Aluminum Profile Factories, Manufacturers, Suppliers

“Mill Finish” is the natural appearance of the aluminum as it comes from the rolling mill or the extrusion mill. It is “as is” with no external mechanical or chemical finishing. Extruded metal is considered “mill finish”. All aluminum has an oxide of some varying thickness. Anodizing is a very heavy controlled oxide. Anodizing is an electrolytically formed and controlled heavy oxide 0.0003 inches thick on up the 0.002 and on up. Mill Finish is a very lightly oxidized film and will wipe off with your bare finger and immediately form. Rolled sheet would probably have a thinner oxide than hot extruded aluminum. If you want to bond silicone adhesive then you want a phosphate etch, or a light chromate or a thin (.0004 anodize in either chromic, sulfuric, or phosphoric.) If you anodize, do not seal the coating and be sure your anodizer knows you do not want it sealed.

The 2016 Chinese Lunar New Year will be on Feb. 8 and it is the year of the Monkey. Think Christmas but the date varies based on the lunar calendar, however, it normally falls between mid-Jan to end of Feb.

As important as the Chinese New Year is for those celebrating across Asia and around the world, it should also be significantly important for importers and those working with Chinese manufacturers. The Chinese New Year basically shuts down all production facilities throughout the country and it’s usually much more than a 3-day weekend.

Experienced importers are usually well aware of this time and the delay they can expect for shipments coming out of China around this time. The time is especially crucial for those that have businesses selling seasonal merchandise such as apparel and sporting goods. Failing to implement proper precautions during the Chinese New Year can result in heavy losses for businesses. And the variable date is one of the factors that can usually lead to confusion and planning complexities.

So what do you need to know as we approach the year of the Monkey?

1. Usually all production and sample development is halted a week to 2 weeks prior to Chinese New Years Eve.
   It’s hard to put it in perspective if you haven’t been in China during this time. Majority of factory workers are going back and forth to their hometowns, combined with families traveling around China to visit relatives.
2. Production is usually suspended for at least 2 weeks after the Chinese New Year
   While the holiday itself lasts roughly 5 days, most people seize the opportunity and extend the holiday by an extra week or two. So you may not be able to reach someone for 2 weeks or more about your order during this time.
3. Getting back to normal is sometimes a struggle
   Think about that first Monday after your 2-week long vacation. Well it’s similar in a way and many manufacturers do struggle to get back into normal mode, but they eventually do.

So to recap, the Chinese New Year can turn into a 2-3 week shutdown for most factories and it’s a time of the year where majority of the people in the country are traveling. As a good rule of thumb, importers should do their research on the holiday and proactively schedule their orders and deliveries well before everyone gets in vacation mode.

Also keep in mind that leading up to the Chinese New Year, your supplier is probably rushing to fulfill orders for most of their buyers and get them shipped before they post the ‘We’ll Be Back’ sign on their doors. It is on you as a buyer to ensure that proper quality control standards are met during this time by making sure you hire a local inspector to perform a pre or post manufacturing inspection.

Formability or workability is generally defined as the amount of deformation that can be given to a specimen without fracture or necking in a given process. Workability is not an intrinsic material property; it depends on design variables:

Therefore, for a given shape, workability is a function of material and process variables and can be expressed as

Workability = ƒ₁ (material) -ƒ₂ (process)where ƒ₁ is a measure of the ductility of the material under processing conditions, represented by forming limit criteria developed for various processes. Forming limit criteria based on limiting strains are of practical applicability because strains, as opposed to stresses, are easy to visualize and analyze in workability studies. The ƒ₂ function, on the other hand, is given by stress, strain, strain-rate, and temperature histories at the potential failure sites of the work piece.

A complete workability analysis involves:

This comparison reveals the margin of safety for the deformation processing of a defect-free product. When a negative margin exists, it assists in deciding on the necessary changes in material or process variables, or both.

Free surfaces are the most commonly observed fracture sites in bulk deformation processes. In most cases, free-surface fractures determine the limits of deformation that can be imparted to the deforming material. Such fractures occur at the free surfaces of the specimen during processing, for example, edge cracking in rolling, surface cracking in bending, heading, open-die forging, or surface cracking before contact is achieved between the preform and the die walls in an impression-die forging.

There is developed a fracture criterion, based on limiting strains-to-fracture, for the prediction and prevention of surface cracks in bulk deformation processes. Local strains calculated from measurements, at fracture, of grid markings on the free surfaces of cylinders upset under different friction conditions and with different height-to-diameter ratios, are plotted. Fracture strains obtained from bend tests, measured by grid markings on convex surfaces of bend specimens, fall onto the extension of the fracture line determined by compression tests. Thus, bend tests are complimentary to compression tests, and are particularly useful when compression testing is not feasible.

The material function ƒ₁, has not been studied systematically. Recently, has examined the effect of size, shape, and volume fraction of second-phase particles on the bulk formability of American Iron and Steel Institute (AISI) 1040, 1060, and 1090 carbon steels. The present study evaluates the workability of three heat-treatable aluminum alloys as influenced by aging and accompanying structural changes.

Three heat-treatable aluminum alloys (2014, 2024, and 7075) were received in the form of 12.7 mm diameter rods. The 2014 (≈100HB) and 2024 (≈130HB) aluminum alloys were in T4 condition. The 7075 alloy was received in T6 condition (≈150 HB).

Chemical compositions of aluminum alloys:

The degree of banding in the 2014 aluminum alloy was more severe, and the elongated grains were larger near the surface. These large grains at the surface layers caused surface wrinkling during upset testing of the alloy, necessitating machining off a layer of 0.7 mm thickness from the surface in order to bring the wrinkling to an acceptable level. In the 2024 and 7075 aluminum alloys, surface wrinkling was minimal; the original surfaces were preserved during testing.

In order to study the effect of aging on workability, the alloys were solution treated (470-500°C) and aged to four different levels: naturally aged, peak-aged, over-aged, and highly over-aged. Solution treatments were carried out in a tube furnace in argon for the 2014 alloy, and in nitrogen for the 2024 and 7075 alloys. This was followed by quenching in an ice-water mixture.

Tests for the naturally aged condition were carried out after aging the specimens at room temperature (25°C) for one week. An oil bath was used for artificial aging. No recrystallization was detected after solution or aging treatments.

The 2024 aluminum alloy shows greater workability than the 2014 and 7075 alloys in all conditions. While the workability index in the 7075 alloy is improved ≈50 percent by over-aging, improvement in workability levels in the 2000 series is more pronounced. In these alloys, the workability index in the highly over-aged condition is approximately three times that of the naturally aged condition.

Upset test specimens of the 7075 alloy revealed exclusively 45-deg cracks in all conditions. The 2014 aluminum alloy specimens also showed 45-deg cracks, except in the highly overaged condition, where cracks in ≈20 percent of the specimens were vertical (also known as normal). These vertical cracks were randomly located on the fracture line.

In the 2024 alloy, both vertical and 45-deg cracks were observed in all conditions; in general, specimens with low aspect ratios tested under high friction conditions gave vertical cracks. The percentage of specimens containing vertical cracks increased with increased aging time. In the naturally aged condition, only ≈15 percent of the specimens had vertical cracks. This type of crack was seen in ≈20 percent in peak-hardness specimens and ≈50 percent of those in the over-aged conditions. In the highly over-aged condition, though, ≈90 percent of the specimens exhibited vertical cracks. It is clear that 45-deg cracking is the predominant fracture mode at low workability levels in this alloy.

The 45-deg cracks did not penetrate the cross-section of the specimens in the 2000 series alloys. Cracks in the 7075 alloy, however, generally traversed the cross-section of the specimen; there was no indication that cracking started in the center of the specimens.

In the three alloys, the poorest bulk workability was obtained in the naturally aged and peak-aged conditions, where the precipitated particles were small and sharable. Localization of shear in these conditions in heat-treatable aluminum alloys is well documented. Localization of shear and accompanying voiding in the 7000 series aluminum alloys has been studied and co-workers and Leroy and Embury.

Chung and co-workers observed the occurrence of localized shear failure in 7075-T4 aluminum alloy before the onset of necking and concluded that either deformation softening or negative strain-rate sensitivity was necessary for localization to occur. The degree of localization in overaged conditions, however, should be lower than that in the naturally aged condition, as evidenced by the small improvement in the workability level.

Results of tension and compression tests on 2014 alloy indicate that lack of shear localization in tension is not a guarantee that this phenomenon will be prevented in compression. In the compression of overaged specimens of this alloy, only 45-deg cracks are observed, and the persistence of localized shear failure is probable. It appears that the 2024 alloy is least affected by shear localization among the three alloys, as evidenced by the high degree of workability and occurrence of vertical cracks in all conditions.

Work hardening is used extensively to produce strain-hardened tempers of the non-heat-treatable alloys. The severely cold worked or full-hard condition (H18 temper) is usually obtained with cold work equal to about 75% reduction in area. The H19 temper identifies products with substantially higher strengths and greater reductions in area. The H16, H14, and H12 tempers are obtained with lesser amounts of cold working, and they represent three-quarter-hard, half-hard, and quarter-hard conditions, respectively.

A combination of strain hardening and partial annealing is used to produce the H28, H26, H24, and H22 series of tempers; the products are strain hardened more than is required to achieve the desired properties and then are reduced in strength by partial annealing.

A series of strain-hardened and stabilized tempers – H38, H36, H34, and H32 – are employed for aluminum-magnesium alloys. In the strain-hardened condition, these alloys tend to age soften at room temperature. Therefore, they are usually heated at a low temperature to complete the age-softening process and to provide stable mechanical properties and improved working characteristics.

Products hardened by cold working can be restored to the O temper, a soft, ductile condition, by annealing. Annealing eliminates strain hardening, as well as the changes in structure that are the result of cold working.

The distorted, dislocated structure resulting from cold working of aluminum is less stable than the strain-free, annealed state, to which it tends to revert. In zone-refined aluminum, this reversion may take place at room temperature. Lower-purity aluminum and commercial aluminum alloys undergo these structural changes only with annealing at elevated temperatures. Accompanying the structural reversion are changes in the various properties affected by cold working. These changes occur in several stages, according to temperature or time, and have led to the concept of different annealing mechanisms or processes. The first of these, occurring at the lowest temperatures and shortest times of annealing, is known as the recovery process.

Recovery

Structural changes occurring during the recovery of polygonization and subgrain formation has been obtained by x-ray diffraction and confirmed with the electron microscope. The electron micrographs may show the change in structure that accompanies advanced recovery. The reduction in the number of dislocations is greatest at the center of the grain fragments, producing a subgrain structure with networks or groups of dislocations at the subgrain boundaries. With increasing time and temperature of heating, polygonization becomes more nearly perfect and the subgrain size gradually increases. In this stage, many of the subgrains appear to have boundaries that are free of dislocation tangles and concentrations.

The decrease in dislocation density caused by recovery-type annealing produces a decrease in strength and other property changes. The effects on the tensile properties of 1100 alloy are shown in Fig. 1. At temperatures through 450°F (230°C), softening is by a recovery mechanism. It is characterized by an initial rapid decrease in strength and a slow, asymptotic approach to a strength that is lower, the higher the temperature.

Fig. 1. Isothermal annealing curves for 1100-H18 sheet.Recovery annealing is also accompanied by changes in other properties of cold worked aluminum. Generally, some property change can be detected at temperatures as low as 200 to 250°F (90°C to 120°C); the change increases in magnitude with increasing temperature. Complete recovery from the effects of cold working is obtained only with recrystallization.

Recrystallization

Recrystallization is characterized by the gradual formation and appearance of a microscopically resolvable grain structure. The new structure is largely strain-free. There are few if any dislocations within the grains and no concentrations at the grain boundaries. Recrystallization occurs with longer times or higher heating temperatures than do the recovery effects described in the preceding section, although some overlapping of the two processes is usual.

Recrystallization depends upon time and temperature. This relationship can be expressed by a rate equation of the type:

1/t = ke^-a/T

where t is time, T is the absolute temperature, e is the base of natural logarithms, and k and a are constants.

The constant a is frequently replaced by Q/R, where R is the gas constant and Q is an energy term, similar to an activation energy. Aluminum alloys generally show good agreement with this time-temperature relationship except when secondary reactions interfere, such as the solution or precipitation of intermetallic phases at annealing temperatures.

Composition also influences the recrystallization process. This is particularly true when various elements are added to extreme purity aluminum; almost any added impurity or alloying element will raise the recrystallization temperature substantially. For commercial-purity aluminum and commercial alloys, however, normal variations in composition have little effect on recrystallization behavior. Extensively cold worked commercial alloys usually can be recrystallized by heating for several hours at 650 to 775°F (340 to 410°C).

Grain size is also strongly affected by composition. Generally, common alloying elements and impurities such as Cu, Fe, Mg, and Mn decrease grain size. The effects of elements of limited solubility, such as Cr, Fe, and Mn, are influenced by the compounds they form with each other and with other elements, and by their distribution in the structure.

The recovery process is not accompanied by any significant change in preferred orientation or texture of the deformed metal. However, the new grains formed by recrystallization frequently develop in orientations that differ from the principal components of the deformation texture. This re-orientation has been extensively studied in rolled sheet and varies considerably with the past history and the composition of the alloy.

Recrystallization produces further changes in the properties of the deformed and recovered metal. These continue until annealing and recrystallization are complete. The properties then are those of the original, unstrained metal, except as they are changed by differences in grain size and preferred orientation. In heat treatable alloys, annealing also may be accompanied by precipitation and changes in solute concentration.

Recrystallization is also accompanied by a further decrease in stored energy, as measured calorimetrically, as well as by complete elimination of residual stresses.

Grain Growth After Recrystallization

Heating after recrystallization may produce grain coarsening. This can take one of several forms. The grain size may increase by a gradual and uniform coarsening of the microstructure. This is usually identified as “normal” grain growth.

It proceeds by the gradual elimination of small grains with unfavorable shapes or orientations relative to their immediate neighbors. This occurs readily in high-purity aluminum and its solid solution alloys, and can lead to relatively large, average grain sizes. Such grain growth is promoted by small recrystallized grains, high temperatures, and extensive heating. Some grain coarsening of this type also occurs in commercial aluminum alloys, but it is greatly restricted by finely divided impurity phases and by intermetallic compounds of elements, such as manganese and chromium that slows down the process pin the grain boundaries, and prevent further movement. Generally, these grains grow only at very high temperatures and may attain diameters of several inches.

Apparently, the normal growth-inhibiting effects of elements such as iron, manganese, and chromium are lost or modified at high temperatures, through solution or through changes in particle size and shape. Because of the high temperatures, the few grains that first lose or overcome these restraints grow rapidly and consume other potential growth centers, and in this manner, a few grains of very large size are formed.

In most alloys, high temperatures alone are not the only cause for “giant grains”: A small primary grain size and well-developed annealing texture are other factors that promote this form of grain growth.