipitates have an average diameter of about 3 to about 50 nm. In some embodiments, the nanoscale precipitates have an average diameter of about 3 to about 20 nm. In some embodiments, the nanoscale precipitates are Al-X nanoscale precipitates. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, the nanoscale precipitates are AlZr. In some embodiments, when multiple transition metals or rare earth metals are present in the aluminum alloy, the Al-X nanoscale precipitates are Al-X1-X2, Al-X1-X2-X3, etc. nanoscale precipitates, where X1, X2, X3, etc. each represent a different transition metal or rare earth metal.

[0048]

[1054] In some embodiments, nanoscale precipitates Al-X (or Al-X1-X2, Al-X1-X2-X3, etc.) having an L12 crystal structure have an average size in the range of about 1 to about 100 nm, e.g., about 1 nm, about 2 nm, about 4 nm, about 6 nm, about 8 nm, about 10 nm, about 12 nm, about 14 nm, about 16 nm, about 18 nm, about 20 nm, about 22 nm, about 24 nm, about 26 nm, about 28 nm, about 30 nm, about 32 nm, about 34 nm, about 36 nm, about 38 nm, about 40 nm, about 42 nm, about 44 nm, about 45 nm, about 46 nm, about 47 nm, about 48 nm, about 49 nm, about 50 nm, about 51 nm, about 52 nm, about 53 nm, about 54 nm, about 55 nm, about 56 nm, about 57 nm, about 58 nm, about 59 nm, about 60 nm, about 61 nm, about 62 nm, about 63 nm, about 64 nm, about 65 nm, about 66 nm, about 67 nm, about 68 nm, about 69 nm, about 70 nm, about 71 nm, about 72 nm, about 73 nm, about 74 nm, about 75 nm, about 76 nm, about 77 nm, about 78 nm, about 79 nm, about 80 nm, about 81 nm, about 82 nm, about 83 nm, about 84 nm, about 85 nm, about 86 nm, about 87 nm, about 88 nm, about 89 nm, about 90 nm, about 91 nm, about 92 nm, about 93 nm, about 94 nm, about 95 nm, about 96 nm,

[0023] In some embodiments, the nanoscale precipitates having the L12 crystal structure have an average diameter of about 44 nm, about 46 nm, about 48 nm, about 50 nm, about 52 nm, about 54 nm, about 56 nm, about 58 nm, about 60 nm, about 62 nm, about 64 nm, about 66 nm, about 68 nm, about 70 nm, about 72 nm, about 74 nm, about 76 nm, about 78 nm, about 80 nm, about 82 nm, about 84 nm, about 86 nm, about 88 nm, about 90 nm, about 92 nm, about 94 nm, about 96 nm, about 98 nm, or about 100 nm (including all ranges and values ​​therebetween). In some embodiments, the nanoscale precipitates having the L12 crystal structure have an average diameter in the range of about 3 to about 50 nm. In some embodiments, the nanoscale precipitates having the L12 crystal structure have an average diameter in the range of about 3 to about 20 nm. Without being bound by any particular theory, it is believed that the formation of these nanoscale precipitates provides increased strength beyond that which would be expected from conventional 7000 series alloys. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, the nanoscale precipitates having an L12 crystal structure are Al3Zn nanoscale precipitates.

[0049]

[1055] In some embodiments, the aluminum alloys of the present disclosure comprise an aluminum matrix having a co-dispersion of Al-X primary precipitates and ZnMg precipitates. In some embodiments, the co-dispersion further comprises nanoscale precipitates of Al-X. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu.

[0050]

[1056] The addition of the above-identified elements Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu (X) is expected to form thermally stable aluminide intermetallic phases in the metal alloy, i.e., Al-X, and if multiple elements are added, mixed aluminide phases, i.e., Al-(X1, X2, X3, etc.), will be formed. Without being bound by any particular theory, it is believed that the purpose of these additional elements and the resulting intermetallic phases are threefold: 1. These solid intermetallic phases will precipitate from the molten alloy to form primary precipitates. The primary precipitates are about 0.1 to tens of micrometers in size, preferably 0.1 to 1.5 μm, and provide nucleation sites for fcc-Al particles upon solidification, resulting in the solidified alloy having a refined grain size. In some embodiments, the primary precipitates are about 0.1 to about 1.5 μm. This overcomes some of the common challenges associated with additive manufacturing. 2. Upon post-processing heat treatment, these elements will form nanoscale aluminide precipitates in the solid alloy. The precipitates will be about 1 to about 100 nm or about 3 to about 20 nm in size. These precipitates provide strength increases beyond those that would be expected from conventional 7000 series alloys. Additionally, because these aluminide precipitates generally do not interact with the zinc and magnesium present in the alloy, they form fine-scale Zn2Mg precipitates in the solid alloy (which are responsible for the strengthening in conventional 7000 series alloys), so that after heat treatment, the alloy will achieve the strength that would be expected from a conventional 7000 series alloy when conventionally heat treated. 3. Both the fine-scale primary precipitates and the nanoscale aluminide precipitates have excellent thermal stability due to the slow diffusivity of these elements in solid aluminum. These precipitates improve the thermal stability of the alloy by providing a barrier to recrystallization.

[0051]

[1057] In some embodiments, the alloys of the present disclosure form unconventional strengthening phases (e.g., intermetallic phases such as AlZr) at high temperatures that are not present in conventional 7000 series alloys. These unconventional precipitates are in addition to the conventional precipitates (e.g., ZnMg) that strengthen 7000 series aluminum alloys. Without being bound by any particular theory, it is believed that these new phases are responsible for the increased strength and improve thermal stability by resisting recrystallization.

[0052]

[1058] In some embodiments, copper is further added to the 7000 series aluminum alloys of the present disclosure. In some embodiments, the amount of copper in the aluminum alloys of the present disclosure is up to about 3 wt. % copper. In some embodiments, the amount of copper in the aluminum alloys of the present disclosure is about 1 to about 4 wt. % copper, for example, about 1%, about 1.25%, about 1.5%, about 1.75%, about 2%, about 2.25%, about 2.5%, about 2.75%, about 3%, about 3.25%, about 3.5%, about 3.75%, or about 4% (including all ranges and values ​​therebetween). In some embodiments, the amount of copper in the aluminum alloys of the present disclosure is about 0 to about 3 wt. % copper. In some embodiments, the aluminum alloys of the present disclosure include 3 wt. % or less copper. In some embodiments, the aluminum alloys of the present disclosure include 2 wt. % or less copper. In some embodiments, the aluminum alloys of the present disclosure include 1 wt. % or less copper. In some embodiments, the aluminum alloys of the present disclosure include about 1% by weight copper.

[0053]

[1059] In some embodiments, the aluminum alloys of the present disclosure further comprise Sn, In, or Sb in the range of about 0.001 to about 0.1 at.%, e.g., about 0.001%, about 0.005%, about 0.010%, about 0.015%, about 0.02%, about 0.025%, about 0.030%, about 0.035%, about 0.040%, about 0.045%, about 0.050%, about 0.055%, about 0.060%, about 0.065%, about 0.070%, about 0.075%, about 0.080%, about 0.085%, about 0.090%, or about 0.10%, about 0.15%, including all ranges and values ​​therebetween. Without being bound by any particular theory, it has been found that these minor additions accelerate the precipitation rate of the transition metal.

[0054]

[1060] In some embodiments, the aluminum alloys of the present disclosure further include one or more silicon (Si) and iron (Fe) impurities. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure, alone or in combination, are present in an amount not exceeding about 1 wt. %, about 0.9 wt. %, about 0.8 wt. %, about 0.7 wt. %, about 0.6 wt. %, about 0.5 wt. %, about 0.4 wt. %, about 0.3 wt. %, about 0.2 wt. %, or about 0.1 wt. %, including all ranges and values ​​therebetween. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.5 wt. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.3 wt. In some embodiments, the silicon and / or iron impurities in the aluminum alloys of the present disclosure are present in an amount not exceeding about 0.1 wt. %. Without being bound by any particular theory, it has been found that high concentrations (i.e., concentrations greater than about 0.5 wt.%) of impurities or combinations of impurities (i.e., silicon and / or iron) form deleterious intermetallic phases in the aluminum matrix that adversely affect the mechanical properties of the aluminum alloys disclosed herein.

[0055]

[1061] In some embodiments, the aluminum alloys of the present disclosure include 4-12 wt.% zinc, 1-4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3-2 wt.% zirconium, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0056]

[1062] In some embodiments, the aluminum alloys of the present disclosure include 7-12 wt.% zinc, 2-4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3-2 wt.% zirconium, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0057]

[1063] In some embodiments, the aluminum alloys of the present disclosure include 5-7 wt.% zinc, 1-4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3-2 wt.% zirconium, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0058]

[1064] In some embodiments, the alloys of the present disclosure include about 4 to about 12 wt.% zinc, 1-4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3-2 wt.% zirconium, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0059]

[1065] In some embodiments, the alloys of the present disclosure include about 7 to about 12 wt.% zinc, 1 to 4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3 to 2 wt.% zirconium, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0060]

[1066] In some embodiments, the alloys of the present disclosure include about 5 to about 7 wt.% zinc, 1 to 4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3 to 2 wt.% zirconium, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not include intentionally added scandium. Thus, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0061]

[1067] In some embodiments, the aluminum alloys of the present disclosure contain about 4 to about 12 wt.% zinc, 1 to 4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3 to 2 wt.% titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium, or a combination thereof, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not contain intentionally added scandium. Therefore, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0062]

[1068] In some embodiments, the aluminum alloys of the present disclosure contain about 7 to about 12 wt.% zinc, 1 to 4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3 to 2 wt.% titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium, or a combination thereof, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not contain intentionally added scandium. Therefore, the amount of scandium is less than about 0.05% or less than about 0.02 wt.%.

[0063]

[1069] In some embodiments, the aluminum alloys of the present disclosure contain about 5 to about 7 wt.% zinc, 1 to 4 wt.% magnesium, optionally up to about 3 wt.% copper, 0.3 to 2 wt.% titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, or lutetium, or a combination thereof, not more than about 0.5 wt.% manganese, chromium, silicon, and iron impurities, and the balance aluminum. In some embodiments, the alloys do not contain intentionally added scandium. Therefore, the amount of scandium is less than about 0.05% or less than about 0.02% by weight.

[0064]

[1070] In some embodiments, the 7000 series aluminum alloys of the present disclosure further comprise one or more inoculants, hi some embodiments, the one or more inoculants are selected from the group consisting of Sn, In, and Sb.

[0065]

[1071] In some embodiments, the balance aluminum is about 77 to about 82% aluminum, e.g., about 77.2%, about 77.4%, about 77.6%, about 77.8%, about 78%, about 78.2%, about 78.4%, about 78.6%, about 78.8%, about 79%, about 79.2%, about 79.4%, 79.6%, about 79.8%, about 80%, about 80.2%, about 80.4%, about 80.6%, about 80.8%, about 81%, about 81.2%, about 81.4%, about 81.6%, about 81.8%, or about 82% by weight, including all ranges and values ​​therebetween. In some embodiments, the balance aluminum is about 78 to about 82% aluminum. In some embodiments, the balance aluminum is about 79 to about 82% aluminum. In some embodiments, the balance is aluminum in an amount of about 80 to about 82%. In some embodiments, the balance is aluminum in an amount of about 80.5 to about 82%. In some embodiments, the balance is aluminum in an amount of about 81 to about 82%. In some embodiments, the balance is aluminum in an amount of about 80 to about 81%. In some embodiments, the balance is aluminum in an amount of about 81.5 to about 82%. In some embodiments, the balance is aluminum in an amount of about 80.5 to about 81.0%.

[0066]

[1072] The 7000 series aluminum alloys of the present disclosure are designed to overcome welding and additive manufacturing challenges, such as liquation cracking and hot tearing, by producing refined grain sizes in the final component via in situ phase reactions as they are processed from the molten phase; such liquid phase processes are inherent in most welding and additive manufacturing processes that utilize an electric arc, laser beam, or electron beam as the energy source. When formed into a component, the aluminum alloys are heat treatable such that the strength of the component is improved by more than 10%, and in some cases 20%, compared to that typically achieved from a conventional 7000 series aluminum alloy (e.g., AA7050). In some embodiments, the strength of the component is increased by about 10%, about 12%, about 14%, about 16%, about 18%, or about 20% compared to the strength of a conventional 7000 series aluminum alloy. In some embodiments, the strength is increased by about 10% to about 25% compared to the strength of a conventional 7000 series aluminum alloy. Additionally, the pre-alloyed metal powders can be processed by powder metallurgy processes such as hot isostatic pressing, powder compaction, extrusion, etc., which do not result in the formation of a liquid phase during the manufacturing process. When processed in this manner, the alloys possess mechanical properties and thermal stability that exceed those expected from conventional 7000 series alloys.

[0067]

[1073] In some embodiments, the aluminum alloys of the present disclosure are shaped into rods, wires, ribbons, chips, powders, or any other form known in the art. In some embodiments, the aluminum alloys of the present disclosure in the form of ingots or solution ingots are shaped into rods, wires, ribbons, chips, or powders. In some embodiments, the aluminum alloys are shaped into ribbons, chips, or powders. In some embodiments, the aluminum alloys are shaped into chips. In some embodiments, the aluminum alloys are shaped into rods or wires. In some embodiments, the aluminum alloys are shaped into rods. In some embodiments, the aluminum alloys are shaped into wires. In some embodiments, the wire of the present disclosure has an average diameter of about 0.8 mm to about 5.2 mm, e.g., about 0.8 mm, about 1.2 mm, about 1.6 mm, about 2.0 mm, about 2.4 mm, about 2.8 mm, about 3.2 mm, about 3.6 mm, about 4.0 mm, about 4.4 mm, about 4.8 mm, or about 5.2 mm (including all ranges and values ​​therebetween). In some embodiments, the aluminum alloy is shaped into a ribbon. In some embodiments, the alloy may be shaped as a melt-spun ribbon, hot consolidated, and extruded as a structure. In some embodiments, the aluminum alloy is shaped into a powder. In some embodiments, the powder is shaped by a process selected from the group consisting of gas powdering, plasma powdering, rotating electrode processing, or mechanical alloying. In some embodiments, the process further comprises plasma spheroidization. In some embodiments, the powder is shaped into spheroids. In some embodiments, spherical particles are desirable because they spread well in powder bed processes and flow well in powder spray processes. Gas powdering generally provides spherical particles with a wide distribution of diameters. In some embodiments, the powder is irregularly shaped. Methods such as air or water powdering generally provide irregular shapes (including, but not limited to, ligamentous and / or spherical).

[0068]

[1074] In some embodiments, the powders of the present disclosure have a particle size in the range of about 1 to about 500 μm, e.g., about 1 μm, about 25 μm, about 50 μm, about 75 μm, about 100 μm, about 125 μm, about 150 μm, about 175 μm, about 200 μm, about 225 μm, about 250 μm, about 275 μm, about 300 μm, about 325 μm, about 350 μm, about 375 μm, about 400 μm, about 425 μm, about 450 μm, about 475 μm, or about 500 μm (including all ranges and values ​​therebetween). In some embodiments, the powders have a particle size in the range of about 15 to about 75 μm. In some embodiments, powders having a particle size in the range of about 15 to about 75 μm are useful in additive manufacturing processes. In some embodiments, the powders have an average particle size d of less than about 100 μm. 50 In some embodiments, the powder comprises particles having an average particle size d of about 5 to about 100 μm, e.g., about 5 μm, about 10 μm, about 15 μm, about 20 μm, about 25 μm, about 30 μm, about 35 μm, about 40 μm, about 45 μm, about 50 μm, about 55 μm, about 60 μm, about 65 μm, about 70 μm, about 75 μm, about 80 μm, about 85 μm, about 90 μm, about 95 μm, or about 100 μm (including all ranges and values ​​therebetween). 50 In some embodiments, the powder comprises particles having an average particle size d of about 10 to about 70 μm. 50 In some embodiments, the powder aluminum alloys of the present disclosure are further processed according to any suitable method known in the art to provide wires, chips, ribbons, and the like.

[0069]

[1075] In some embodiments, the aluminum alloys of the present disclosure are shaped into components having a yield strength of greater than 580 MPa, an ultimate tensile strength of greater than 600 MPa, and an elongation at break of greater than 2%. In some embodiments, the yield strength of the component is from about 500 MPa to about 750 MPa, e.g., about 500 MPa, about 550 MPa, about 600 MPa, about 650 MPa, about 700 MPa, or about 750 MPa (including all ranges and values ​​therebetween). In some embodiments, the ultimate tensile strength of the component is from about 500 MPa to about 750 MPa, e.g., about 500 MPa, about 550 MPa, about 600 MPa, about 650 MPa, about 700 MPa, or about 750 MPa (including all ranges and values ​​therebetween). In some embodiments, the component has an elongation at break of greater than 1%, greater than 2%, greater than 3%, greater than 4%, greater than 5%, greater than 6%, greater than 7%, greater than 8%, greater than 9%, or greater than 10% (including all ranges and values ​​therebetween).

[0070]

[1076] In some embodiments, the aluminum alloys of the present disclosure are formed into sheets, forgings, or extrusions, hi some embodiments, the sheets, forgings, or extrusions are welded to assemble components.

[0071]

[1077] In some embodiments, the aluminum alloys of the present disclosure are formed into rods or wires. In some embodiments, the rods or wires are used as filler material during a fusion process to join conventional aluminum alloys or to join components shaped from alloys of the present disclosure. In some embodiments, the composition of the filler material is the same as the aluminum alloy components being joined.

[0072]

[1078] The aluminum alloys of the present disclosure have many advantages over conventional 7000 series aluminum alloys. In some embodiments, the aluminum alloys of the present disclosure have improved thermal stability, for example, thermal stability greater than that of conventional 7000 series aluminum alloys. In some embodiments, the aluminum alloys of the present disclosure are high-strength, weldable aluminum alloys. In some embodiments, the alloys of the present disclosure have a strength-to-weight ratio at room temperature that is at least as good as or better than that of conventional 7000 series aluminum alloys. In some embodiments, the strength-to-weight ratio is greater than or equal to about 190 MPa cm as measured by ASTM-E8 / E8M Strength Testing and Density Determination Methods (e.g., ASTM B962). 3 / g ~ approx. 370MPa cm 3 / g, for example, about 190 MPa cm 3 / g, approx. 200MPa cm 3 / g, approx. 210MPa cm 3 / g, approx. 220MPa cm 3 / g, approx. 230MPa cm 3 / g, approx. 240MPa cm 3 / g, approx. 250MPa cm 3 / g, approx. 260MPa cm 3 / g, approx. 270MPa cm 3 / g, approx. 280MPa cm 3 / g, approx. 290MPa cm 3 / g, approx. 300MPa cm 3 / g, approx. 310MPa cm 3 / g, approx. 320MPa cm 3 / g, approx. 330MPa cm 3 / g, approx. 340MPa cm 3 / g, approx. 350MPa cm 3 / g, approx. 360MPa cm 3 / g, or approximately 370 MPa·cm 3 / g (including all ranges and values ​​therebetween). In some embodiments, the properties described above result in aluminum alloys of the present disclosure that are weldable or suitable for use in additive manufacturing.

[0073]

[1079] In some embodiments of the present disclosure, the average grain size after solution heat treatment is less than 100 μm. In some embodiments, the average grain size after solution heat treatment is less than 95 μm. In some embodiments, the average grain size after solution heat treatment is less than 90 μm. In some embodiments, the average grain size after solution heat treatment is less than 85 μm. In some embodiments, the average grain size after solution heat treatment is less than 80 μm. In some embodiments, the average grain size after solution heat treatment is less than 75 μm. In some embodiments, the average grain size after solution heat treatment is less than 70 μm. In some embodiments, the average grain size after solution heat treatment is less than 65 μm. In some embodiments, the average grain size after solution heat treatment is less than 60 μm. In some embodiments, the average grain size after solution heat treatment is less than 55 μm. In some embodiments, the average grain size after solution heat treatment is less than 50 μm. In some embodiments, the average grain size after solution heat treatment is less than 45 μm. In some embodiments, the average grain size after solution heat treatment is less than 40 μm. In some embodiments of the present disclosure, the average grain size after solution heat treatment is about 40 to about 100 μm, e.g., about 40 μm, about 45 μm, about 50 μm, about 55 μm, about 60 μm, about 65 μm, about 70 μm, about 75 μm, about 80 μm, about 85 μm, about 90 μm, about 95 μm, or about 100 μm (including all ranges and values ​​therebetween). In some embodiments, this refined grain size results in the aluminum alloy of the present disclosure being free of liquation cracking and hot tearing during welding or additive manufacturing processes.

[0074]

[1080] In some embodiments, the aluminum alloys of the present disclosure, or components shaped from the aluminum alloys of the present disclosure, have a tensile strength at least as great as or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the tensile strength of the aluminum alloys of the present disclosure is in a range of about 50 to about 750 MPa, e.g., about 50 MPa, about 100 MPa, about 150 MPa, about 200 MPa, about 250 MPa, about 300 MPa, about 350 MPa, about 400 MPa, about 450 MPa, about 500 MPa, about 550 MPa, about 600 MPa, about 650 MPa, about 700 MPa, or about 750 MPa (including all ranges and values ​​therebetween). In some embodiments, the tensile strength is greater than about 350 MPa. In some embodiments, the tensile strength is greater than about 450 MPa. In some embodiments, the tensile strength is greater than about 500 MPa. In some embodiments, the tensile strength is greater than about 550 MPa. In some embodiments, the tensile strength is greater than about 600 MPa. In some embodiments, the tensile strength is greater than about 650 MPa. In some embodiments, the tensile strength is greater than about 700 MPa. In some embodiments, the tensile strength is greater than about 750 MPa.

[0075]

[1081] In some embodiments, aluminum alloys of the present disclosure, or components shaped from aluminum alloys of the present disclosure, have shear strengths at least as high as or greater than those of conventional 7000 series aluminum alloys. In some embodiments, the shear strength of aluminum alloys of the present disclosure is in the range of about 50 to about 400 MPa, e.g., about 50 MPa, about 75 MPa, about 100 MPa, about 125 MPa, about 150 MPa, about 175 MPa, about 200 MPa, about 225 MPa, about 250 MPa, about 275 MPa, about 300 MPa, about 325 MPa, about 350 MPa, about 375 MPa, or about 400 MPa (including all ranges and values ​​therebetween). In some embodiments, the shear strength is about 250 MPa. In some embodiments, the shear strength is about 300 MPa. In some embodiments, the shear strength is greater than about 200 MPa.

[0076]

[1082] In some embodiments, the aluminum alloys of the present disclosure, or components shaped from the aluminum alloys of the present disclosure, have a yield strength at least as great as or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the yield strength of the aluminum alloys of the present disclosure is in a range of about 150 to about 600 MPa, e.g., about 150 MPa, about 175 MPa, about 200 MPa, about 225 MPa, about 250 MPa, about 275 MPa, about 300 MPa, about 325 MPa, about 350 MPa, about 375 MPa, about 400 MPa, about 425 MPa, about 450 MPa, about 475 MPa, about 500 MPa, about 525 MPa, about 550 MPa, about 575 MPa, or about 600 MPa (including all ranges and values ​​therebetween). In some embodiments, the yield strength is greater than about 450 MPa. In some embodiments, the yield strength is greater than about 500 MPa. In some embodiments, the yield strength is greater than about 550 MPa. In some embodiments, the yield strength is greater than about 580 MPa.

[0077]

[1083] In some embodiments, the aluminum alloys of the present disclosure, or components shaped from the aluminum alloys of the present disclosure, have a modulus of elasticity at least as great as or greater than that of conventional 7000 series aluminum alloys. In some embodiments, the modulus of elasticity of the aluminum alloys of the present disclosure is in a range of about 50 to about 80 GPa, e.g., about 50 GPa, about 52.5 GPa, about 55 GPa, about 57.5 GPa, about 60 GPa, about 62.5 GPa, about 65 GPa, about 67.5 GPa, about 70 GPa, about 72.5 GPa, about 75 GPa, about 77.5 GPa, or about 80 GPa (including all ranges and values ​​therebetween). In some embodiments, the modulus of elasticity is about 65 GPa. In some embodiments, the modulus of elasticity is about 70 GPa. In some embodiments, the modulus of elasticity is about 75 GPa. In some embodiments, the modulus of elasticity is about 80 GPa. In some embodiments, the modulus of elasticity is greater than about 75 GPa.

[0078]

[1084] In some embodiments, the aluminum alloys of the present disclosure, or components shaped from the aluminum alloys of the present disclosure, have an elongation to break of about 1 to about 15%. In some embodiments, the aluminum alloys of the present disclosure, or components shaped from the aluminum alloys of the present disclosure, have an elongation to break of about 2 to about 10%. The elongation to break is greater than about 2%, greater than about 3%, greater than about 4%, greater than about 5%, greater than about 6%, greater than about 7%, greater than about 8%, greater than about 9%, or greater than about 10%. In some embodiments, the elongation to break is greater than about 2%. In some embodiments, the elongation to break is greater than about 3%. In some embodiments, the elongation to break is greater than about 4%. In some embodiments, the elongation to break is greater than about 5%.

[0079]

[1085] In some embodiments, aluminum alloy components (e.g., net shape or near net shape) shaped from the 7000 series aluminum alloys of the present disclosure (e.g., by processes such as additive manufacturing or powder metallurgy) have the tensile strength, shear strength, yield strength, and / or elastic modulus defined above.

[0080]

[1086] Based on these properties, in some embodiments, structures shaped from the alloy in either form may be used in applications where extremely high strength and low density are desired, such as found in aerospace components, satellite components, automotive components, transportation applications, sporting or leisure goods, or consumer products.

[0081]

[1087] As noted above, in some embodiments, the aluminum alloys of the present disclosure are in the form of powders. In some embodiments, the aluminum alloy powders disclosed herein are useful in additive manufacturing processes. In some embodiments, the aluminum alloy powders useful in additive manufacturing processes are spherical metal alloy powders. In some embodiments, the spherical metal powders are formed using gas powdering, plasma powdering, or plasma spheroidizing.

[0082]

[1088] In some embodiments, the aluminum alloys disclosed herein are useful in joining techniques, including, but not limited to, welding. Without being bound by any particular theory, the utility of the aluminum alloys of the present disclosure may be a result of the reduced or eliminated tendency to hot tear or liquation crack when subjected to such processes.

[0083] method

[1089] In some embodiments, a method for producing a weldable 7000 series aluminum alloy is provided, the method comprising: a) melting recycled or virgin aluminum with the addition of an aluminum master alloy or pure elements at a temperature of about 700°C to about 1000°C to form a liquid mixture of components comprising about 4 to about 12 wt.% zinc, about 1 to about 4 wt.% magnesium, about 0.3 to about 2 wt.% transition metal or rare earth metal, balance aluminum, and the components being free of intentionally added scandium; and b) casting the molten components in an ambient or chill casting mold to form a cast ingot; c) heat treating the cast ingot at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours to form a solutionized ingot comprising an Al-Zn-Mg solid solution dispersed with AlZr nanoscale precipitates of the L12 structure; and d) hot forming and / or cold forming the solutionized ingot into a sheet, foil, rod, wire, extrusion, or forging.

[0084]

[1090] In some embodiments, a method for producing a weldable 7000 series aluminum alloy is provided. The method comprises: a) melting recycled or virgin aluminum with the addition of an aluminum master alloy or pure elements at a temperature of about 700°C to about 1000°C to form a liquid mixture of components, the liquid mixture of components comprising about 4 to about 12 wt.% zinc, about 1 to about 4 wt.% magnesium, about 0.3 to about 2 wt.% transition metals, the balance aluminum, and the components containing no intentionally added scandium; and b) forming a liquid mixture of the melt blended components. c) heat treating the cast ingot at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours to form a solutionized ingot comprising an Al-Zn-Mg solid solution dispersed with AlZr nanoscale precipitates of L12 structure; and d) hot forming and / or cold forming the solutionized ingot into a sheet, foil, rod, wire, extrusion, or forging.

[0085]

[1091] In some embodiments, the transition metal in the liquid mixture of components is selected from the group consisting of titanium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, and yttrium, hi some embodiments, the transition metal in the liquid mixture of components is zirconium.

[0086]

[1092] In some embodiments, the rare earth metal is selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, gadolinium, dysprosium, erbium, ytterbium, or combinations thereof.

[0087]

[1093] In some embodiments, the amount of zinc in the liquid mixture of ingredients is about 4 to about 12% by weight zinc, for example, about 4%, about 4.5%, about 5%, about 5.5%, about 6%, about 6.5%, about 7%, about 7.5%, about 8%, about 8.5%, about 9%, about 9.5%, about 10%, about 10.5%, about 11%, about 11.5%, or about 12% (including all ranges and values ​​therebetween). In some embodiments, the alloys of the present disclosure comprise about 5 to about 12% by weight zinc, about 6 to about 12% by weight zinc, about 7 to about 12%, about 8 to about 12%, about 9 to about 12%, about 10 to about 12%, about 5 to about 11%, about 6 to about 11%, about 7 to about 11%, about 8 to about 11%, about 4 to about 10%, about 5 to about 10%, about 6 to about 10%, about 7 to about 10%, about 8 to about 10%, about 4 to about 9%, about 5 to about 9%, about 6 to about 9%, about 7 to about 9%, about 4 to about 8%, about 5 to about 8%, about 6 to about 8%, about 4 to about 7%, about 5 to about 7%, and about 4 to about 6% (including all ranges and values ​​therebetween). In some embodiments, the amount of zinc in the liquid mixture of components is about 10% by weight zinc. In some embodiments, the amount of zinc in the liquid mixture of ingredients is about 11% zinc by weight. In some embodiments, the amount of zinc in the liquid mixture of ingredients is about 12% zinc by weight.

[0088]

[1094] In some embodiments, the amount of magnesium in the liquid mixture of ingredients is about 1 to about 4% magnesium by weight, e.g., about 1%, about 1.25%, about 1.5%, about 1.75%, about 2%, about 2.25%, about 2.5%, about 2.75%, about 3%, about 3.25%, about 3.5%, about 3.75%, or about 4% (including all ranges and values ​​therebetween). In some embodiments, the amount of magnesium in the liquid mixture of ingredients is about 1.5% magnesium by weight. In some embodiments, the amount of magnesium in the liquid mixture of ingredients is about 2% magnesium by weight. In some embodiments, the amount of magnesium in the liquid mixture of ingredients is about 2.5% magnesium by weight. In some embodiments, the amount of magnesium in the liquid mixture of ingredients is about 3% magnesium by weight.

[0089]

[1095] In some embodiments, the temperature in step a) is about 700°C, about 725°C, about 750°C, about 775°C, about 800°C, about 825°C, about 850°C, about 875°C, 900°C, about 925°C, about 950°C, about 975°C, or about 1000°C (including all ranges and values ​​therebetween). In some embodiments, the temperature in step a) is about 750°C to about 1000°C. In some embodiments, the temperature in step a) is about 800°C to about 1000°C. In some embodiments, the temperature in step a) is about 850°C to about 1000°C. In some embodiments, the temperature in step a) is about 900°C to about 1000°C.

[0090]

[1096] In some embodiments, step a) includes the elements zinc (Zn), magnesium (Mg), and zirconium (Zr) in any of the amounts or ranges described above for the aluminum alloys of the present disclosure.

[0091]

[1097] In some embodiments, the components of step a) further comprise about 0.0 to about 4 wt. % copper, e.g., about 0%, about 0.25%, about 0.50%, about 0.75%, about 1%, about 1.25%, about 1.50%, about 1.75%, about 2%, about 2.25%, about 2.50%, about 2.75%, about 3%, about 3.25%, about 3.50%, about 3.75%, or about 4 wt. % copper (including all ranges and values ​​therebetween). In some embodiments, the amount of copper is less than about 4 wt. % copper, less than about 3 wt. % copper, less than about 2 wt. % copper, or less than about 1 wt. In some embodiments, the amount of copper is up to about 3 wt. In some embodiments, when copper is present, the solution-annealed ingot comprises an Al-Zn-Mg-Cu solid solution dispersed with AlZr nanoscale precipitates of the L12 structure.

[0092]

[1098] As stated, the components of the liquid mixture of step a) do not include intentionally added scandium. Thus, in some embodiments, the liquid mixture of components of step a) includes less than about 0.5% scandium, less than about 0.5% scandium, less than about 0.3% scandium, less than about 0.2% scandium, less than about 0.1% scandium, or less than about 0.05% scandium by weight, none of which is intentionally added to the aluminum alloys of the present disclosure.

[0093]

[1099] In some embodiments, step b) of the method for producing a weldable 7000 series aluminum alloy comprises casting the molten component in an ambient casting mold to form a cast ingot. In some embodiments, step b) of the method for producing a weldable 7000 series aluminum alloy comprises casting the molten component in a chill casting mold to form a cast ingot. In some embodiments, the chill casting mold is at a temperature of less than about 20°C, less than about 15°C, less than about 10°C, less than about 5°C, or less than about 0°C. In some embodiments, the chill casting mold is at a temperature of about 0°C to about 15°C, e.g., about 0°C, about 3°C, about 6°C, about 9°C, about 12°C, or about 15°C (including all ranges and values ​​therebetween). In some embodiments, the chill casting mold is at a temperature of about 5°C to about 10°C. In some embodiments, the chill casting mold is at a temperature of about 0°C to about 10°C.

[0094]

[1100] In some embodiments, the heat treatment of the cast ingot in step c) is carried out at a temperature of about 400°C, about 410°C, about 420°C, about 430°C, about 440°C, about 450°C, about 460°C, about 470°C, or about °C (including all ranges and values ​​therebetween). In some embodiments, the heat treating of the cast ingot in step c) is conducted for a time period of about 0.25 h, about 0.5 h, about 0.75 h, about 1 h, about 1.25 h, about 1.5 h, about 1.75 h, about 2 h, about 2.25 h, about 2.5 h, about 2.75 h, about 3 h, about 3.25 h, about 3.5 h, about 3.75 h, about 4 h, about 4.25 h, about 4.5 h, about 4.75 h, about 5 h, about 5.25 h, about 5.5 h, about 5.75 h, or about 6 hours (including all ranges and values ​​therebetween) to form a solutionized ingot comprising an Al-Zn-Mg solid solution dispersed with AlZr nanoscale precipitates of L12 structure.

[0095]

[1101] In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides a sheet. In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides a foil. In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides a rod. In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides a wire. In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides an extrusion. In some embodiments, hot forming and / or cold forming the solution-annealed ingot in step d) provides a forging.

[0096]

[1102] In some embodiments, the method of producing a weldable 7000 series aluminum alloy further comprises step e) heat aging the formed sheet, foil, rod, wire, extrusion, or forging at a temperature of from about 1 hour to about 48 hours at a temperature of from about 100°C to about 180°C.

[0097]

[1103] In some embodiments, the heat aging of step e) is carried out at about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, about 100°C, about 105°C, or about 180°C (including all ranges and values ​​therebetween).

[0098]

[1104] In some embodiments, the heat aging in step e) is for about 1 h, about 2 h, about 3 h, about 4 h, about 5 h, about 6 h, about 7 h, about 8 h, about 9 h, about 10 h, about 11 h, about 12 h, about 13 h, about 14 h, about 15 h, about 16 h, about 17 h, about 18 h, about 19 h, about 20 h, about 21 h, about 22 h, about 23 h, about 24 h, about 25 h, about The thermal aging period may be about 26 h, about 27 h, about 28 h, about 29 h, about 30 h, about 31 h, about 32 h, about 33 h, about 34 h, about 35 h, about 36 h, about 37 h, about 38 h, about 39 h, about 40 h, about 41 h, about 42 h, about 43 h, about 44 h, about 45 h, about 46 h, about 47 h, or about 48 h (including all ranges and values ​​therebetween). In some embodiments, the thermal aging period of step e) is about 1 h to about 10 h. In some embodiments, the thermal aging period of step e) is about 1 h to about 5 h. In some embodiments, the thermal aging period of step e) is about 1 h to about 3 h. In some embodiments, the thermal aging period of step e) is about 5 h to about 20 h. In some embodiments, the thermal aging period of step e) is about 5 h to about 15 h. In some embodiments, the heat aging in step e) is for a time period of about 5 h to about 10 h.

[0099]

[1105] In some embodiments, the aluminum alloys disclosed herein are produced by a rapid solidification process as described in EJ Lavernia et al. Journal of Material Science 2010, 45, 287-325, the disclosure of which is hereby incorporated by reference in its entirety. In some embodiments, the rapid solidification process is selected from the group consisting of melt spinning, melt extraction, beam glazing, spray deposition, gas powdering, plasma powdering, and plasma spheroidization ... 2 ~about 10 7 Ks -1 , for example, about 10 2 Ks -1 , about 10 3 Ks -1 , about 10 4 Ks -1 , about 10 5 Ks -1 , about 10 6 Ks -1 , or about 10 7 Ks -1 (including all ranges and values ​​therebetween).

[0100]

[1106] Melt spinning is a convenient and economical method for producing metal ribbons on an industrial scale. In some applications of melt spinning, a material (e.g., an aluminum alloy) is melted for extrusion through a spinneret and then directly solidified by cooling. In some embodiments, melt spinning further produces non-equilibrium phases, such as nanocrystalline phases, quasicrystalline phases, and supersaturated solid solutions. In some embodiments, the aluminum alloy produced from melt spinning is in the form of a ribbon (i.e., a thin strip). In some embodiments, melt spinning produces ribbons comprising amorphous aluminum alloys and / or glassy aluminum alloys.

[0101]

[1107] Spray deposition, also known as spray casting, spray forming, and in-situ consolidation, is a method for casting uniformly microstructured near-net-shape metal components via the deposition of semi-solid spray droplets onto a shaped substrate. In some embodiments, the spray deposition method is selected from the group consisting of cold gas spraying, plasma spraying (vacuum, atmospheric, etc.), high velocity oxy-fuel spraying (HVOF), gas-assisted spray forming, or combustion flame spraying. In some embodiments, spray deposition involves powdering molten metal, but instead of solidifying as a powder, the spray is collected on a substrate to form a billet for subsequent forging. In some embodiments, spray deposition is used to form 7000 series aluminum alloy tubes, strip, sheet, or near-net-shape preforms.

[0102]

[1108] In plasma spheroidization, non-spherical powder is melted with a plasma beam to form spherical particles. In some embodiments, a gas (e.g., N, Ar) is used to transport the powder. In some embodiments, the method is useful for producing aluminum alloys of the present disclosure that have high melting points. In some embodiments, plasma spheroidization is used to convert irregularly shaped 7000 series aluminum alloy particles into spherical powders of 7000 series aluminum alloys. In some embodiments, the spherical powders so produced have a uniform composition.

[0103]

[1109] Plasma powderization is also useful for producing spherical powders of 7000 series aluminum alloys. In some embodiments, plasma powderization is used to convert a feedstock 7000 series aluminum alloy into a spherical powder of 7000 series aluminum alloys. In some embodiments, the spherical powder thus produced has a uniform composition. In some embodiments, a 7000 series aluminum alloy wire feedstock is fed into a plasma torch, and a gas is utilized to granulate the wire into a spherical metal powder. In some embodiments, the powder particle size is within the range of about 1 to about 200 μm, including all ranges and values ​​therebetween.

[0104]

[1110] Another method for producing metal powders is gas powdering. In some embodiments, an aluminum alloy feedstock is melted under a blanket of air or an inert gas, or under vacuum. The chamber can then be backfilled with gas, and the molten alloy can be forced through a nozzle, where high-velocity air, nitrogen, helium, or argon gas impinges on and breaks up the flowing melt. The resulting powder is primarily spherical. In some embodiments, there are small amounts of asymmetric particles and satellites (i.e., small particles attached to larger particles).

[0105]

[1111] In some embodiments, the rapid solidification process results in the formation of primary crystallites with diameters of about 10 μm or less. In some embodiments, the primary crystallites are less than about 10 μm, less than about 9 μm, less than about 8 μm, less than about 7 μm, less than about 6 μm, less than about 5 μm, less than about 4 μm, less than about 3 μm, less than about 2 μm, or less than about 1 μm (including all ranges and values ​​therebetween). In some embodiments, the rapid solidification process results in an expansion of the solid solution range.

[0106]

[1112] Generally, due to the rapid solidification of metal alloys during the powderization process, the powder may consist primarily of a solid solution of the alloying elements, but may also contain intermetallic phases (e.g., AlZr). When metal alloy powders are synthesized by mechanical alloying processes, which are solid-state processes that do not involve quenching a molten alloy to a solid, with sufficient mechanical energy input, the metal alloy powder will still consist primarily of a solid solution of the alloying elements, but may also contain secondary intermetallic phases. When used in additive manufacturing processes that form a liquid phase in the alloy, the presence of secondary intermetallic phases is not considered a detrimental or beneficial attribute of the metal alloy powder, but when used in powder metallurgy processes that do not form a liquid phase, such intermetallic phases may be considered beneficial to the metal alloy powder, and the powder shaping method may be tailored to promote the formation of secondary intermetallic phases in the metal alloy powder.

[0107]

[1113] The methods disclosed herein may include fabricating a component using a manufacturing technique utilizing welding, where an alloy of the present disclosure is utilized as a base or filler material. In some embodiments, the 7000 series aluminum alloy rods and wires described above are used as a filler material to join two aluminum alloy components in a welding process. Thus, a method for fabricating a welded metal assembly is provided. The method includes joining two aluminum alloy components in a welding process with a filler material, where the filler material joining the components is a wire or rod formed from a 7000 series aluminum alloy of the present disclosure, and the two aluminum alloy components are each independently selected from the group consisting of an Al-Zn-Mg alloy, an Al-Zn-Mg-Cu alloy, an Al-Zn-Mg-Zr alloy, and an Al-Zn-Mg-Cu-Zr alloy. In some embodiments, the filler material is a rod formed from a 7000 series aluminum alloy of the present disclosure. In some embodiments, the filler material is a wire formed from a 7000 series aluminum alloy of the present disclosure. In some embodiments, the filler material is a shaped sheet of the 7000 series aluminum alloy of the present disclosure.

[0108]

[1114] In some embodiments, the welding process is selected from the group consisting of arc welding, torch welding, laser beam welding, and electron beam welding. In some embodiments, the welding process does not result in liquation cracking and / or hot cracking of the welded metal assembly. Thus, in some embodiments, the welded metal assembly is free of liquation cracking and hot cracking.

[0109]

[1115] In some embodiments, the filler material and the two aluminum alloy components have the same composition. Thus, in some embodiments, the filler material and the two aluminum alloy components, each independently selected from the group consisting of an Al-Zn-Mg alloy, an Al-Zn-Mg-Cu alloy, an Al-Zn-Mg-Zr alloy, and an Al-Zn-Mg-Cu-Zr alloy, contain about 4 to about 12 weight percent zinc, about 1 to about 4 weight percent magnesium, about 0.3 to about 2% zirconium, when present, and up to about 3% copper, when present. As noted above, neither the filler material nor the aluminum alloy components have intentionally added scandium.

[0110]

[1116] The 7000 series aluminum alloys disclosed herein are suitable for use in a variety of additive manufacturing processes due to their beneficial properties, including, but not limited to, weldability and high strength-to-weight ratio. Examples of additive manufacturing processes are disclosed in U.S. Patent No. 10,124,408, which is incorporated herein by reference in its entirety. Figure 7 provides an overview of some additive manufacturing processes applicable to aluminum alloys, but is not limited to them.

[0111]

[1117] In some embodiments, the present disclosure provides a method for producing a net-shape or near-net-shape component. The method includes applying an additive manufacturing process (e.g., additive layered manufacturing) to an aluminum alloy of the present disclosure to produce the net-shape or near-net-shape component. In some embodiments, the aluminum alloy is a rod, wire, ribbon, powder, or chip. In some embodiments, the aluminum alloy is a wire. In some embodiments, the aluminum alloy is a powder. In some embodiments, the powder is a spherical aluminum alloy powder. The method may include using a pre-alloyed metal powder to shape a structure using an additive manufacturing (or powder metallurgy) process. In this case, the method may include the formation of a liquid phase.

[0112]

[1118] In some embodiments, the additive manufacturing process is powder bed fusion or selective laser melting. In some embodiments, the additive manufacturing process is powder bed fusion. In some embodiments, the additive manufacturing process is selective laser melting. In some embodiments of powder bed fusion or selective laser melting processes, a laser is used to melt powder and fuse it together into a net shape or near net shape component.

[0113]

[1119] In some embodiments, the additive manufacturing process is powder directed energy deposition. In some embodiments of the powder directed energy deposition process, a laser is used to melt-blow powder and fuse it into a net-shape or near-net-shape component.

[0114]

[1120] In some embodiments, the additive manufacturing process includes subjecting the aluminum alloy to a focused energy source. In some embodiments, the focused energy source is selected from the group consisting of a laser beam and an electron beam. In some embodiments, the focused energy source is a laser beam. In some embodiments, the laser beam is a pulsed energy laser beam. In some embodiments, the focused energy source is an electron beam.

[0115]

[1121] In some embodiments of the additive manufacturing process, a focused energy source is used to fully melt the aluminum alloy. In some embodiments, the fully molten aluminum alloy is deposited as a layer onto an existing substrate or layer on which aluminum alloy has already been deposited. In some embodiments, the deposited layer of aluminum alloy undergoes rapid solidification to fuse the material to the existing substrate or layer on which aluminum alloy has already been deposited. In some embodiments, the rapid solidification occurs within a time period of about 10 2 ~about 10 8 Ks -1 , for example, about 10 2 Ks -1 , about 10 3 Ks -1 , about 10 4 Ks -1 , about 10 5 Ks -1 , about 10 6 Ks -1 , about 10 7 Ks -1 , or about 10 8 Ks -1 In some embodiments, the rapid solidification is carried out at a cooling rate of at least about 10 7 Ks -1 In some embodiments, the rapid solidification is carried out at a cooling rate of about 10 7 Ks -1As described herein, net or near net shape components fabricated using the 7000 series aluminum alloys of the present disclosure avoid liquation cracking and hot tearing as a result of the beneficial properties of the aluminum alloy material of the present disclosure.

[0116]

[1122] In some embodiments, the additive manufacturing processes disclosed herein further include thermally aging the net-shape or near-net-shape component at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours to achieve a co-dispersion of fine-scale ZnMg precipitates, primary precipitates, and Al-X nanoscale precipitates, resulting in a component having a strength at least as great as or greater than that of a net-shape or near-net-shape component conventionally produced from a conventional 7000 series aluminum alloy. In some embodiments, the primary precipitates have an average diameter in the range of about 0.1 to about 10 μm, e.g., about 0.1 μm, about 0.5 μm, about 1 μm, about 1.5 μm, about 2 μm, about 2.5 μm, about 3 μm, about 3.5 μm, about 4 μm, about 4.5 μm, about 5 μm, about 5.5 μm, about 6 μm, about 6.5 μm, about 7 μm, about 7.5 μm, about 8 μm, about 8.5 μm, about 9 μm, about 9.5 μm, or about 10 μm (including all ranges and values ​​therebetween). In some embodiments, the primary precipitates have an average diameter in the range of about 0.5 to about 1.5 μm. In some embodiments, the primary precipitates have an average diameter in the range of about 0.1 to about 1.5 μm. In some embodiments, the primary precipitates are Al-X primary precipitates. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, X is Zr. In some embodiments, the primary precipitates are AlZr primary precipitates.In some embodiments, the Al-X nanoscale precipitates have a size in the range of about 1 to about 100 nm, e.g., about 1 nm, about 2 nm, about 4 nm, about 6 nm, about 8 nm, about 10 nm, about 12 nm, about 14 nm, about 16 nm, about 18 nm, about 20 nm, about 22 nm, about 24 nm, about 26 nm, about 28 nm, about 30 nm, about 32 nm, about 34 nm, about 36 nm, about 38 nm, about 40 nm, about 42 nm, about 44 nm, about 46 nm, about 48 nm, about 50 nm, about 52 nm, about 54 nm, about 56 nm, about 58 nm, about 59 nm, about 60 nm, about 61 nm, about 62 nm, about 63 nm, about 64 nm, about 65 nm, about 66 nm, about 67 nm, about 68 nm, about 69 nm, about 70 nm, about 71 nm, about 72 nm, about 73 nm, about 74 nm, about 75 nm, about 76 nm, about 77 nm, about 78 nm, about 79 nm, about 80 nm, about 81 nm, about 82 nm, about 83 nm, about 84 nm, about 85 nm, about 86 nm, about 87 nm, about 88 nm, about 89 nm, about 90 nm, about 91 nm, about 92 nm, about 93 nm, about 94 nm, about 95 nm, about 96 nm, about 97 nm, about 98 nm, about 99 nm, about 100 nm, about 101 nm, about 102 nm, about 103 nm, about 104 nm, about 105 nm, about 106 nm, about 107 nm The Al-X nanoscale precipitates have an average diameter of about 50 nm, about 52 nm, about 54 nm, about 56 nm, about 58 nm, about 60 nm, about 62 nm, about 64 nm, about 66 nm, about 68 nm, about 70 nm, about 72 nm, about 74 nm, about 76 nm, about 78 nm, about 80 nm, about 82 nm, about 84 nm, about 86 nm, about 88 nm, about 90 nm, about 92 nm, about 94 nm, about 96 nm, about 98 nm, or about 100 nm (including all ranges and values ​​therebetween). In some embodiments, the Al-X nanoscale precipitates have an average diameter in the range of about 3 to about 50 nm. In some embodiments, the Al3Zr nanoscale precipitates have an average diameter in the range of about 3 to about 20 nm. In some embodiments, the Al-X nanoscale precipitates have an average diameter in the range of about 3 to about 10 nm. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, the nanoscale precipitates are AlZr nanoscale precipitates.

[0117]

[1123] In some embodiments, heat aging of the net shape or near net shape component is carried out at a temperature of about 100°C, about 110°C, about 120°C, about 130°C, about 140°C, about 150°C, about 160°C, about 170°C, or about 180°C (including all ranges and values ​​therebetween).

[0118]

[1124] In some embodiments, the heat aging of the net shape component or near net shape component is for about 1 hour, about 2 hours, about 3 hours, about 4 hours, about 5 hours, about 6 hours, about 7 hours, about 8 hours, about 9 hours, about 10 hours, about 11 hours, about 12 hours, about 13 hours, about 14 hours, about 15 hours, about 16 hours, about 17 hours, about 18 hours, about 19 hours, about 20 hours, about 21 hours, about 22 hours, about 23 hours, about 24 hours, about 25 hours, about 26 hours, about 27 hours, about 28 hours, about 29 hours, about 30 hours, about 31 hours, about 32 hours, about 33 hours, about 34 hours, about 35 hours, about 36 hours, about 37 hours, about 38 hours, about 39 hours, about 40 hours, about 41 The heat aging step may be performed for a period of time ranging from about 3 h, about 24 h, about 25 h, about 26 h, about 27 h, about 28 h, about 29 h, about 30 h, about 31 h, about 32 h, about 33 h, about 34 h, about 35 h, about 36 h, about 37 h, about 38 h, about 39 h, about 40 h, about 41 h, about 42 h, about 43 h, about 44 h, about 45 h, about 46 h, about 47 h, or about 48 h (including all ranges and values ​​therebetween). In some embodiments, the heat aging step is performed for a period of time ranging from about 1 h to about 10 h. In some embodiments, the heat aging step is performed for a period of time ranging from about 1 h to about 5 h. In some embodiments, the heat aging step is performed for a period of time ranging from about 1 h to about 3 h. In some embodiments, the heat aging step is performed for a period of time ranging from about 5 h to about 20 h. In some embodiments, the heat aging step is performed for a period of time ranging from about 5 h to about 15 h. In some embodiments, the heat aging step lasts for a time period of about 5 h to about 10 h.

[0119]

[1125] In some embodiments of the additive manufacturing process, prior to the heat aging step, the net or near net shape component is heat treated at a temperature of about 400° C. to about 480° C. for a time period of about 0.25 hours to about 6 hours. In some embodiments, the heat treatment temperature is about 400° C., about 410° C., about 420° C., about 430° C., about 440° C., about 450° C., about 460° C., about 470° C., or about 480° C. (including all ranges and values ​​therebetween). In some embodiments, the heat aging is for a time period of about 0.25 h, about 0.5 h, about 0.75 h, about 1 h, about 1.25 h, about 1.5 h, about 1.75 h, about 2 h, about 2.25 h, about 2.5 h, about 2.75 h, about 3 h, about 3.25 h, about 3.5 h, about 3.75 h, about 4 h, about 4.25 h, about 4.5 h, about 4.75 h, about 5 h, about 5.25 h, about 5.5 h, about 5.75 h, or about 6 hours (including all ranges and values ​​therebetween).

[0120]

[1126] In some embodiments, a method for producing an aluminum alloy component includes using wire produced by the methods disclosed herein in an additive manufacturing process to produce a net-shape or near-net-shape component. In some embodiments, the method includes heat treating the net-shape or near-net-shape component at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours after the wire-using step and before the heat-aging step. In some embodiments, the method further includes heat-aging the net-shape or near-net-shape component at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours after the heat-treating step to achieve a simultaneous dispersion of fine-scale Zn2Mg precipitates, primary precipitates having an average diameter of about 0.1 to about 10 μm, and Al-X nanoscale precipitates having an average diameter of about 1 to about 100 nm, resulting in a component having strength at least as great as or greater than that of components conventionally produced from conventional 7000 series aluminum alloys. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, X is Zr.

[0121]

[1127] The present disclosure also provides methods for producing net shape, near net shape, or billet extruded components. The methods include subjecting shaped ribbons, chips, or powders from a 7000 series aluminum alloy disclosed herein to a powder metallurgy process to produce the net shape, near net shape, or billet extruded component. In some embodiments, the powder metallurgy process includes hot pressing, hot isostatic pressing, cold isostatic pressing, powder compaction, hot extrusion, or extrusion.

[0122]

[1128] FIG. 8 shows an overview of some of the steps in a typical powder metallurgy process. In some embodiments, powder metallurgy involves blending powders shaped from the 7000 series aluminum alloys of the present disclosure to form a homogeneous mass having a uniform distribution of particle size and composition. In some embodiments, the powder metallurgy process further involves pressing or consolidating the powders shaped from the 7000 series aluminum alloys of the present disclosure (e.g., powder particles) in a die and sintering the powder to fuse (or bond) the particles together. In some embodiments, pressing is performed at high pressure. In some embodiments, sintering is performed at a temperature between about 300°C and about 650°C, e.g., about 300°C, about 325°C, about 350°C, about 375°C, about 400°C, about 425°C, about 450°C, about 475°C, about 500°C, about 525°C, about 550°C, about 575°C, about 600°C, about 625°C, or about 650°C (including all ranges and values ​​therebetween). In some embodiments, the sintering temperature is below the melting temperature of the major component in the aluminum alloy. In some embodiments, below melting means that the sintering process is carried out at a temperature that is about 70-90% of the melting point of the metal. In some embodiments, sintering is carried out under an inert atmosphere, such as argon or nitrogen. After cooling and optional secondary processing, the finished product is obtained.

[0123]

[1129] In some embodiments, the aluminum alloy powders of the present disclosure used in powder metallurgy processes are made by a rapid solidification process. In some embodiments, the process results in the formation of a powder containing a solid solution of the alloying elements (e.g., Mg, Zn, Zr). In some embodiments, the powder further comprises one or more secondary intermetallic phases. In some embodiments, the powder metallurgy process of the present disclosure is modified by any suitable method to promote the formation of intermetallic phases.

[0124]

[1130] In some embodiments, the powder metallurgy processes disclosed herein can be carried out for about 0.25 hours to about 6 hours (e.g., 0.25 hours, about 0.5 hours, about 0.75 hours, about 1 hour, about 1.25 hours, about 1.5 hours, about 1.75 hours, about 2 hours, about 2.25 hours, about 2.5 hours, about 2.75 hours, about 3 hours, about 3.25 hours, about 3.5 hours, about 3.75 hours, about 4 hours, about 4.25 hours, about 4.5 hours, about 4.75 hours, about 5 hours, about 5.25 hours, about 5.5 hours, about 5.75 hours, or about 6 hours). The method includes heat treating the net shape component, near net shape component, or component extruded from a billet at a temperature of about 400°C to about 480°C (e.g., about 400°C, about 410°C, about 420°C, about 430°C, about 440°C, about 450°C, about 460°C, about 470°C, or about 480°C (including all ranges and values ​​therebetween)) for a period of time (including all ranges and values ​​therebetween).

[0125]

[1131] In some embodiments, the powder metallurgy process disclosed herein further includes heat aging the net shape component, near net shape component, or component extruded from a billet at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours to achieve a co-dispersion of fine-scale Zn2Mg precipitates, primary precipitates, and Al3Zr nanoscale precipitates, resulting in a component having a strength at least as great as or greater than that of a net shape or near net shape component conventionally produced from a conventional 7000 series aluminum alloy. In some embodiments, the primary precipitates have an average diameter in the range of about 0.1 to about 10 μm, e.g., about 0.1 μm, about 0.5 μm, about 1 μm, about 1.5 μm, about 2 μm, about 2.5 μm, about 3 μm, about 3.5 μm, about 4 μm, about 4.5 μm, about 5 μm, about 5.5 μm, about 6 μm, about 6.5 μm, about 7 μm, about 7.5 μm, about 8 μm, about 8.5 μm, about 9 μm, about 9.5 μm, or about 10 μm (including all ranges and values ​​therebetween). In some embodiments, the primary precipitates have an average diameter in the range of about 0.5 to about 1.5 μm. In some embodiments, the primary precipitates have an average diameter in the range of about 0.1 to about 1.5 μm. In some embodiments, the primary precipitates are Al-X primary precipitates. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, X is Zr. In some embodiments, the primary precipitates are AlZr primary precipitates.In some embodiments, the Al-X nanoscale precipitates have a size in the range of about 1 to about 100 nm, e.g., about 1 nm, about 2 nm, about 4 nm, about 6 nm, about 8 nm, about 10 nm, about 12 nm, about 14 nm, about 16 nm, about 18 nm, about 20 nm, about 22 nm, about 24 nm, about 26 nm, about 28 nm, about 30 nm, about 32 nm, about 34 nm, about 36 nm, about 38 nm, about 40 nm, about 42 nm, about 44 nm, about 46 nm, about 48 nm, about 50 nm, about 52 nm, about 54 nm, about 56 nm, about 58 nm, about 59 nm, about 60 nm, about 61 nm, about 62 nm, about 63 nm, about 64 nm, about 65 nm, about 66 nm, about 67 nm, about 68 nm, about 69 nm, about 70 nm, about 71 nm, about 72 nm, about 73 nm, about 74 nm, about 75 nm, about 76 nm, about 77 nm, about 78 nm, about 79 nm, about 80 nm, about 81 nm, about 82 nm, about 83 nm, about 84 nm, about 85 nm, about 86 nm, about 87 nm, about 88 nm, about 89 nm, about 90 nm, about 91 nm, about 92 nm, about 93 nm, about 94 nm, about 95 nm, about 96 nm, about 97 nm, about 98 nm, about 99 nm, about 100 nm, about 101 nm, about 102 nm, about 103 nm, about 104 nm, about 105 nm, about 106 nm, about 107 nm The Al-X nanoscale precipitates have an average diameter of about 50 nm, about 52 nm, about 54 nm, about 56 nm, about 58 nm, about 60 nm, about 62 nm, about 64 nm, about 66 nm, about 68 nm, about 70 nm, about 72 nm, about 74 nm, about 76 nm, about 78 nm, about 80 nm, about 82 nm, about 84 nm, about 86 nm, about 88 nm, about 90 nm, about 92 nm, about 94 nm, about 96 nm, about 98 nm, or about 100 nm (including all ranges and values ​​therebetween). In some embodiments, the Al-X nanoscale precipitates have an average diameter in the range of about 3 to about 50 nm. In some embodiments, the Al3Zr nanoscale precipitates have an average diameter in the range of about 3 to about 20 nm. In some embodiments, the Al-X nanoscale precipitates have an average diameter in the range of about 3 to about 10 nm. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, the nanoscale precipitates are AlZr nanoscale precipitates.

[0126]

[1132] In some embodiments, the heat aging of a net shape component, a near net shape component, or a component extruded from a billet is performed for about 1 hour, about 2 hours, about 3 hours, about 4 hours, about 5 hours, about 6 hours, about 7 hours, about 8 hours, about 9 hours, about 10 hours, about 11 hours, about 12 hours, about 13 hours, about 14 hours, about 15 hours, about 16 hours, about 17 hours, about 18 hours, about 19 hours, about 20 hours, about 21 hours, about 22 hours, about 23 hours, about 24 hours, about 25 hours, about 26 hours, about 27 hours, about 28 hours, about 29 hours, about 30 hours, about 31 hours, about 32 hours, about 33 hours, about 34 hours, about 35 hours, about 36 hours, about 37 hours, about 38 hours, about 39 hours, about 40 hours, about 41 hours, about 42 hours, about 43 hours, about 44 hours, about 45 hours, about 46 hours, about 47 hours, about 48 hours, about 49 hours, about 50 hours, about 51 hours, about 52 hours, about 53 hours, about 54 hours, about 55 hours, about 56 hours, about 57 hours, about 58 hours, about 59 hours, about 60 hours, about 61 hours, about 62 hours, about 63 hours, about 64 hours, about 65 hours, about 66 hours, about 67 hours, about 68 hours, about 69 hours, about 70 hours, about 71 hours, about 72 hours, about 73 hours, about 74 hours, about 75 hours, about 76 hours, about 77 hours, about 78 hours, about 79 hours, about 80 hours, about 81 hours, about The heat aging step may be for a period of time of about 1 hour, about 22 hours, about 23 hours, about 24 hours, about 25 hours, about 26 hours, about 27 hours, about 28 hours, about 29 hours, about 30 hours, about 31 hours, about 32 hours, about 33 hours, about 34 hours, about 35 hours, about 36 hours, about 37 hours, about 38 hours, about 39 hours, about 40 hours, about 41 hours, about 42 hours, about 43 hours, about 44 hours, about 45 hours, about 46 hours, about 47 hours, or about 48 hours (including all ranges and values ​​therebetween). In some embodiments, the heat aging step is for a period of time of about 1 hour to about 10 hours. In some embodiments, the heat aging step is for a period of time of about 1 hour to about 5 hours. In some embodiments, the heat aging step is for a period of time of about 1 hour to about 3 hours. In some embodiments, the heat aging step is for a period of time of about 5 hours to about 20 hours. In some embodiments, the heat aging step lasts for a time period of about 5 hours to about 15 hours. In some embodiments, the heat aging step lasts for a time period of about 5 hours to about 10 hours.

[0127]

[1133] In some embodiments, aluminum alloy components are produced by using a rapid solidification process to shape ribbons, chips, or powder from any of the 7000 series aluminum alloys, and then using the ribbons, chips, or powder in a powder metallurgy process to produce net shape components, near net shape components, or components extruded from a billet. In some embodiments, the method further includes heat treating the net shape component, near net shape component, or component extruded from a billet at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours, and heat aging the component at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours to achieve a simultaneous dispersion of fine-scale ZnMg precipitates, primary precipitates having an average diameter of about 0.1 to about 10 μm, and Al-X nanoscale precipitates having an average diameter of about 1 to about 100 nm, resulting in a component having a strength at least as great as or greater than that of components conventionally produced from conventional 7000 series aluminum alloys. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, X is Zr.

[0128]

[1134] In some embodiments, an aluminum alloy component is produced by shaping a powder from any of the 7000 series aluminum alloys using a rapid solidification process and then using the powder in an additive manufacturing process to produce a net-shape or near-net-shape component. In some embodiments, the method further includes heat treating the net-shape or near-net-shape component at a temperature of about 400°C to about 480°C for a time period of about 0.25 hours to about 6 hours, and then thermally aging the component at a temperature of about 100°C to about 180°C for a time period of about 1 hour to about 48 hours to achieve a simultaneous dispersion of fine-scale Zn2Mg precipitates, primary precipitates having an average diameter of about 0.1 to about 10 μm, and Al-X nanoscale precipitates having an average diameter of about 1 to about 100 nm, resulting in a component having strength at least as great as or greater than that of components conventionally produced from conventional 7000 series aluminum alloys. In some embodiments, X is Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, Mn, Y, La, Ce, Pr, Nd, Pm, Sm, Gd, Tb, Dy, Ho, Er, Tm, Yb, or Lu. In some embodiments, X is Zr.

[0129]

[1135] In some embodiments, a method of repairing or forming a protective coating on a component made from an aluminum alloy or magnesium alloy is provided, the method comprising applying a cold spray process, a thermal spray process, a laser-assisted cold spray process, or a laser cladding process to an aluminum alloy powder disclosed herein, and disposing the treated powder on a surface of a component made from the aluminum alloy, thereby repairing or forming a protective coating on the component.

[0130]

[1136] In some embodiments, a method for repairing or forming a protective coating on a component made from an aluminum alloy is provided, the method comprising applying a cold spray process, a thermal spray process, a laser-assisted cold spray process, or a laser cladding process to an aluminum alloy powder disclosed herein and disposing the treated powder on a surface of the component made from the aluminum alloy, thereby repairing or forming a protective coating on the component.

[0131]

[1137] In some embodiments, the method of repairing or forming a protective coating further comprises heat aging the component made from the aluminum alloy at a temperature of about 100° C. to about 180° C. for a time period of about 1 hour to about 48 hours. In some embodiments, prior to the heat aging step, the component made from the aluminum alloy component of the present disclosure is heat treated at a temperature of about 400° C. to about 480° C. for a time period of about 0.25 hours to about 6 hours.

[0132]

[1138] From the foregoing, it will be appreciated that many modifications and variations may be made without departing from the true spirit and scope of the novel concepts of the present disclosure. It is to be understood that no limitation to the specific embodiments illustrated and described is intended or should be inferred. [Example]

[0133] Example 1

[1139] The chemical compositions and physical properties of Alloy Example 1 (Zr-free) and the new alloy containing Zr are compared in Table 2. Both alloys were fabricated by melt spinning, followed by hot pressing to consolidate into billets, and then extrusion into shapes. After melt spinning, both compositions have similar hardness, but the present alloy exhibits an age-hardening response upon heat treatment, while the example alloy does not (Figure 5). Without being bound by any particular theory, this is believed to be an effect of Al-X precipitates formed during this thermal process. Both alloys respond to the second thermal aging with the formation of conventional Zn2Mg precipitates, and the present alloy retains the same hardness increase relative to the example alloy.

[0134]

[1140] The addition of Zr allows the alloy to reach a higher ultimate strength and improves its thermal stability by maintaining fine grain during high temperature heat treatment, as shown in Figure 3 (Alloy Example 1), Figure 4, and Figure 6.

[0135]

[1141] Scanning electron micrographs of melt-spun ribbons of Alloy Example 1 support these findings, showing large grains (Figure 1). In contrast, scanning electron micrographs of the present alloy, based on Table 2, show highly refined grains with numerous grains in the ribbon (Figure 2). As a result, conventional alloys experience uncontrolled grain growth, which ultimately leads to liquation cracking and hot tearing when the material is welded or subjected to additive manufacturing, but the present aluminum alloy does not. As a result, the present alloy is stronger and more thermally stable.

[0136] [Table 2]

[0137] Example 2

[1142] Attempts have been made to print conventional 7000 series aluminum alloys using an additive manufacturing process, namely selective laser melting (SLM). These attempts have been largely unsuccessful due to hot tearing issues (Alloy Example 1) [HRL, see Sistiaga publication]. To this end, research has been conducted towards developing custom 7000 series alloys tailored for AM processes. One example is an Al-Zn-Mg alloy with a large addition of Sc (Alloy Example 3) [Zhou].

[0138]

[1143] Another solution is to mix the aluminum alloy powder with a second powder that acts as an inoculant to nucleate fine particles during solidification (Alloy Example 2) [HRL]. While technically feasible, this approach adds complexity and cost.

[0139]

[1144] This alloy solves the problem of hot tearing during printing without the use of expensive elements like scandium, while also improving strength over other examples of 3D-printed 7000-series aluminum.

[0140]

[1145] The properties of 7000 series aluminum alloys fabricated by selective laser melting of gas-pulverized powders are listed in Table 3. In all cases, the 3D printed materials underwent a T6 heat treatment, which includes a solutionizing step at approximately 450–480°C followed by an artificial aging step at approximately 120°C.

[0141] [Table 3]

[0142] Example 3:

[1146] The 7000 series alloys can be shaped by rapid solidification processes and consolidated by conventional powder processes. One such alloy is commercially available AA7034, which is produced from melt-spun ribbon that is cut into chips, consolidated by hot pressing into a billet, and extruded into a shape. In this example, the Cu-free 7000 series alloy is produced in powder form by gas powdering (a rapid solidification process), consolidated by hot pressing into a billet, and extruded into a shape (Process 1). Also in this example, the Cu-free 7000 series alloy produced in powder form by gas powdering is extruded directly into a shape without an intermediate consolidation step (Process 2).

[0143]

[1147] The mechanical properties are similar to the commercial alloy, but the elimination of copper from the alloy composition is advantageous to improve weldability and corrosion resistance, and the addition of zirconium is advantageous to improve weldability and thermal stability.

[0144]

[1148] The mechanical properties of the rapidly solidified and extruded 7000 series alloys are provided in Table 4. In all cases, the extruded material underwent a T6 heat treatment, which included a solution treatment step at about 450-480°C followed by an artificial aging step at about 120°C.

[0145] [Table 4]

Claims

1. 7 to 12 wt% zinc, 1 to 4 wt. % magnesium; 1 to 2 wt. % zirconium; 0-3 wt. % copper; Impurities and The balance is aluminum, An aluminum alloy consisting of

2. 2. The aluminum alloy of claim 1, comprising 1.2 to 2 wt. % zirconium.

3. An aluminum alloy as described in claim 1 or 2, containing 1 to 3 weight percent copper.

4. An aluminium alloy according to any one of claims 1 to 3, wherein the alloy contains, as an impurity, less than 0.05% by weight of scandium.

5. An aluminium alloy according to any one of claims 1 to 4, wherein the alloy contains silicon and iron impurities not exceeding 0.3 wt% in total.

6. An aluminum alloy according to any one of claims 1 to 5, wherein the alloy is selected from the group consisting of: a) Al-12Zn-2.6Mg-1.4Zr, b) Al-11Zn-3.2Mg-1.4Zr, c) Al-10Zn-3.0Mg-1.2Zr, and d) Al-11Zn-2.5Mg-1Cu-1.5Zr.

7. An aluminum alloy according to any one of claims 1 to 6, in the form of a powder.

8. An aluminium alloy according to any one of claims 1 to 6 in the form of a wire or rod.

9. An aluminum alloy according to any one of claims 1 to 6 in the form of a wire.

10. An aluminium alloy according to any one of claims 1 to 6 in the form of a rod.

11. An aluminium alloy according to any one of the preceding claims having a yield strength greater than 580 MPa, an ultimate tensile strength greater than 600 MPa and an elongation at break greater than 2%.

12. 1. A method for additively manufacturing a net shape or near net shape component, comprising: a) melting an aluminium alloy according to any one of claims 1 to 6 using a focused energy source; b) fusing the molten alloy as a layer by rapid solidification to an existing substrate or layer of already molten aluminum alloy to provide a net-shape or near-net-shape component; A method comprising:

13. 13. The method of claim 12, wherein the aluminum alloy of step a) is a rod, wire, or powder.

14. 13. The method of claim 12, wherein the aluminum alloy of step a) is a wire.

15. 13. The method of claim 12, wherein the aluminum alloy of step a) is a powder.

16. 16. The method of claim 15, wherein the powder is a spherical aluminum alloy powder.

17. 17. The method of any one of claims 12 to 16, wherein the additive manufacturing comprises a process of powder bed fusion, selective laser melting, or powder directed energy deposition.

18. 18. The method of claim 17, wherein the powder bed fusion, the selective laser melting, or the powder directed energy deposition process comprises subjecting the aluminum alloy to a focused energy source.

19. 20. The method of claim 18, wherein the focused energy source is selected from the group consisting of a laser beam and an electron beam.

20. 17. The method of any one of claims 12 to 16, wherein the additive manufacturing process is powder bed fusion or selective laser melting, using a laser to melt powder and fuse together into a net shape or near net shape component.

21. 17. The method of any one of claims 12 to 16, wherein the additive manufacturing process is powder directed energy deposition, using a laser to melt blow and fuse powder onto a net shape or near net shape component.

22. heat treating the net shape or near net shape component at a temperature of 400°C to 480°C for a time period of 0.25 hours to 6 hours; The method of any one of claims 12 to 21, further comprising:

23. 23. The method of claim 22, wherein after heat treatment, the net shape or near net shape component is heat aged at a temperature of from 100°C to 180°C for a time period of from 1 hour to 48 hours.

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