An aluminum alloy for near net shaped casting of structural components is disclosed. The alloy contains 2 to 10 wt. % Zn, 0.5 to 5 wt. % Mg, 0.5 to 5 wt. %) Fe, optionally Cu, Ti, Sr, Be, Zr, V, Cr, Sc, Na, Si, Mn, Mo, B, and Ni, with balance aluminum. The alloy may be subjected to heat treatment selected from the group consisting of solutionizing, incubation, aging, and two or more heat treatment steps.

Described herein is a method of manufacturing an aluminium alloy rolled product of a heat-treatable aluminium alloy, comprising: semi-continuous casting a heat-treatable aluminium alloy into a rolling ingot; homogenizing of the rolling ingot to a peak metal temperature (PMT) and whereby said aluminium alloy has a specific energy associated with a DSC signal less than 2 J/g in absolute value; hot rolling of the rolling ingot in multiple hot rolling steps into a hot rolled product having a final rolling gauge of at least 1 mm, whereby the hot rolled product during at least one of the last three rolling steps has a temperature less than 50° C. below PMT; quenching of the hot rolled product at final rolling gauge from hot-mill exit temperature to below 175° C.; optionally stress relieving and ageing of the quenched and optionally stress relieved hot rolled product.

Disclosed is a processing technology for inhibiting weld coarse grains of magnesium alloy profiles, including the following steps: preparation of a magnesium alloy ingot, homogenization, scalping, extrusion, pre-stretching at room temperature, solution treatment, quenching, stretching correction, artificial aging, etc. The processing technology can effectively control the production of weld coarse grains in extrusion and heat treatment processes of magnesium alloy profiles, and all property indexes of final products are higher than standard requirements.

Dispersoids 7xxx aluminum alloy products with enhanced fatigue crack growth deviation and Environmentally Assisted Cracking (EAC) resistance are disclosed. The 7xxx aluminum alloy comprises 1 to 3 wt. % Cu, 1.2 to 3 wt. % Mg, 4 to 8.5 wt. % Zn, up to 0.3 wt. % Mn, up to 0.15 wt. % Zr, up to 0.3 wt. % Cr dispersoid elements, incidental elements, and the balance Al. In one embodiment, the alloy includes Zr + Cr + Mn in the range of 0.2 to 0.8 wt. %. In another embodiment, the alloy includes Zr + Mn in the range of 0.07 to 0.7 wt. %. This alloy can be fabricated to plate, extrusion, or forging products, and is especially suitable for aerospace structural components. The products have enhanced EAC resistance and fatigue crack growth deviation resistance. Meanwhile, the products have an excellent combination of strength, fracture toughness, ductility at different orientations, and Stress Crack Corrosion (SCC), and exfoliation corrosion resistance suitable for aerospace application.

Dispersoids 7xxx aluminum alloy products with enhanced fatigue crack growth deviation and Environmentally Assisted Cracking (EAC) resistance are disclosed. The 7xxx aluminum alloy comprises 1 to 3 wt. % Cu, 1.2 to 3 wt. % Mg, 4 to 8.5 wt. % Zn, up to 0.3 wt. % Mn, up to 0.15 wt. % Zr, up to 0.3 wt. % Cr dispersoid elements, incidental elements, and the balance Al. In one embodiment, the alloy includes Zr + Cr + Mn in the range of 0.2 to 0.8 wt. %. In another embodiment, the alloy includes Zr + Mn in the range of 0.07 to 0.7 wt. %. This alloy can be fabricated to plate, extrusion, or forging products, and is especially suitable for aerospace structural components. The products have enhanced EAC resistance and fatigue crack growth deviation resistance. Meanwhile, the products have an excellent combination of strength, fracture toughness, ductility at different orientations, and Stress Crack Corrosion (SCC), and exfoliation corrosion resistance suitable for aerospace application.

Disclosed herein are aluminum alloy products and methods of making the aluminum alloy products. Specifically, disclosed herein is an aluminum alloy provided in a temper achieved by rapidly quenching the aluminum alloy product after hot rolling. The aluminum alloys provided in the tempers described herein allow an end user to further process the aluminum alloys using less time and requiring less energy.

Described herein are formable, high strength aluminum alloy products and methods of preparing and processing the same. The methods of preparing and processing the aluminum alloy products include casting an aluminum alloy and performing tailored rolling and downstream thermal processing steps. The resulting aluminum alloy products possess high strength and formability properties.

Described herein are formable, high strength aluminum alloy products and methods of preparing and processing the same. The methods of preparing and processing the aluminum alloy products include casting an aluminum alloy and performing tailored rolling and downstream thermal processing steps. The resulting aluminum alloy products possess high strength and formability properties.

A method for forming a structure using an interim temper process is provided. A metal material is partially-aged to a stable temper that does not require cold storage. The partially-aging step is completed at a supplier facility prior to the metal material being received by the manufacturer. Once received by the manufacturer, the partially-aged metal material is heated to a first temperature to perform retrogression. A structure is formed from the partially-aged metal material after performing the retrogression. The structure is shaped and inspected. The structure is then heated to a second temperature in an age oven to reach its final aged state. The final aged state may be close to, meet, or exceed a T6 temper.

The invention relates to a rolled composite aerospace product comprising a 2XXX-series core layer and an Al—Mg alloy clad layer coupled to at least one surface of the 2XXX-series core layer, wherein the Al—Mg alloy is a 5XXX-series aluminium alloy comprising 0.4% to 4.8% Mg, and preferably 0.7% to 4.5% Mg.