Abstract: An aluminum alloy for structures with increased electrical resistivity, consisting essentially of: 1.0-5.0% by weight of Li; one or a plurality of members selected from the group consisting of not more than 0.20% by weight of Ti, 0.05-0.40% by weight of Cr, 0.05-0.30% by weight of Zr, 0.05-0.35% by weight of V and 0.05-0.30% by weight of W; and the balance being aluminum, and impurities which would inevitably be included in the alloy. The aluminum alloy may further include (a) not more than 5.0% by weight of Mn, and/or (b) 0.05-5.0% by weight of Cu and/or 0.05-8.0% by weight of Mg.

Abstract: A clad material for use in heat exchangers comprises a core metal layer made of an aluminum base alloy containing Mg, and a cladding metal layer made of an aluminum base alloy containing Sn and Mg. The core metal layer can contain at least one metal selected from the group consisting of Mn, Si, Cr, Cu and Zr, and a cladding metal layer can also contain at least one metal selected from the group consisting of Zn, Ti, In and Ga.

Abstract: A high electrical resistance, superior formability aluminum alloy useful as structural materials used in structures suffering the action of high magnetic field, nuclear fusion reactor or the like, said aluminum alloy consisting essentially of, by weight, 1.0 to 8.0% of Mg, 0.05 to less than 1.0% of Li, at least one element selected from the group consisting of 0.05 to 0.20% of Ti, 0.05 to 0.40% of Cr, 0.05 to 0.30% of Zr, 0.05 to 0.35% of V, 0.05 to 0.30% of W and 0.05 to 2.0% of Mn, and the balance being aluminum and incidental impurities. Further, Bi in the range of 0.05 to 0.50 wt. % may be contained in said alloy.

Abstract: A plate fin heat exchanger adapted to applications using superhigh-pressure fluids was fabricated by brazing, the heat exchanger using as fin stock an alloy consisting essentially of 0.3 to 1.0 wt. % Si, 0.05 to 0.25 wt. % Cu, 0.6 to 1.5 wt. % Mn and 0.45 to 0.9 wt. % Mg, the balance being aluminum and impurities, wherein said impurities contain up to 0.8 wt. % Fe.At least one component selected from the group consisting of 0.05 to 0.25 wt. % Cr, 0.01 to 0.25 wt. % Ti, 0.03 to 0.25 wt. % Zr and 0.01 to 0.25 wt. % V may be added to the above fin alloy stock.By using the above plate fin, excessive silicon diffusion from a brazing alloy into the fin, which may cause reduction of width of the brazed joint, is suppressed, and as a result, lowering of the bonding strength of the brazed joint is eliminated.

Abstract: An aircraft stringer material having high strength, small grain size, good resistance to stress corrosion cracking and a very high degree of workability is produced from an aluminum base alloy consisting essentially of 5.1 to 8.1 wt. % Zn, 1.8 to 3.4 wt. % Mg, 1.2 to 2.6 wt. % Cu, up to 0.20 wt. % Ti and at least one of 0.18 to 0.35 wt. % Cr and 0.05 to 0.25 wt. % Zr, the balance being aluminum and impurities, by a production method characterized by a special annealing step including rapid heating to a temperature of 320.degree. to 500.degree. C. at a heating rate exceeding 11.degree. C./min.Further, a corrosion-resistant stringer material is produced in a manner very similar to the above production method, using the above aluminum alloy as a core and AA7072 alloy as cladding.

Abstract: An aluminum alloy material having a high strength, small grain size, good resistance to stress corrosion cracking and very high degree of workability is produced from an aluminum base alloy consisting essentially of 5.1 to 8.1 wt. % Zn, 1.8 to 3.4 wt. % Mg, 1.2 to 2.6 wt. % Cu, up to 0.2 wt. % Ti and at least one of 0.18 to 0.35 wt. % Cr and 0.05 to 0.25 wt. % Zr, the balance being aluminum and impurities by an improved production method described in detail in the disclosure. The improved method is particularly characterized by a special annealing step in a continuous annealing furnace under the application of a tension not exceeding 2 kg/mm.sup.2 to a coiled alloy sheet to be annealed, the annealing including rapid heating of the coiled alloy sheet to a temperature of 400.degree. to 500.degree. C. at a heating rate exceeding 50.degree. C./min.

Abstract: An aircraft stringer material having high strength, small grain size, good resistance to stress corrosion cracking and a very high degree of workability is produced from an aluminum base alloy consisting essentially of 5.1 to 8.1 wt. % Zn, 1.8 to 3.4 wt. % Mg, 1.2 to 2.6 wt. % Cu, up to 0.20 wt. % Ti and at least one of 0.18 to 0.35 wt. % Cr and 0.05 to 0.25 wt. % Zr, the balance being aluminum and impurities, by a production method characterized by a special annealing step including rapid heating to a temperature of 320.degree. to 500.degree. C. at a heating rate exceeding 11.degree. C./min.Further, a corrosion-resistant stringer material is produced in a manner very similar to the above production method, using the above aluminum alloy as a core and AA7072 alloy as cladding.

Abstract: An aluminum alloy, excellent concurrently in strength and formability, suitably used in car bodies, essentially contains Mg within the range between 3.5 and 5.5%, Zn within the range between 0.5 and 2.0%, and Cu within the range between 0.3 and 1.2%, wherein percents are all by weight; and another still further improved aluminum alloy, excellent concurrently in strength and formability, suitable for similar use, and finer in grain size, indispensably contains all the abovementioned three essential elements in the same ranges of percent by weight, and has optionally added thereto one or more of the elements selected from Mn within the range between 0.05 and 0.4%, Cr within the range between 0.05 and 0.25%, Zr within the range between 0.05 and 0.25%, and V within the range between 0.01 and 0.15%, wherein percents are all by weight.