Aluminium alloys chemical composition pdf

Continue Alloy in which aluminum is the predominant lye frame of aluminum welded aluminium alloy, manufactured in 1990. Aluminum alloys (or aluminium alloys; see spelling differences) are alloys in which aluminium (Al) is the predominant metal. Typical alloy elements are copper, magnesium, manganese, silicon, tin and zinc. There are two main classifications, namely casting alloys and forged alloys, both further subdivided into heat-treatable and heat-free categories. Approximately 85% of aluminium is used for forged products, e.g. laminated plates, foils and extrusions. Aluminum cast alloys produce cost-effective products due to their low melting point, although they generally have lower tensile strength than forged alloys. The most important cast aluminium alloy system is Al–Si, where high silicon levels (4.0–13%) contributes to giving good casting features. Aluminum alloys are widely used in engineering structures and components where a low weight or corrosion resistance is required. [1] Alloys composed mostly of aluminium have been very important in aerospace production since the introduction of metal leather aircraft. Aluminum-magnesium alloys are both lighter than other aluminium alloys and much less flammable than other alloys containing a very high percentage of magnesium. [2] Aluminum alloy surfaces will develop a white layer, protective of aluminum oxide, if not protected by proper anodization and/or dyeing procedures. In a wet environment, galvanic corrosion can occur when an aluminum alloy is placed in electrical contact with other metals with a more positive corrosion potential than aluminum, and an electrolyte is present that allows the exchange of ions. Called different metal corrosion, this process may appear as exfoliation or intergranular corrosion. Aluminum alloys can be treated improperly thermally. This causes the internal elements to separate, and the metal then corrodes from the inside out. [citation required] Aluminum alloy compositions are registered with the Aluminum Association. Many organizations publish more specific standards for the manufacture of aluminum alloy, including the Society of Automotive Engineers standards organization, in particular its aerospace standards subgroups,[3] and ASTM International. Engineering of use and aluminum alloys properties aluminum alloy alloy wheel bike. 1960 Bootie Folding Cycle Aluminum Alloys with a wide range of properties are used in engineering structures. Alloy systems are classified by a numerical system (ANSI) or by name indicating their main alloy constituents (DIN and ISO). Selecting the right alloy a particular application involves considerations of tensile strength, density, ductility, formality, manoeuvrability, weldability and corrosion resistance, to name a few. A brief historical overview of alloys and manufacturing technologies is in Ref.[4] Aluminum alloys are widely used in aircraft due to the high strength-to-weight ratio. On the other hand, pure aluminium metal is far too soft for such uses and does not have the high tensile strength required for aeroplanes and helicopters. Aluminum alloys compared to steel types Aluminum alloys usually have an elastic module of about 70 GPa, which accounts for about one third of the elastic module of most types of steel and steel alloys. Therefore, for a given load, an aluminium alloy component or unit will present a greater deformation of the elastic regime than a steel part of identical size and shape. Although there are aluminum alloys with slightly higher tensile strength than the commonly used steel types, simply replacing a steel part with an aluminum alloy could lead to problems. With completely new metal products, design options are often governed by the choice of manufacturing technology. Extrusions are particularly important in this regard, due to the ease with which aluminum alloys, especially the Al–Mg–Si series, can be extruded to form complex profiles. In general, stiffer and lighter models can be made with aluminum alloy than is possible with steels. For example, consider bending a thin-walled tube: the second surface moment is inversely related to the stress in the tube wall, i.e. the voltages are lower for higher values. The second moment of the surface is proportional to the cube of the radius or the thickness of the wall, thus increasing the radius (and weight) by 26% will lead to a halving of the stress of the wall. For this reason, aluminium alloy bike frames use larger tube diameters than steel or titanium to achieve the desired stiffness and strength. In automotive engineering, aluminum alloy cars use space frames from extruded profiles to ensure rigidity. This represents a radical change from the common approach to the current design of the steel machine, which depend on the body shells for stiffness, known as unibody design. Aluminum alloys are widely used in motor engines, especially in cylindrical and carter blocks due to the weight savings that are possible. Because aluminum alloys are susceptible to deformation at high temperatures, the cooling system of these engines is critical. Manufacturing techniques and metallurgical advances have also been essential for the successful application of motor engines. In the 1960s, the aluminium cylindrical ends of the Corvair gained a reputation for the failure and untying of wires, which is not seen in the current ends of the aluminium cylinders. A limitation important of aluminum alloys is their lower fatigue resistance compared to steel. Under laboratory controlled conditions, the steels display a fatigue limit, which is the stress amplitude under which no malfunctions occur – the metal does not to lose weight with extensive stress cycles. Aluminum alloys do not have this lower fatigue limit and will continue to lose weight with continuous stress cycles. Therefore, aluminum alloys are poorly used in parts that require high fatigue resistance in the high cycle regime (more than 107 stress cycles). Considerations of sensitivity to heat Often, the sensitivity of metal to heat must also be taken into account. Even a relatively routine workshop procedure involving heating is complicated by the fact that aluminum, unlike steel, will melt without first shining red. Training operations where a blow torch is used can reverse or eliminate thermal treatment, therefore, no way is recommended. No visual sign reveals how the material is internally damaged. Just like treated heat welding, high chain strength link, all strength is now lost to the heat of the torch. The chain is dangerous and must be discarded. Aluminium is subject to internal demands and tensions. Sometimes, years later, so is the tendency of aluminum bike frames improperly welded to gradually twist out of alignment from the stresses of the welding process. Thus, the aerospace industry avoids heat altogether by joining the parts with rivets of metallic composition, other fasteners or adhesives. The voltages in the overheated aluminium can be eased by the thermal treatment of the parts in an oven and their gradual cooling – in fact, by reanimating the voltages. However, these parts can still become distorted, so the thermal treatment of welded bicycle frames, for example, can lead to a significant fraction of becoming unaligned. If the non-alignment is not too severe, the cooled parts may be bent into alignment. Of course, if the frame is properly designed for stiffness (see above), that bending will require enormous force. The intolerance of aluminium at high temperatures did not prevent its use in rockets; even for use in the construction of combustion chambers where gases can reach 3500 K. The upper-stage engine used a regenerative lymine-cooled design for parts of the nozzle, including the thermally critical neck region; in fact, the extremely high thermal conductivity of aluminium prevented the neck from reaching the melting point even under massive thermal flux, resulting in a reliable and light component. Household cabling Main article: Aluminum wire Due to its high conductivity and relatively low price compared to copper in 1960, aluminum was introduced at that time for household electrical cables in North America, even many luminaires were not designed to accept aluminum wire. But the new use brought some problems: The higher thermal expansion coefficient of aluminum causes the extension of the wire and the contract in relation to the different connection of the metal screw, eventually weakening the connection. Pure aluminium tends to crawl under sustained constant pressure (to a greater extent than the temperature to loosen the connection again. The galvanic corrosion of different metals increases the electrical resistance of the connection. All this has led to overheated and free connections, and this in turn has led to some fires. Builders then became wary of using wire, and many jurisdictions outlawed its use in very small sizes in new constructions. However, newer bodies were eventually introduced with connections designed to avoid weakening and overheating. At first they were marked with Al/Cu, but now they carry a CO/ALR encoding. Another way to prevent the heating problem is to crimp the short pig tail of copper wire. A suitably high-pressure crimping of the appropriate task is tight enough to reduce any thermal expansion of the aluminium. Today, new alloys, models and methods are used for aluminum cables in combination with aluminum endings. Alloy names Forged and cast aluminium alloys use different identification systems. Forged aluminium is identified with a four-digit number that identifies alloy elements. Aluminum cast alloys use a number of four to five digits with one decimal place. The figure in the place of hundreds indicates the alloy elements, while the figure after the decimal point indicates the shape (cast or ingot). Temperament name The temperament name follows the name number cast or forged with a line, a letter and possibly a number of one to three digits, e.g. 6061-T6. Definitions for temperaments are:[5][6] -F: As manufactured -H: Hardened strain (cold worked) with or without heat treatment -H1: Hardened strain without heat treatment -H2: Strengthened and partially re- elected strain -H3: Hardened and stabilized strain by low temperature heating Second digit: A second digit denotes the degree of hardness -HX2 = 1/4 hard -HX4 = 1/2 hard -HX6 = 3/4 hard -HX8 = full hard -HX9 = extra hard -O : Full soft (annealyd) -T : Heat treated to produce stable temperaments -T1 : Cool from hot working and naturally aged (at room temperature) -T2: Cool from hot work, cold-worked, and naturally aged -T3: Heat-treated and cold-treated solution worked -T4: Heat-treated and natural-aged solution -T5 : Cold from hot working and in artificial age (at high temperature) -T51 : Stress released by stretching -T510 : No straightening after stretching -T511 : Minor straightening after stretching -T52 : Stress released by heat treatment -T6 : Heat-treated and artificial-aged solution -T7 : Heat-treated and stabilized solution -T8 : Heat-treated solution, cold worked, and artificial lye -T9: Heat-treated solution, artificial lye, and cold worked -T10: Cooled from hot work, cold-worked, artificially aged -W: Heat solution treated only Note: -W is a relatively soft intermediate name, which is applied after heat treatment and before aging is completed. -W -W can be extended to extremely low temperatures, but not indefinitely and, depending on the material, will not last more than 15 minutes at ambient temperatures. Forged Alloys The International Alloy Designation System is the most widely accepted naming system for forged alloys. Each alloy is given a four-digit number, where the first digit indicates the major alloy elements, the second - if different from 0 - indicates a variation of the alloy, and the third and fourth digits identify the specific alloy in the series. For example, in alloy 3105, number 3 indicates that the alloy is in the manganese series, 1 indicates the first modification of alloy 3005 and, finally, 05 identifies it in the 3000 series. [7] The 1000 Series is essentially pure aluminium with an aluminium content of at least 99% by weight and can be strengthened by work. The 2000 series are alloyed with copper, can be precipitated reinforced at strengths comparable to steel. Previously referred to as duralumin, they were once the most common aerospace alloys, but were susceptible to stress of cracking corrosion and are increasingly being replaced by the 7000 series in new models. The 3000 series are allied with manganese, and can be work hardened. The 4000 Series are silicon-allied. Variations of aluminium-silicon alloys intended for casting (and therefore not included in the 4000 series) are also known as silumin. The 5000 Series is magnesium-alled and offers superb corrosion resistance, suitable for marine applications. The 5083 alloy also has the highest strength of heat-treated alloys. Most alloys in the 5000 series include manganese as well. The 6000 series are alloyed with magnesium and silicon. They are easy to process, are welded, and can be hardened precipitation, but not to the high resistances that 2000 and 7000 can reach. The 6061 alloy is one of the most widely used aluminium alloys for general use. The 7000 series are alloyed with zinc and can be reinforced with the highest strength of any aluminium alloy (final tensile strength of up to 700 MPa for the 7068 alloy). Most 7000 series alloys include magnesium and copper as well. The 8000 series are allied with other elements that are not covered by other series. Aluminum-lithium alloys are an example. [8] Series 1000 1000 series 1000 series aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy Alloy Elements Uses and refs 1050 99.5 - Drawing tube, Chemical equipment 1060 99.6 - Universal 1070 99.7 - Thick wall-drawn tube 1100 99.0 With 0.1 Universal, holloware 1145 99.45 - Sheet, plate, foil 1199 99.99 - Foil[9] 1200 99.0 max (Si + Fe) 1.0 max; 0.05 max; Mn 0.05 max; Zn 0,10 max; Ti 0.05 max; others 0.05 (each) .015 (total) [10] 1230 (VAD23)# And 0.3; Fe 0,3; 4.8–5.8; Mn 0.4–0.8; Mg 0.05; Zn 0.1; Ti 0.15; Li Cd 0.1–0.25 Tu-144 Aircraft[11] 1350 99.5 - Electrical Conductors 1370 99.7 - Electric Electric 1420# 92.9 mg 5.0; Li 2.0; Zr 0.1 Aerospace 1421# 92.9 Mg 5.0; Li 2.0; Mn 0,2; Sc 0.2; Zr 0.1 Aerospace[12] 1424# And 0.08; Fe 0,1; Mn 0.1–0.25; Mg 4.7–5.2; Zn 0.4–0.7; Li 1.5–1.8; Zr 0.07–0.1; Be 0.02–0.2; Sc 0.05–0.08; Na 0.0015 [11] 1430# And 0.1; Fe 0,15; 1.4–1.8; Mn 0.3–0.5; Mg 2.3–3.0; Zn 0.5–0.7; Ti 0.01–0.1; Li 1.5–1.9; Zr 0.08–0.14; Be 0.02–0.1; Sc 0.01–0.1; Na 0.003; What 0.2–0.4; Y 0.05–0.1 [11] 1440# And 0.02–0.1; Fe 0.03–0.15; 1.2–1.9; Mn 0.05; Mg 0.6–1.1; Cr 0.05; Ti 0.02–0.1; Li 2.1–2.6; Zr 0.10–0.2; Be 0.05–0.2; Na 0.003 [11] 1441# And 0.08; Fe 0,12; 1.5–1.8; Mn 0.001–0.010; Mg 0.7–1.1; Ti 0.01–0.07; Ni 0.02–0.10; Li 1.8–2.1; Zr 0.04–0.16; Be 0.02–0.20 Be-103 and Be-200 seaplanes[11] 1441K# And 0.08; Fe 0,12; 1.3–1.5; Mn 0.001–0.010; Mg 0.7–1.1; Ti 0.01–0.07; Ni 0.01–0.15; Li 1.8–2.1; Zr 0.04–0.16; Be 0.002–0.01 [11] 1445# And 0.08; Fe 0,12; 1.3–1.5; Mn 0.001–0.010; Mg 0.7–1.1; Ti 0.01–0.1; Ni 0.01–0.15; Li 1.6–1.9; Zr 0.04–0.16; Be 0.002–0.01; Sc 0.005–0.001; Ag 0.05–0.15; As 0.005–0.04; Na 0.0015 [11] 1450# And 0.1; Fe 0,15; 2.6–3.3; Mn 0.1; Mg 0,1; Cr 0.05; Zn 0.25; Ti 0.01–0.06; Li 1.8–2.3; Zr 0.08–0.14; Be 0.008–0.1; Na 0.002; What 0.005–0.05 Aircraft An-124 and An-225[11] 1460# And 0.1; Fe 0.03–0.15; 2.6–3.3; Mg 0.05; Ti 0.01–0.05; Li 2.0–2.4; Zr 0.08–0.13; Na 0.002; Sc 0.05– 0.14; B 0.0002–0.0003 Aircraft Tu-156[11] V-1461# And 0.8; Fe 0.01–0.1; 2.5–2.95; Mn 0.2–0.6; Mg 0.05–0.6; Cr 0.01–0.05; Zn 0.2–0.8; Ti 0.05; Ni 0.05–0.15; Li 1.5–1.95; Zr 0.05–0.12; Be 0.0001–0.02; Sc 0.05–0.10; As 0.001–0.05; Na 0.0015 [11] V-1464# And 0.03–0.08; Fe 0.03–0.10; 3.25–3.45; Mn 0.20–0.30; Mg 0.35–0.45; Ti 0.01–0.03; Li 1.55–1.70; Zr 0.08–0.10; Sc 0.08–0.10; Be 0.0003–0.02; Na 0.0005 [11] V-1469# And 0.1; Fe 0,12; 3.2–4.5; Mn 0.003–0.5; Mg 0,1–0,5; Li 1.0–1.5; Zr 0.04–0.20; Sc 0.04–0.15; Ag 0.15–0.6 [11] # There is an international system for designating alloy designation designation 2000 series 2000 aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy elements Uses and refs 2004 93.6 With 6.0; Zr 0.4 Aerospace 2011 93.7 With 5.5; Bi 0.4; Pb 0.4 Universal 2014 93.5 With 4.4; And 0.8; Mn 0,8; Mg 0.5 Universal 2017 94.2 With 4.0; And 0.5; Mn 0.7; Mg 0.6 Aerospace 2020 93.4 With 4.5; Li 1.3; Mn 0.55; Cd 0.25 Aerospace 2024 93.5 With 4.4; Mn 0,6; Mg 1.5 Universal, Aerospace[13] 2029 94.6 With 3.6; Mn 0,3; Mg 1.0; Ag 0,4; Zr 0.1 Alclad Sheet, Aerospace[14] 2036 96.7 With 2.6; Mn 0.25; Mg 0.45 Sheet 2048 94.8 With 3.3; Mn 0,4; Mg 1.5 Sheet, plate 2055 93.5 With 3.7; Zn 0,5; Li 1.1; Ag 0,4; Mn 0,2; Mg 0,3; Zr 0.1 Aerospace Extrusions,[15] 2080 94.0 Mg 3.7; Zn 1.85; Cr 0.2; Li 0.2 Aerospace 2090 95.0 With 2.7; Li 2.2; Zr 0.12 Aerospace 2091 94.3 With 2.1; 2.0; Mg 1,5; Zr 0.1 Aerospace, cryogenics 2094 And 0.12; Fe 0,15; 4.4–5.2; Mn 0.25; Mg 0.25–0.8; Zn 0.25; Ti 0.10; Ag 0.25–0.6; Li 0.7–1.4; Zr 0.04–0.18 [11] 2095 93.6 With 4.2; Li 1.3; Mg 0,4; Ag 0,4; Zr 0.1 Aerospace 2097 And 0.12; Fe 0,15; 2.5–3.1; Mn 0.10–0.6; Mg 0.35; Zn 0.35; Ti 0.15; Li 1.2–1.8; Zr 0.08–0.15 [11] 2098 And 0.12; Fe 0,15; With 2.3–3.8; Mn 0.35; Mg 0.25–0.8; Zn 0.35; Ti 0.10; Ag 0.25–0.6; Li 2.4–2.8; Zr 0.04–0.18 [11] 2099 94.3 With 2.53; Mn 0,3; Mg 0.25; Li 1.75; Zn 0.75; Zr 0.09 Aerospace[16] 2124 93.5 With 4.4; Mn 0,6; Mg 1.5 Plate 2195 93.5 With 4.0; Mn 0,5; Mg 0.45; Li 1.0; Ag 0,4; Zr 0.12 Aerospace,[17][18] Space Shuttle Super Lightweight external tank,[19] and SpaceX Falcon 9[20] and Falcon 1st launch vehicles in stage two. [21] 2196 And 0.12; Fe 0,15; 2.5–3.3; Mn 0.35; Mg 0.25–0.8; Zn 0.35; Ti 0.10; Ag 0.25–0.6; Li 1.4–2.1; Zr 0.08–0.16[11] Extrusion 2197 And 0.10; Fe 0,10; 2.5–3.1; Mn 0.10–0.50; Mg 0.25; Zn 0.05; Ti 0.12; Li 1.3–1.7; Zr 0.08–0.15 [11] 2198 Sheet 2218 92.2 With 4.0; Mg 1,5; Fe 1.0; And 0.9; Zn 0.25; Mn 0.2 Forgings, aircraft engine cylinders[22] 2219 93.0 With 6.3; Mn 0,3; Ti 0.06; V 0,1; Zr 0.18 Universal, Space Shuttle Standard Weight external tank 2297 And 0.10; Fe 0,10; 2.5–3.1; Mn 0.10–0.50; Mg 0.25; Zn 0.05; Ti 0.12; Li 1.1–1.7; Zr 0.08–0.15 [11] 2397 And 0.10; Fe 0,10; 2.5–3.1; Mn 0.10–0.50; Mg 0.25; Zn 0.05–0.15; Ti 0.12; Li 1.1– 1.7; Zr 0.08–0.15 [11] 2224&2324 93.8 With 4.1; Mn 0,6; Mg 1.5 Plate[13] 2319 93.0 Cu 6.3; Mn 0,3; Ti 0.15; V 0,1; Zr 0.18 Bar and Wire 2519 93.0 With 5.8; Mg 0,2; Ti 0.15; V 0,1; Zr 0.2 Aerospace Armor Plate 2524 93.8 With 4.2; Mn 0,6; Mg 1.4 Plate, sheet[23] 2618 93.7 With 2.3; And 0.18; Mg 1.6; Ti 0.07; Fe 1.1; Ni 1.0 Forgings series 3000 series 3000 series aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy elements Uses and refs 3003 98.6 Mn 1.5; With 0.12 Universal, sheet, rigid foil containers, signs, decorative 3004 97.8 Mn 1.2; Mg 1 Universal, beverage cans[24] 3005 98.5 Mn 1.0; Mg 0.5 Work Strengthened 3102 99.8 Mn 0.2 Work Strengthened[25] 3103&3303 98.8 Mn 1.2 Work Strengthened 3105 97.8 Mn 0.55; Mg 0.5 Sheet 3203 98.8 Mn 1.2 Sheet, high strength foil 4000 series 4000 series aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy elements Uses and refs 4006 98.3 Si 1.0; Fe 0.65 Hardened or aged 4007 96.3 And 1.4; No 1.2; Fe 0,7; Ni 0.3; Cr 0.1 Hard work 4015 96.8 And 2.0; Mn 1.0; Mg 0.2 Strengthened work 4032 85 And 12.2; 0.9; Mg 1; Ni 0.9; Forgings 4043 94.8 And 5.2 Rod 4047 85.5 And 12.0; Fe 0,8; 0.3; Zn 0.2; Mn 0.15; Mg 0.1 Sheet, plaging, fillings[26] 4543 93.7 And 6.0; Mg 0.3 architectural extrusions 5000 series 5000 series aluminum alloy nominal compositions (% weight) and applications Alloy Al content Alloy elements Uses and refs & & 99.2 Mg 0.8 Sheet, plate, rod 5010 99.3 Mg 0.5; Mn 0,2; 5019 94.7 mg 5.0; Mn 0.25; 5024 94.5 mg 4.6; Mn 0,6; Zr 0.1; Sc 0.2 Extrusions, Aerospace[27] 5026 93.9 Mg 4.5; No. and 0.9; Fe 0,4; With 0.3 5050 98.6 Mg 1.4 Universal 5052 & 5652 97.2 Mg 2.5; Cr 0.25 Universal, aerospace, marine 5056 94.8 Mg 5.0; Mn 0,12; Cr 0.12 Foil, rod, rivets 5059 93.5 Mg 5.0; Mn 0,8; Zn 0.6; Zr 0.12 cryogenic missile tanks 5083 94.8 Mg 4.4; Mn 0.7; Cr 0.15 Universal, welding, marine 5086 95.4 Mg 4.0; Mn 0,4; Cr 0.15 Universal, welding, marine 5154 & 5254 96.2 Mg 3.5; Cr 0.25; Universal rivets[28] 5182 95.2 Mg 4.5; Mn 0.35; Sheet 5252 97.5 mg 2,5; Sheet 5356 94.6 mg 5.0; Mn 0,12; Cr 0,12; Ti 0.13 Rod, wire MIG 5454 96.4 Mg 2.7; Mn 0,8; Cr 0.12 Universal 5456 94 Mg 5.1; Mn 0,8; Cr 0.12 Universal 5457 98.7 mg 1.0; Mn 0,2; With 0.1 Sheet, auto-asian[29] 5557 99.1 Mg 0.6; Mn 0,2; With 0.1 Sheet, auto-asian[30] 5754 95.8 Mg 3.1; Mn 0,5; Cr 0.3 Sheet, Rod series 6000 series 6000 aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy Alloy Elements Uses and refs 6005 98.7 And 0.8; Mg 0.5 Extrusions, angles 6009 97.7 and 0.8; Mg 0,6; Mn 0,5; With 0.35 Sheet 6010 97.3 And 1.0; Mg 0,7; Mn 0,5; With 0.35 Sheet 6013 97.05 And 0.8; Mg 1.0; Mn 0.35; With 0.8 Plate, aerospace, smartphone cases[31][32] 6022 97.9 And 1.1; Mg 0,6; Mn 0.05; 0.05; Fe 0.3 Sheet, auto[33] 6060 98.9 And 0.4; Mg 0,5; Fe 0.2 Thermal Treatable 6061 97.9 And 0.6; Mg 1.0; 0.25; Cr 0.2 Universal, structural, aerospace 6063 & 646g 98.9 And 0.4; Mg 0.7 Universal, marine, decorative 6063A 98.7 And 0.4; Mg 0,7; Fe 0.2 Heat treatment 6065 97.1 And 0.6; Mg 1.0; 0.25; Bi 1.0 Heat treatment 6066 95.7 And 1.4; Mg 1.1; Mn 0,8; With 1.0 Universal 6070 96.8 And 1.4; Mg 0,8; Mn 0.7; With 0.28 Extrusions 6081 98.1 And 0.9; Mg 0,8; Mn 0.2 Heat treatment 6082 97.5 And 1.0; Mg 0.85; Mn 0.65 Heat treatment 6101 98.9 And 0.5; Mg 0.6 Extrusions 6105 98.6 And 0.8; Mg 0.65 Heat treatment 6113 96.8 And 0.8; Mg 1.0; Mn 0.35; 0.8; O 0.2 Aerospace 6151 98.2 And 0.9; Mg 0,6; Cr 0.25 Forgings 6162 98.6 And 0.55; Mg 0.9 Heat treatment 6201 98.5 And 0.7; Mg 0.8 Rod 6205 98.4 And 0.8; Mg 0,5; Mn 0.1; Cr 0.1; Zr 0.1 Extrusions 6262 96.8 And 0.6; Mg 1.0; 0.25; Cr 0.1; Bi 0.6; Pb 0.6 Universal 6351 97.8 And 1.0; Mg 0,6; Mn 0.6 Extrusions 6463 98.9 And 0.4; Mg 0.7 Extrusions 6951 97.2 And 0.5; Fe 0,8; 0.3; Mg 0,7; Mn 0.1; Zn 0.2 Heat-treatable 7000 series 7000 series aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy Alloy Elements Uses and refs 7005 93.3 Zn 4.5; Mg 1.4; Mn 0.45; Cr 0.13; Zr 0.14; Ti 0.04 Extrusions 7010 93.3 Zn 6.2; Mg 2.35; With 1.7; Zr 0.1; Aerospace 7022 91.1 Zn 4.7; Mg 3.1; Mn 0,2; 0.7; Cr 0.2; plate, moulds[34][35] 7034 85.7 Zn 11.0; Mg 2.3; With 1.0 Supreme Traction Resistance 750 MPa[36] 7039 92.3 Zn 4.0; Mg 3.3; Mn 0,2; Cr 0.2 aerospace armor 7049 88.1 Zn 7.7; Mg 2.45; 2,45; 1.6; Cr 0.15 Universal, Aerospace 7050 89.0 Zn 6.2; Mg 2.3; With 2.3; Zr 0.1 Universal, Aerospace 7055 87.2 Zn 8.0; Mg 2.3; With 2.3; Zr 0.1 Plate, extrusion, aerospace[37] 7065 88.5 Zn 7.7; Mg 1.6; With 2.1; Zr 0.1 Plate, aerospace[38] 7068 87.6 Zn 7.8; Mg 2,5; With 2.0; Zr 0.12 Aerospace, Supreme Traction Resistance 710 MPa 7072 99.0 Zn 1.0 Sheet, foil 7075 & 7175 90.0 Zn 5.6; Mg 2,5; With 1.6; Cr 0.23 Universal, aerospace, forgings 7079 91.4 Zn 4.3; Mg 3.3; 0.6; Mn 0,2; Cr 0.15 - 7085 89.4 Zn 7.5; Mg 1,5; With 1.6 Thick, aerospace plate[39] 7093 86.7 Zn 9.0; Mg 2,5; With 1.5; O 0.2; Zr 0.1 Aerospace 7116 93.7 Zn 4.5; Mg 1; With 0.8 Heat treat7129 93.2 Zn 4.5; Mg 1.6; With 0.7 - 7150 89.05 Zn 6.4; Mg 2.35; With 2.2; O 0.2; Zr 0.1 Aerospace 7178 88.1 Zn 6.8; Mg 2.7; With 2.0; Cr 0.26 Universal, Aerospace 7255 87.5 Zn 8.0; Mg 2.1; With 2.3; Zr 0.1 Plate, aerospace[40] 7475 90.3 Zn 5.7; Mg 2.3; And 1.5; Cr 0.22 Universal, aerospace series 8000 series 8000 aluminum alloy nominal composition (% weight) and applications Alloy Al content Alloy Alloy Elements Uses and refs 8006 98.0 Fe 1.5; Mn 0,5; Universal, weldable 8009 88.3 Fe 8.6; And 1.8; V 1.3 High-temperature aerospace[41] 8011 98.7 Fe 0.7; And 0.6 Strengthened work 8014 98.2 Fe 1.4; Mn 0,4; universal[42] 8019 87.5 Fe 8.3; Ge 4.0; O 0.2 Aerospace 8025 And 0.05; Fe 0.06–0.25; 0.20; Mg 0.05; Cr 0.18; Zn 0.50; Ti 0.005–0.02; Li 3.4–4.2; Zr 0.08–0.25 [11] 8030 99.3 Fe 0.5; With 0.2 wire[43] 8090 and 0.20; Fe 0,30; 1.0–1.6; Mn 0,10; Mg 0.6–1.3; Cr 0,10; Zn 0.25; Ti 0.10; Li 2.2–2.7; Zr 0.04–0.16 [11] 8091 And 0.30; Fe 0.50; 1.0–1.6; Mn 0,10; Mg 0.50–1.2; Cr 0,10; Zn 0.25; Ti 0.10; Li 2.4–2.8; Zr 0.08–0.16 [11] 8093 And 0.10; Fe 0,10; 1.6–2.2; Mn 0,10; Mg 0.9–1.6; Cr 0,10; Zn 0.25; Ti 0.10; Li 1.9–2.6; Zr 0.04–0.14 [11] 8176 99.3 Fe 0.6; And 0.1 Electric Wire[44] Mixed List Limits of Forged Aluminum Alloy Composition (% Weight) Alloy Si Fe With Mn Mg Cr Zn V Ti Bi Ga Pb Zr Limits†† Al Each Total 1050[45] 0. 25 0.40 0.05 0.05 0.05 0.05 0.03 99.5 min 1060 0.25 0.35 0.05 0.028 0.03 0.03 0.05 0.05 0.05 0.028 0.03 0.03 0.03 0.028 99.6 min 1100 0.95 Si+Fe 0.05–0.20 0.05 0.0 10 0.05 0.15 99.0 min 1199[45] 0.006 0.006 0.006 0.002 0.006 0.006 0.005 0.002 0.005 0.002 99.99 min 2014 0.50–1.2 0.7 3.9–5.0 0.40–1.2 0.20–0.8 0.1 0.25 0.15 0.05 0.15 remainder 2024 0.50 0.50 3.8–4.9 0.30–0.9 1.2–1.8 0.10 0.25 0.15 0.05 0.15 r 2219 0.2 0.30 5.8–6.8 0.20–0.40 0.02 0.10 0.05–0.15 0.02–0.10 0.10–0.25 0.05 0.15.6 0.7 0.05–0.20 1.0–1.5 0.10 0.05 0.15 remainder 3004 0.30 0.7 0.25 1.0–1.5 0.8–1.3 0.25 0.05 0.15 remainer 3102 0.40 0.7 0.10 0.05–0.40 0.30 0.10 0.05 0.15 remaining 4041 4.5–6.15 0 0.80 0.30 0.05 0.05 0.10 0.20 0.05 0 ,15 remain 5005 5005 5005 0.3 0.7 0.2 0.2 0.5-1.1 0.1 0.25 0.05 0.15 remain 5052 0.25 0.40 0.10 0.10 2.2–2.8 0.15–0.35 0.15 remainder 5083 0.40 0.40 0.10 0.40–1.0 4.0–4.9 0.05–0.25 0.25 0.15 0.05 0.15 remainder 5086 0.40 0.50 0.50 0.50 10 0.20–0.7 3.5–4.5 0.05–0.25 0.25 0.15 0.05 0.15 finder 5154 0.25 0.40 0.10 0.10 3.10–3.90 0.15–0.35 0.20 0.20 0.05 0.15 remainder 5356 0.25 0.40 0.10 0.10 4.50–5.50 0.05–0.20 0.10 0.06–0.20 0.05 0.15 remember 5454 0.25 0.40 0.10 0.50–1.0 2.4–3.0 0.05–0.20 0.25 0.20 0.05 0.15 finder 5456 0.25 0.40 0.10 0.50–1.0 4.7–5.5 0.05–0.20 0.25 0.20 0.05 0.15 finder 5754 0.40 0.40 0.10 0.50 2.6–3.6 0.30 0.20 0.1 5 0.05 0.15 remainder 6005 0.6–0.9 0.35 0.10 0.10 0.40– 0.6 0.10 0.10 0.10 0.05 0.15 remainder 6005A† 0.50–0 0.9 0.35 0.30 0.50 0.40–0.7 0.30 0.20 0.10 0.05 0.15 remainder 6060 0.30–0.6 0.10–0.30 0.10 0.10 0.35–35–35–35 0.6 0.05 0.15 0.10 0.05 0.15 remainder 6061 0.40–0.8 0.7 0.15–0.40 0.15 0.8–1.2 0.04–0.35 0.25 0.15 0.05 0.15 remainder 6063 0.20–0.6 0.10 0.10 0.45–0.9 0.10 0.10 0.10 0.05 0.15 remainder 6066 0.9–1.8 0.50 0.7–1.2 0.6–1 0.8–1.4 0.40 0.25 0.20 0.05 0.15 remainder 6070 1.0–1.7 0.50 0.15–0.40 0.40–1.0 0.50–1.2 0.10 0.25 0.15 0.05 0.15 remainder 6082 0.7–1.3 0.10 0.40–1.0 0.60–1.2 0.25 0.20 0.1 0.05 0.15 remainder 6105 0.6–1.0 0.35 0.10 0.10 0.45–0.8 0.10 0.10 0.10 0.05 0.15 remainder 6162 0.40– 0.8 0.50 0.20 0.10 0.7–1 0.10 0.25 0.10 0.05 0.15 finder 6262 0.40–0.8 0.7 0.15–0.40 0.15 0.8–1.2 0.04–0.14 0.25 0.15 0.40–0.7 0.40–0.7 0.05 0.15 finder 6351 0.7–1.3 0.50 0.10 0.40–0.8 0.40–0.8 0.20 0.20 0.05 0.15 remainder 6463 0.20–0.6 0.15 0.20 0.05 0.45–0.9 0.05 0.05 0.15 remainder 7005 0.35 0.4 0.10 0.20–0.70 1.0–1.8 0.06–0.20 4.0–5.0 0.01–0.06 0.08–0.20 0.05 0.15 finder 7022 0.50 0.50 0.50–1.00 0.10–0.40 2.60–3.70 0.10–0.30 4.30–5.20 0.05 0.15 remainder 7068 0.12 0.15 1.60–2.40 0.10 2.20–3.00 0.05 7.30–8.30 0.01 0.05–0.15 0.05 0.15 remainder 7072 0.7 Si+Fe 0.10 0.10 0.10 0.8–1.3 0.05 0.15 remainder 7075 0.40 0.50 1.2–2.0 0.30 2.1–2.9 0.18–0.28 5.1–6.1 0.20 0.05 0.15 remainder 7079 0.3 0.40 0.40–0.80 0.10–0.30 2.9–3.7 0.10–0.25 3.8–4.8 0.10 0.05 0.15 remainder 7116 0.15 0.30 0.50– 1.1 0.05 0.8–1.4 4.2–5.2 0.05 0.05 0.03 0.05 0.15 rest 7129 0.15 0.30 0.50 –0.9 0.10 1.3–2.0 0.10 4 ,2–5.2 0.05 0.05 0.03 0.05 0.15 remain7178 0.40 0.0.0.0.05 0.15 remain7178 0.40 0.0.0.05 0.15 0.15 rest 7178 0.40 0.0.0.03 0.05 0.15 rest 7178 0.40 0.0.0.03 0.05 0.15 rest 7178 0.40 0.0.0.0.0.0.0.0.0.0.03 50 1.6–2.4 0.30 2.4–3.1 0.18–0.28 6.3–7.3 0.20 0.05 0.15 remain8176[44] 0 .03–0.15 0.40– 1.0 0.10 0.03 0.05 0.15 rest Alloy Si Fe Cu Mn Mg Cr Zn V Ti Bi Bi Ga Pb Zr Limits†† Al Each Total †Manganess plus chrome must be between 0.12–0.50%.††This limit applies to all items for which no other limit is specified in a given row because there is no column or because the column is blank. Casting Alloys The Aluminium Association (AA) has adopted a nomenclature similar to that of Alloys. British Standard and DIN have different names. In the AA system, the second two digits indicate the minimum percentage of aluminium, e.g. 150.x correspond scans to a minimum of 99.50% aluminium. The figure after the decimal point takes a value of 0 or 1, denoting the casting and ingots, respectively. [1] The main alloying elements in the AA system are as follows:[46] 1xx.x series are minimum 99% aluminium 2xx.x series copper 3xx.x series silicon, with added copper and/or magnesium 4xx.x series silicon 5xx.x series magnesium 6xx.x unused series 7xx.x series zinc 8xx.x series tin 9xx.x other elements Minimum tensile requirements for cast aluminium alloys[47] Alloy type Temper Tensile strength (min) in ksi (MPa) Yield strength (min) in ksi (MPa) Elongation in 2 in % ANSI UNS 201.0 A02010 T7 60.0 (414) 50.0 (345) 3.0 204.0 A02040 T4 45.0 (310) 28.0 (193) 6.0 242.0 A02420 O 23.0 (159) N/A N/A T61 32.0 (221) 20.0 (138) N/A A242.0 A12420 T75 29.0 (200) N/A 1.0 295.0 A02950 T4 29.0 (200) 13.0 (90) 6.0 T6 32.0 (221) 20.0 (138) 3.0 T62 36.0 (248) 28.0 (193) N/A T7 29.0 (200) 16.0 (110) 3.0 319.0 A03190 F 23.0 (159) 13.0 (90) 1.5 T5 25.0 (172) N/A N/A T6 31.0 (214) 20.0 (138) 1.5 328.0 A03280 F 25.0 (172) 14.0 (97) 1.0 T6 34.0 (234) 21.0 (145) 1.0 355.0 A03550 T6 32.0 (221) 20.0 (138) 2.0 T51 25.0 (172) 18.0 (124) N/A T71 30.0 (207) 22.0 (152) N/A C355.0 A33550 T6 36.0 (248) 25.0 (172) 2.5 356.0 A03560 F 19.0 (131) 9.5 (66) 2.0 T6 30.0 (207) 20.0 (138) 3.0 T7 31.0 (214) N/A N/A T51 23.0 (159) 16.0 (110) N/A T71 25.0 (172) 18.0 (124) 3.0 A356.0 A13560 T6 34.0 (234) 24.0 (165) 3.5 T61 35.0 (241) 26.0 (179) 1.0 443.0 A04430 F 17.0 (117) 7.0 (48) 3.0 B443.0 A24430 F 17.0 (117) 6.0 (41) 3.0 512.0 A05120 F 17.0 (117) 10.0 (69) N/A 514.0 A05140 F 22.0 (152) 9.0 (62) 6.0 520.0 A05200 T4 42.0 (290) 22.0 (152) 12.0 535.0 A05350 F 35.0 (241) 18.0 (124) 9.0 705.0 A07050 T5 30.0 (207) 17.0 (117)† 5.0 707.0 A07070 T7 37.0 (255) 30.0 (207)† 1.0 710.0 A07100 T5 32.0 (221) 20.0 (138) 2.0 712.0 A07120 T5 34.0 (234) 25.0 (172)† 4.0 713.0 A07130 T5 32.0 (221) 22.0 (152) 3.0 771.0 A07710 T5 42.0 (290) 38.0 (262) 1.5 T51 32.0 (221) 27.0 (186) 3.0 T52 36.0 (248) 30.0 (207) 1.5 T6 42.0 (290) 35.0 (241) 5.0 T71 48.0 (331) 45.0 (310) 5.0 850.0 A08500 T5 16.0 (110) N/A 5.0 851.0 A08510 T5 17.0 (117) N/A 3.0 852.0 A08520 T5 24.0 (165) 18.0 (124) N/A †Only when requested by the customer Named alloys A380 Offers an excellent combination of casting, mechanical and thermal properties, exhibits excellent fluidity, pressure tightness and resistance to hot cracking. Used in the aerospace industry Alferium an aluminium-iron alloy developed by Schneider, used for the manufacture of aircraft by Société pour la Construction d'Avions Métallique Aviméta Alclad aluminum foil consisting of high-purity aluminium surface layers glued to high aluminium alloy base material (aluminum, magnesium) a product of Birmetals Company, practically equivalent to 5251 Duralumin (copper, aluminum) Hindalium (aluminum, magnesium, manganese, silicon) product of Hindustan Aluminium Corporation Ltd, manufactured in 16ga laminate sheets for Pandalloy Pratt&Whitney cooking pots alloy owner, supposed to have high strength and superior performance at high temperature. Magnalium Magnox (magnesium, aluminium) Silumin (aluminum, silicon) Titanal (aluminum, zinc, magnesium, copper, zirconium) a product of Austria Metall AG. Frequently used in high performance sports products, especially snowboard and skis. Alloy Y, Heduminium Alloys, R.R.: pre-war nickel-aluminum alloys, used in aerospace and engine pistons, for their ability to maintain their resistance at high temperature. They are replaced nowadays with high-performance iron-aluminum alloys, would be 8009, capable of operating with low creep up to 300C. Aerospace Alloy Applications Aluminum–Scandium Parts of Mig–29 are made of Al–Sc. alloy [49] The addition of scandium to aluminum creates Nanoscale Al3Sc precipitates that limit the excessive growth of cereals that occurs in the heat-affected area of welded aluminium components. This has two beneficial effects: The precipitated Al3Sc forms smaller crystals than are formed in other aluminum alloys[49] and the width of the precipitateless areas that normally exist at the grain limits of aluminum alloys that can be strengthened according to age is reduced. [49] Scandium is also a powerful grain refiner in cast aluminum alloys, and atom for atom, the strongest aluminum enhancer, both as a result of grain refinement and precipitation consolidation. An additional benefit of the additions of scandium to aluminium is that the al3sc precipitates at the nanoscale that give the alloy its strength are resistant to coarseness at relatively high temperatures (~350 °C). This is in contrast to the typical commercial 2xxx and 6xxx alloys, which quickly lose their power at temperatures above 250 °C due to the rapid coarseness of their hardening precipitates. [50] The effect of Al3Sc precipitates also increases the strength of the alloy yield by 50–70 MPa (7.3–10.2 ksi). In principle, aluminum alloys reinforced with scandium additions are very similar to traditional basic nickel superalloys, in which both are reinforced by consistent, coarse-resistant precipitates with an orderly L12 structure. However, Al-Sc alloys contain a much smaller volume fraction of precipitate, and the inter-precipitated distance is much smaller than in their nickel base counterparts. In both cases, however, coarse-resistant precipitates allow alloys to retain their at high temperatures. [51] The increase in the operating temperature of Al-Sc alloys has significant implications for energy-efficient applications, especially in the automotive industry. These alloys can provide a replacement for denser such as steel and titanium which are used in environments of 250-350 °C, would be engines in or near them. Replacing these materials with lighter aluminium alloys leads to weight reductions, which in turn leads to increased fuel efficiency. [52] The additions of erbium and zirconium have been shown to increase the coarse resistance of Al-Sc alloys to ~400 °C. This is achieved by forming a zirconium-rich shell around the precipitated scandium and erbium cores, forming hardening precipitates with the composition Al3(Sc,Zr,Er). [53] Further improvements in coarse resistance will allow these alloys to be used at increasingly high temperatures. Titanium alloys, which are stronger but heavier than Al-Sc alloys, are still much more widely used. [54] The main application of metal plank by weight is in aluminum-scandium alloys for minor components of the aerospace industry. These alloys contain between 0.1% and 0.5% (by weight) of scandium. They were used in russian military aircraft Mig 21 and Mig 29. [49] Some items of sports equipment, which are based on high-performance materials, were made with scandium-aluminum alloys, including baseball bats,[55] lacrosse sticks, as well as bicycle frames and components,[56] and tent poles. American weapons manufacturer Smith & Wesson produces frame revolvers composed of scandium alloy and titanium cylinders. [57] List of aerospace aluminium alloys The following aluminium alloys are commonly used in aircraft and other aerospace structures:[58][59] 1420 2004; 2014; 2017; 2020; 2024; 2080; 2090; 2091; 2095; 2219; 2224; 2324; 2519; 2524 4047 6013; 6061; 6063; 6113; 6951; 7010; 7049; 7050; 7055; 7068; 7075; 7079; 7093; 7150; 7178; 7475; 8009; Note that the term aluminium for aircraft or aerospace aluminium usually refers to 7075. [60] [61] Aluminum 4047 is a unique alloy used in both the aerospace industry and automotive applications as a plaging alloy or filler. As a filler, aluminum alloy 4047 strips can be combined to complicated applications to bind two metals. [62] 6951 is a heat-treatable alloy that provides additional resistance to fins while increasing sag resistance; this allows the manufacturer to reduce the track gauge of the sheet and therefore reduce the weight of the formed fin. These distinctive features make the 6951 aluminium alloy one of the preferred heat transfer alloys and heat exchangers manufactured for aerospace applications. [63] Aluminum alloys 6063 can be heat-treated with moderately high resistance, excellent corrosion resistance and good extrusion. They are regularly used as architectural and [64] The following list of aluminium alloys is currently produced,[required citation] but less widespread[required citation] used: 2090 aluminum 2124 aluminum 2324 aluminum 6013 aluminum 7050 aluminum 7055 aluminum 7150 aluminum 7475 aluminum Marine alloys These alloys alloys used for boat construction and shipbuilding, as well as other maritime and water-sensitive applications. [65] 5052 aluminum alloy 5059 aluminum alloy 5083 aluminum alloy 5086 aluminum alloy 6061 aluminum alloy 6063 aluminum alloy 4043, 5183, 6005A, 6082 also used in marine construction and off shore applications. Cycling Alloys These alloys are used for frames and components for cycling[required citation] 2014 aluminum 6061 aluminum 6063 aluminum 7005 aluminum 7075 aluminum Scandium aluminum Alloys car 6111 aluminum and aluminum alloy 2008 are widely used for exterior car body panels, with 5083 and 5754 used for interior panels of the bodywork. The hoods were manufactured from 2036, 6016 and 6111 alloys. The body panels of trucks and trailers used 5456 aluminium. Car frames often use 5182 sheets of aluminum or 5754 of aluminum, 6061 or 6063 extrusions. The wheels were cast from aluminum A356.0 or formed 5xxx sheet. [66] Cylindrical blocks and carters are often cast from aluminum alloys. The most popular aluminum alloys used for cylindrical blocks are A356, 319 and to a lesser extent 242. 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