A method for controlling continuous heat treating and annealing of heat-treatable and non-heat-treatable aluminum alloy sheet at final thickness continuously moving in a floating state horizontally through a continuous convection floating furnace arranged to heat the moving aluminum sheet to a set peak metal temperature. The controlling including controlling fan speeds and furnace air temperature to accommodate variations in line speed of the aluminum alloy sheet continuously moving in the floating state horizontally through the continuous convection floating furnace

A wire rod made of an aluminum alloy. The aluminum alloy includes Al crystal grains, an Al—Zr compound, and an Al—Co—Fe or Al—Ni—Fe compound. The aluminum alloy includes high-angle tilt crystal grain boundaries, each of which has a difference between crystal orientations in both its sides of 15 degrees or more, and low-angle tilt crystal grain boundaries, each of which has a difference between crystal orientations in both its sides of 2 degrees or more and less than 15 degrees. An average grain diameter of ones of the Al crystal grains surrounded by the high-angle boundaries is 12 μm or more. An average grain diameter of the ones of the Al crystal grains surrounded by the high-angle boundaries, ones of the Al crystal grains surrounded by the high-angle boundaries and the low-angle boundaries, and ones of the Al crystal grains surrounded by the low-angle boundaries, is 10 μm or less.

An alloy which consists of aluminum, titanium, scandium and zirconium with or without one, two or more further metals selected from hafnium, vanadium, niobium, chromium, molybdenum, silicon, iron, cobalt, nickel and calcium. The aluminum alloy is suitable for the additive manufacture of lightweight components for aircraft. In a first additive manufacturing step, such as laser melting by the L-PBF process (laser powder bed fusion), a lightweight component precursor is produced from a powder of the aluminum alloy of the invention, this precursor comprising titanium, scandium and zirconium in solid solution, as a result of rapid solidification of the laser melt. In a second step the lightweight component precursor is hardened by precipitation of secondary phases at 250 to 400° C. to give the lightweight component. 3D-printed lightweight components of high strength are obtained.

A device includes a capsule extending longitudinally from a proximal end to a distal end and including a channel extending therethrough. The capsule is releasably coupled to a proximal portion of the device. Device also includes a first arm rigidly fixed to the distal end of the capsule to extend distally therefrom. In addition, Device includes a second arm, a proximal end of which is slidably received within the capsule so that the second arm is movable between an open configuration, in which the second arm is moved laterally away from the first arm and a distal end of the second arm is moved distally past the distal end of the first arm, and a closed configuration, in which the second arm is moved toward the first arm and the distal end of the second arm is moved proximally toward the distal end of the first arm.

A palladium-copper-silver alloy consisting of 40 to 58% by weight of palladium, 25 to 42% by weight of copper, 6 to 20% by weight of silver, optionally up to 6% by weight of at least one element from the group ruthenium, rhodium, and rhenium, and up to 1% by weight of impurities, wherein the palladium-copper-silver alloy contains a crystalline phase with a B2 crystal structure and has 0% by volume to 10% by volume of precipitates of silver, palladium, and binary silver-palladium compounds. The invention also relates to a molded body, a wire, a strip, or a probe needle made of such a palladium-copper-silver alloy and to the use of such a palladium-copper-silver alloy for testing electrical contacts or for electrical contacting or for the production of a sliding contact. The invention also relates to a method for producing a palladium-copper-silver alloy.

A nickel-based alloy is disclosed which is suitable for casting gas turbine components having improved strength and comparative lower density while utilizing commercially available heat treatment cycles. The nickel-based alloy is suitable for providing equiaxed, directionally solidified, and single crystal castings. Methods of providing a cast article of the nickel-based alloy and subjecting the article to heat treatment cycles are also disclosed.

An object of the present disclosure is to provide a method for manufacturing an aluminum alloy plastically-processed article, capable of preventing a burning crack from occurring due to processing heat generated during plasticity processing while maintaining a solution-treatment temperature of an aluminum alloy material for ensuring a mechanical strength thereof. A method for manufacturing an aluminum alloy plastically-processed article, includes a step of performing a solution treatment for an aluminum alloy material by heating and maintaining the aluminum alloy material at a solution-treatment temperature, a step of performing plasticity processing for the aluminum alloy material subjected to the solution treatment, and steps of cooling the plastically-processed aluminum alloy material at a time at which the step of the plasticity processing is completed, and aging the cooled aluminum alloy material. The method further includes pre-plasticity-processing cooling step of cooling the aluminum alloy material subjected to the solution treatment.

A high-strength and high-toughness magnesium alloy includes a Mg—Al—Bi—Sb—Zn—Sr—Y—Mn alloy, prepared from the following components in percentage by mass: 7.0 to 10.0% of Al, 0.2 to 2.0% of Bi, 0.2 to 0.8% of Sb, 0.2 to 0.5% of Zn, 0.1 to 0.5% of Sr, 0.03 to 0.3% of Y, 0.05 to 0.1% of Mn and a balance of Mg.

High strength and high fracture toughness 7xxx aluminum alloy products comprise 6.5 to 7.2 wt. % Zn, 1.55 to 1.95 wt. % Cu, 1.75 to 2.15 wt. % Mg, 0.095 to 0.15 wt. % Zr, incidental elements, and the balance Al. In one embodiment, the aluminum alloy product includes Mg/Cu and Zn/Mg ratios in the range of 1.05 to 1.35, and 3.2 to 4.0, respectively. This aluminum alloy product can be fabricated to produce plate, extrusion or forging products, and is especially suitable for aerospace structural components. The products have an excellent combination of strength, fracture toughness, K.sub.max at the fatigue crack deviation point, ductility in different orientations, and corrosion resistance suitable for aerospace application.

A method for the manufacturing of an object. The method includes receiving a desired alloy composition for the object, depositing a plurality of foils in a stack to form the object, applying heat to the stack at a first temperature to bond the plurality of foils to each other, and applying heat to the stack at a second temperature to homogenize the composition of the stack. The homogenized stack has the desired alloy composition.