The present disclosure discloses a method for manufacturing an equal-hardness Cr5 back up roll. The method comprises the following steps: 1) preparing a steel raw material according to chemical components and weight percentage contents in a Cr5 back up roll material, and preparing a steel ingot according to a smelting procedure production process; 2) preparing a roller blank from the steel ingot according to a forging procedure production process; 3) performing thermal treatment on the roller blank; and 4) processing and detecting the roller blank to obtain an equal-hardness forged steel back up roll. The present disclosure solves problems that a hardness, an abrasion resistance, and a contact fatigue of a conventional forged steel back up roll are rapidly reduced in a middle and later use period, and prolongs a comprehensive use period and a service life of the back up roll.

The disclosure discloses a method of producing a magnesium alloy wheel hub, comprises the following steps: step 1, heating a magnesium alloy bar to 350-430° C. and keeping the temperature for 20 minutes; step 2, initially forging and forming the bar under a forging press, the forging speed is 6-15 mm/s; step 3, finally forging and forming the bar under a forging press, and the forging speed is 5-8 mm/s; step 4, testing the microstructure and material properties of the final forged blank to obtain the layered material property distribution on the thickness of the blank; step 5, according to the layered material property distribution on the thickness of the blank obtained in step 4, selecting the part that meets the requirements to make a magnesium alloy wheel hub. According to the different properties in the thickness direction of the blank, the spoke orientation of the magnesium alloy wheel can be quickly designed according to the needs, and the magnesium alloy wheel that meets the usage performance can be obtained, which greatly improves the design and processing efficiency.

An aluminum-silicon carbide composite including flat-plate-shaped composited portion containing silicon carbide and an aluminum alloy, and aluminum layers containing an aluminum alloy provided on both plate surfaces of composited portion, wherein circuit board is mounted on one plate surface and the other plate surface is used as heat-dissipating surface, wherein: the heat-dissipating-surface-side plate surface of the composited portion has a convex curved shape; the heat-dissipating-surface-side aluminum layer has a convex curved shape; ratio (Ax/B) between the average (Ax) of the thicknesses at the centers on opposing short sides of outer peripheral surfaces and thickness (B) at central portions of the plate surfaces satisfies the relationship: 0.91≤Ax/B≤1.00; and a ratio (Ay/B) between the average (Ay) of the thicknesses at the centers on opposing long sides of outer peripheral surfaces and thickness (B) at central portions of the plate surfaces satisfies the relationship: 0.94≤Ay/B≤1.00 and production method therefor.

A superalloy seamless pipe and a preparation method thereof are provided. The superalloy seamless pipe comprises the following components in percentages by weight: C:0.01-0.06%, Si:0.40-1.00%, Mn:0.30-1.00%, P≤0.025%, S≤0.020%, Cr:15.00-17.00%, Ni:44.00-46.00%, Al:2.90-3.90%, Ce:0.01-0.03%, Ti:0.10-0.30%, N:0.03-0.08%, and the balance of Fe and inevitable impurities.

A method of forming a copper manganese sputtering target including subjecting a copper manganese billet to a first unidirectional forging step, heating the copper manganese billet to a temperature from about 650° C. to about 750° C., subjecting the copper manganese billet to a second unidirectional forging step, and heating the copper manganese billet to a temperature from about 500° C. to about 650° C. to form a copper alloy.

The invention provides a method and a product for manufacturing a titanium alloy dual-structure turbine disk based on partial hydrogenation, which includes the following steps: coating a glass coating on the partial surface of a titanium alloy billet where hydrogen-blocking is required, and sintering the titanium alloy billet coated with the glass coating; performing hydrogenation treatment on the titanium alloy billet, such that the hydrogen concentration at the hydrogenation-required portion reaches the predetermined level; removing the glass coating from the titanium alloy billet; preheating the titanium alloy billet, and then performing high temperature die forging in the forging dies; performing vacuum dehydrogenation treatment on the forged turbine disk to remove hydrogen element inside the forging, so that the hydrogen content is 0.015 wt. % or less.

An exemplary process includes determining a desired pore size, selecting an initial pore size greater than the target pore size, manufacturing a porous structure with the initial pore size, forging the porous structure to form a forged part having the desired pore size, and forming an orthopedic device from the forged part.

Described is a method of modifying material properties of a workpiece using a high-pressure-torsion apparatus, comprising a working axis, a first anvil, a second anvil, and an annular body, comprising a first recirculating convective chiller, a second recirculating convective chiller, and a heater, positioned between the first recirculating convective chiller and the second recirculating convective chiller along the working axis. The method comprises compressing the workpiece along a central axis of the workpiece and. simultaneously with compressing the workpiece along the central axis, twisting the workpiece about the central axis. The method further comprises. while compressing the workpiece along the central axis and twisting the workpiece about the central axis, translating the annular body along the working, axis of the high-pressure-torsion apparatus, collinear with the central axis of the workpiece, and heating the workpiece with the heater.

The invention relates to a method for manufacturing a laminated or forged material, the thickness of which is 14 to 100 mm. The materials according to the invention are particularly suitable for manufacturing airplane underwing elements.

An exemplary process includes determining a desired pore size, selecting an initial pore size greater than the target pore size, manufacturing a porous structure with the initial pore size, forging the porous structure to form a forged part having the desired pore size, and forming an orthopedic device from the forged part.