Patent Grant
7615125
This application claims priority from French application No. 04 10138, filed Sep. 24, 2004, the content of which is incorporated herein by reference in its entirety.
1. Field of the Invention
The present invention relates generally to a process for fabrication of rolled aluminium alloy products with high toughness and high fatigue resistance, and products made using such a process. In particular, the instant process comprises refining liquid metal as well as providing sheets or light-gauge plates that may, for example, be used in aircraft fuselage skins and related applications.
2. Description of Related Art
It is generally known that the various properties required during the manufacture of semi-finished products and structural elements for aircraft construction typically cannot all be optimized at the same time independently of each other. When the chemical composition of the alloy or parameters of product production processes are modified, several critical properties may even change in conflicting trends. This is the case particularly for properties included under the term “static mechanical properties” (particularly the ultimate strength Rm and the yield stress Rp0.2) on the one hand, and properties included under the term “damage tolerance” (particularly toughness and resistance to fatigue crack propagation) on the other hand. Furthermore, some working properties such as fatigue resistance, resistance to corrosion, formability and elongation at failure are linked to the static mechanical properties in a complex and frequently unpredictable manner. Therefore, optimization of all the properties of a material for mechanical construction, for example in the aeronautical sector, frequently depends on a compromise between several key parameters.
For example, Al—Si—Mg—Cu type alloys can be used for structural elements of fuselages for wide body civil aircraft. First, these elements generally should have high mechanical strength, and secondly, possess high toughness and high fatigue resistance. Any new possibility of improving one of these groups of properties without degrading the others would be desirable.
Up to now, efforts made have focused on optimizing the chemical composition of alloys, and optimizing sheets or plate transformation conditions; in other words optimizing rolling and heat treatment sequences.
It was well known that reducing iron and silicon impurities in alloys in the 2xxx and 7xxx series increases the toughness (see J. T. Staley “Microstructure and Toughness of High-Strength Aluminium Alloys” published in the book “Properties Related to Fracture Toughness”, ASTM Special Technical Publication 65, 1976, pp 71-103). In some cases, the reduction of Fe and Si also tends to increase fatigue resistance.
There are few studies related to the influence of conditions for refining of liquid metal and casting of as-cast forms (such as billets and ingots) on the toughness of ingots obtained from such as-cast forms.
EP 1 205 567 A (Alcoa Inc.) teaches that the addition of 0.003 to 0.010% of Ti and Boron or Carbon to a wrought alloy will result in cast grain sizes of 200 μm or less.
U.S. 2002/0011289 A1 (Pechiney Rhenalu) teaches that for thick products with only a slightly recrystallized microstructure (in other words in which the fraction of recrystallized grains is less than 35%), a high as-cast grain size could lead to a specific microstructure of the transformed and heat-treated product that has a beneficial effect on toughness. This result is obtained particularly by careful control of the titanium and boron content, these elements being added in the form of TiB2 to refine the metal grain during solidification.
U.S. Pat. No. 5,104,616 (Baeckerud) particularly addresses problems that arise due to hard boride particles in the beverage can and thin aluminium sheet industries and teaches that it may be advantageous to replace a refining agent containing boron with a refining agent containing carbon. However, problems that arise in the aluminium packaging industry such as pin-holes, are incomparable with problems that arise in the aeronautical industry, where product strength and durability are of the utmost importance.
A purpose of the present invention was the provision of a new process for producing highly recrystallized wrought products, preferably rolled products, and particularly sheets or light-gauge plates made of an alloy in the 6xxx series with high mechanical strength that also have excellent toughness and fatigue resistance.
An object of the instant invention was the provision of a process for manufacturing aluminium alloy products, and particularly highly recrystallized products with high toughness and fatigue resistance comprising:
Another object of the present invention was providing a rolling ingot that can be obtained by a casting process of the present invention.
Yet another object of the present invention was directed a sheet or light gauge plate that can be obtained using a process and/or using a rolling ingot according to the invention.
Further included as part of the present invention are methods of preparation and usage of systems and treatments according to the present invention.
Additional objects, features and advantages of the invention will be set forth in the description which follows, and in part, will be obvious from the description, or may be learned by practice of the invention. The objects, features and advantages of the invention may be realized and obtained by means of the instrumentalities and combination particularly pointed out in the appended claims.
Unless otherwise indicated, all the indications relating to the chemical composition of the alloys are expressed as a mass percentage by weight based on the total weight of the alloy. When the concentration is expressed in ppm (parts per million), this indication also refers to a concentration by mass.
Alloy designations used herein are in accordance with the regulations of The Aluminium Association, known of to those skilled in the art. The tempers are laid down in European standard EN 515. The chemical composition of normalized aluminium alloys is defined, for example, in standard EN 573-3 and in THE ALUMINUM ASSOCIATION publications. These rules, standards and publications are known to those of skill in the art. For the purposes of this description, “alloy in the 6xxx series” or “Al—Mg—Si type alloy” means aluminium alloys (i) for which the chemical composition satisfies one of the standard designations of an alloy in the 6xxx series, or (ii) is derived from an alloy satisfying such a standard designation by adding or removing one or several chemical elements other than silicon or magnesium, and/or by the concentration of one or several chemical elements (including silicon and magnesium) being above or below the standard concentration range for 6xxx, wherein it is understood that in both cases (i) and (ii), application of the standard designation rules would be such that this modified alloy would be classified in the 6xxx series.
Unless otherwise indicated, the static mechanical characteristics, in other words the ultimate tensile strength (UTS, also designated as Rm), the tensile yield strength (YS, also designated as TYS or Rp0.2), the elongation at fracture A and the elongation at necking Ag, of the metal sheets or plates are determined by a tensile test according to standard EN 10002-1, wherein the location and the direction of the test pieces taken are defined in standard EN 485-1. Fatigue resistance is determined by a test defined in standard ASTM E 466, fatigue crack propagation rate (called the da/dn test) by a test according to ASTM R 647, and critical stress intensity factor KC, KCO or Kapp according to ASTM E 561. The term “extruded product” includes “drawn” products, in other words, products produced by extrusion followed by drawing.
Unless mentioned otherwise, definitions in European standard EN 12258-1 apply.
By “sheet or light-gauge plate” as used herein means a rolled product not exceeding about 12 mm in thickness.
For the purposes of this description, a “structure element” or “structural element” of a mechanical construction means a mechanical part that, if it fails, could endanger the safety of the construction, its users, passengers, and/or others. For an aircraft, these structure elements include particularly, for example, elements making up the fuselage (such as the fuselage skin, stiffeners or stringers, bulkheads, circumferential frames, wings (such as the wing skin), stringers or stiffeners, ribs and spars, and the tail fin composed essentially of the horizontal and vertical stabilizers, and the floor beam, seat tracks and doors.
The present invention may be applicable to any wrought alloys such as those in the 1xxx, 2xxx, 3xxx, 4xxx, 5xxx, 6xxx, 7xxx and 8xxx series, and particularly alloys in the 2xxx, 6xxx and 7xxx series, and more particularly alloys in the 6xxx series. The instant invention is based on one hand, on the discovery that refining of an aluminium alloy using a refining agent containing the right proportion of AlTiC type phases can give a very particular microstructure of the as-cast product, and particularly a grain size larger than about 500 μm and a uniform distribution of intermetallic phases, observed by an optical microscope typically with a magnification of about 50. After hot transformation using known processes, the present invention provides wrought products that surprisingly have a significantly improved toughness and a lower crack propagation rate than is the case for products produced from as-cast forms using known processes, particularly for strongly recrystallized products. A strongly recrystallized product is a product for which the fraction of recrystallized grains measured between one-quarter thickness and mid-thickness of the final wrought product is higher than about 70% by volume. In one advantageous embodiment of the present invention, products output from the solution heat treatment are strongly recrystallized. It is generally known that for slightly recrystallized products, the as-cast microstructure can have an effect on the properties of the transformed product (for example hot rolled, cold rolled and heat treated), but in this case the mechanism of this surprising phenomenon has not yet been elucidated in terms of structural metallurgy. A product produced by a process according to the instant invention is generally different from products according to the state of the art, for example by virtue of the presence of AlTiC type phases. “AlTiC type phases” means any Al—Ti—C ternary phase and any Ti—C binary phase in an aluminium matrix; this term includes the AlTiC2 and TiC phases in particular. These phases are typically added in a refining agent wire. Despite the small quantity of these phases, their effect on the cast microstructure is very clearly defined. Since refining using a wire containing AlTiC type phases can be substituted for refining with wire containing boron (such as AT5B) as is frequently used, an as-cast form produced by the instant process according to the invention can in some cases, and advantageously can contain less than about 0.0001% of boron.
An as-cast microstructure obtained by the process according to the invention is advantageously characterized by two parameters, p* (dimension [μm], and s* (dimension [μm−1]). In particular, these parameters generally characterize the fineness and uniformity of micro-segregation. The parameter p* characterizes the average distance between precipitates in solidification structures, and therefore the average dimension of zones with no precipitates. The s* parameter characterizes the uniformity of the distribution of these distances. A precise definition of these two parameters and the method of determining them are given in the article entitled “Quantification of Spatial Distribution of as-cast Microstructural Features” by Ph. Jarry, M. Boehm and S. Antoine, published in Proceedings of the Light Metals 2001 Conference, Ed. J. L. Anjier, TMS, pp 903-909, the content of which is incorporated herein by reference in its entirety. The p* parameter is determined by an interlaboratory test performed in the context of the European VIRCAST project, see the article by Ph. Jarry and A. Johansen “Characterisation by the p* method of eutectic aggregates spatial distribution in 5xxx and 3xxx aluminium alloys cast in wedge moulds and comparison with SDAS measurements”, published in Solidification of Alloys, ed. M. G. Chu, D. A. Granger and Q. Han, TMS 2004, incorporated herein by reference in its entirety.
The p* and s* parameters are based on an analysis by optical microscopy of polished sections of the as-cast form typically at a magnification of 50, or any other magnification that gives a good compromise between representative sampling of the studied microstructure and the necessary resolution. Images are typically acquired using a CCD (charge-coupled device) type color camera connected to an image analysis computer. The analysis procedure, described in detail in the above-mentioned article by Ph. Jarry, M. Boehm and S. Antoine, incorporated herein by reference in its entirety, comprises the following steps:
The digital analysis of the image advantageously includes the iterative closing of the image with an increasing pitch. The step i that closes the image Ci is defined by i successive expansions of the image of the same object (one expansion consisting of replacing each pixel in an image by the maximum value of all its neighbours) followed by i successive erosions of the image of the same object (an erosion consisting of replacing each pixel in an image by the minimum value of all its neighbours) in the image d (note that the erosion and expansion operations cannot be inverted). The surface ratio A, that represents the fraction of the surface area of each object, is plotted as a function of the number of closing pitches i. A sigmoid curve is obtained that is then adjusted by a sigmoid function so as to extract the characteristic parameters p* and s*, knowing that p* is the abscissa of the inflection point, expressed in length units, and s* is the slope of the sigmoid curve at the inflection point.
The parameter p* is thus defined by the equation:
The parameter p* represents the average distance between particles present in the matrix.
The other parameter s* is defined by the equation:
It has been shown that 1/s* is proportional to the standard deviation of the distribution of distances to the first neighbouring particle. Therefore the s* parameter is a measure of the regularity of the distribution of phases in the matrix.
Therefore the description of the as-cast structure using the s* and p* parameters accounts for the fineness and the uniformity of micro-segregation. The applicant has observed that s* can be more significant in some cases for describing the uniformity of the particle distribution, while p* can be more significant for describing the fineness of their spatial distribution. In one preferred embodiment of the invention, a rolling ingot is prepared using a process according to the invention, so as to obtain a value of s* at least about 0.92 μm−1, and preferably greater than 0.94 μm−1. The corresponding value of p* obtained is preferably at most about 107 μm.
According to the present invention, the as-cast form obtained after casting, such as an extrusion ingot, a forging ingot or a rolling ingot, is hot transformed, or optionally cold transformed, to its final thickness. The product at its final thickness can then be subjected to a solution heat treatment and a quenching treatment, followed by relaxation by controlled stretching with a permanent elongation of from about 0.5 to about 5%, optionally followed by annealing. If the permanent elongation obtained during relaxation by controlled stretching is less than about 0.5%, the product may not become sufficiently plane enough in some cases. If the permanent elongation obtained during relaxation by controlled stretching is more than about 5%, the tolerance to damage properties may be affected in some embodiments.
A process according to the instant invention is particularly suitable in some embodiments for producing wrought products made of an alloy in the 6xxx series, and particularly AA6056, AA6156 or similar alloys. It is preferred to limit the iron content to about 0.15% for these two alloys, and even to about 0.13%, to reduce the tendency towards micro-segregation during casting. One advantageous embodiment for heat-treatable alloys includes transformation of the rolling ingot by hot rolling of a sheet or light-gauge plate between 3 and 12 mm, and heat treatment to obtain the T6 temper. If this process is used for the AA6056 or AA6156 alloys, a sheet or light-gauge plate is obtained with damage tolerance KR, determined in the T-L direction for a crack length of Δaeff, equal to 20 mm using an R curve measured according to ASTM E561 equal to at least 115 MPa√m, and preferably at least 116 MPa√m.
The said rolling ingot could also be cladded on one or both sides using known operating methods after scalping or possibly after a first hot rolling sequence; for example, this could be advantageous with AA2024, AA6056 and AA6156 alloys.
A sheet or light-gauge plate made from an AA6056 or AA6156 alloy between 3 and 12 mm thick in the T6 temper manufactured by the process according to the invention in one embodiment has a tolerance to damage KR determined in the T-L direction for a crack extension Δaeff equal to 60 mm, obtained from an R curve measured according to ASTM E561, equal to at least 175 MPa√m.
Moreover, its crack propagation rate da/dn in the T-L direction, measured according to ASTM E 561 on a panel with width w=400 for Δk=50 MPa√m and R=0.1, advantageously is less than 2×10−2 mm/cycle.
In industrial practice, the improvement of the KR parameter achieved using the process according to this invention, tends to improve the minimum guaranteed value of this parameter for a given constraint, knowing that like all parameters that characterize a metallurgical product, the KR parameter can be subject to a certain amount of statistical dispersion.
The following examples contain a description of advantageous embodiments of the invention. These examples are not limitative.
An AA6056 alloy was cast in two industrial sized rolling ingots with a thickness of 446 mm, at a rate of 55 mm/minute and at a temperature of 680° C. The chemical composition comprised (in % by weight):
Table 1 shows the refining method (AlT3C0.15 or AT5B wire). The name AlT3C0.15 denotes a composition Al-3% Ti-0.15% C. The name AT5B denotes a composition Al-5% Ti-1% B; this product is also known under the tradename “AlTiB 5:1”), the Ti content (in ppm by mass), the inoculation ratio and the average values for the s* and p* parameters are as defined above. The s* and p* parameters were determined on sections cut at about 140 mm from the skin and at one third of the width of rolling ingots.
These rolling ingots were used to manufacture clad sheets with a final thickness of 5 mm in the T6 temper using the same transformation procedure comprising homogenisation, hot rolling, solution heat treatment, quenching, relaxation by controlled stretching, and annealing. The permanent elongation obtained during relaxation by controlled stretching was 1.5%. The fraction of recrystallized grains measured between the quarter thickness and the mid-thickness of the finished products was approximately 100%.
The static mechanical characteristics and the damage tolerance properties of these sheets were determined. The results are given in Table 2. The parameter KR(20) relates to a crack extension value Δaeff equal to 20 mm.
The crack propagation rate da/dn was also determined according to ASTM E 647 for a sheet with a width w=400 mm in the T-L direction, and a ratio R=0.1.
It can be seen that the static mechanical characteristics of the two sheets are not significantly different. On the other hand, the resistance to damage, represented by the KR parameter, increases significantly when the liquid metal is refined with a wire containing AlTiC type phases. The crack propagation rate for the latter product is lower when the stress intensity factor is about 30 MPa√m.
Other rolling ingots made of the AA6056 alloy were cast using the process according to the invention. The refining parameters and the casting microstructure are summarised in table 3.
Table 4 summarizes the total Ti content in the alloys in examples 1 and 2, and the size of as-cast grains.
The Ti and C content added by the refining wire may be calculated from the inoculation ratios and the wire composition.
Classical refining at 0.7 kg/t of ATB5 introduces about 7 ppm of B. Refining with 1 kg/t of wire type AT3C0.15 as used for these tests introduces about 1.5 ppm of C. Refining of 0.5 kg/t of the same wire introduces about half this amount of C, namely about 0.75 ppm, while refining of 2 kg/t introduces about twice as much, namely about 3 ppm. For titanium, refining of 1 kg/t of AT3C0.15 introduces about 30 ppm, refining of 0.5 kg/t adds half this amount (about 15 ppm) and refining of 2 kg/t adds twice this amount (about 60 ppm).
Additional advantages, features and modifications will readily occur to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details, and representative devices, shown and described herein. Accordingly, various modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
All documents referred to herein are specifically incorporated herein by reference in their entireties.
As used herein and in the following claims, articles such as “the”, “a” and “an” can connote the singular or plural.
| Number | Date | Country | Kind |
|---|---|---|---|
| 04 10138 | Sep 2004 | FR | national |
| Number | Name | Date | Kind |
|---|---|---|---|
| 4748001 | Banerji | May 1988 | A |
| 5104616 | Baeckerud | Apr 1992 | A |
| 5186236 | Gabathuler et al. | Feb 1993 | A |
| 5480498 | Beaudoin | Jan 1996 | A |
| 6077363 | Heymes et al. | Jun 2000 | A |
| 6216521 | Heymes et al. | Apr 2001 | B1 |
| 6645321 | Sigworth | Nov 2003 | B2 |
| 20020011289 | Warner | Jan 2002 | A1 |
| 20020031682 | Dif et al. | Mar 2002 | A1 |
| Number | Date | Country |
|---|---|---|
| 0493318 | Jul 1992 | EP |
| 1158068 | Nov 2001 | EP |
| 1158068 | Nov 2001 | EP |
| 1205567 | May 2002 | EP |
| 2216542 | Oct 1989 | GB |
| 2243374 | Oct 1991 | GB |
| 60145365 | Dec 1985 | JP |
| 04292449 | Nov 1995 | JP |
| 701000 | Mar 1996 | RU |
| Number | Date | Country | |
|---|---|---|---|
| 20060065331 A1 | Mar 2006 | US |
