Dispersion strengthened aluminum alloys

Abstract: The embrittling tendency of lithium in aluminum-­ base alloy compositions containing lithium is decreased by incorporating silicon in the alloy composition and forming the alloy as a dispersion strengthened powder. Dispersion strengthened aluminum-base alloy compositions comprising aluminum, lithium, silicon, carbon and oxygen are disclosed.

Description: The present invention relates to a dispersion strengthened alloy system comprising aluminum, lithium and silicon and to a method of producing forged aluminum alloys of this system having improved mechanical properties. In recent years there has been an intensive search for high strength aluminum which would satisfy the demands of advanced design in aircraft, automotive, naval and electrical industries. The requirements for such alloys are explained in detail in EP-A-0 180 144. In particular they require a combination of high strength with ductility, low density, toughness and resistance to fatigue and corrosion, depending on the ultimate end use. The ultimate product forms are often complex shapes, and it is desirable to be able to shape the alloys into such forms readily and economically: thus it is an advantage to be able to make a complex shape by forging rather than by a route which requires individual shaping by machining. In designing low density aluminum alloys, preferred additives are magnesium and lithium. These elements not only lower the density but also increase the strength of the aluminum. Lithium also increases the elastic modulus of aluminum. These highly useful effects are the basis for current interest in developing alloys of this type. However, efforts to develop high strength alloys of this type have been severely hampered by the propensity for these alloys to display relatively low tensile strength and low fracture toughness. In our application EP-A-0 180 144 we have disclosed dispersion strengthened aluminum-magnesium-lithium alloys which are made by mechanical alloying, extruded and forged to shape. The essential constituents of the matrix of these alloys are aluminium, magnesium end lithium, and the dispersion strengthening agents comprise carbides, oxides and/or silicides. Thus the alloys may also contain silicon. In numerical terms the alloys comprise, by weight, from about 0.5 to 7% magnesium, from about 0.5 to 4% lithium, from 0 to 4% silicon, a small but effective amount for increased strength up to about 5% carbon, a small but effective amount for increased stability and strength, up to about 1%, oxygen, the balance being essentially aluminium, The alloys include a small but effective amount, up to about 10% by volume, of dispersoid. Unless otherwise specified, all percentages of constituentsin this description and claims are by weight. These alloys have useful properties and the processing route disclosed gives the possibility of using a wide range of conditions under which the materials can be forged and affords improved reproducibility of the forged parts. While the alloys disclosed have highly desirable properties, they nevertheless have limitations. For example, lithium additions are far more effective in lowering the density of aluminum than any other element. Each percent of lithium added reduces density by about 3%. The maximum solubility of lithium in aluminum is about 4% at elevated temperatures, but drops to about 1.3% (wt. %) at room temperature. (Sanders & Starke, Aluminum-Lithium Alloys, AIME proceedings, May 19-21, 1980). In view of the benefits of lithium addition, it is desirable to add as much lithium as possible However, if lithium is increased above the solubility limit the alloys become age hardenable and susceptible to embrittlement in service. The present invention is based on the discovery that when silicon is incorporated into dispersion-strengthened aluminum-base alloys containing lithium but free from magnesium the age-hardening and embrittling tendency of lithium in these alloys is decreased. Thus when silicon is co-present, the amount of lithium that can be added without sacrifice of ductility is increased, thus enabling alloys to be obtained having decreased density and good ductility. This surprising effect opens the door to the possibility of strengthening the alloy system by addition of heavier elements such as copper, cobalt, zinc, manganese, nickel, iron, chromium, titanium, niobium, zirconium, vanadium and rare earth metals, e.g. cerium. According to the invention, a dispersion-strengthened aluminum-lithium-silicon alloy comprises, by weight, lithium in an amount of at least 0.5% and above the solubility limit of lithium in the alloy at room temperature, but not exceeding 4%, silicon from 0.2 to 4%, carbon from 0.05 to 5%, and oxygen from 0.05 to 1%, with or without one or more of the following elements up to the maximum amounts indicated, but preferably not exceeding 20% in total: cobalt up to 6%, copper up to 6%, zinc up to 7%, manganese up to 2%, chromium up to 6%, nickel up to 6%, iron up to 8%, titanium up to 6%, niobium up to 6%, zirconium up to 6%, vanadium up to 6%, rare earth metal up to 5%; the balance, apart from impurities, being aluminum. Advantageously, the lithium range is from 1 up to 3%, and preferably from 1.5 or 1.6 up to 2.5%. The lithium is introduced into the alloy system as a powder (elemental or preferably prealloyed with aluminum) thereby avoiding problems which accompany the melting of lithium in ingot metallurgy methods. Compounds of carbon, oxygen and silicon are present as a small weight percentage of the alloy system as insoluble dispersoids such as oxides and/or carbides and/or silicides. Other elements may be incorporated in the alloy so long as they do not interfere with the desired properties of the alloy for a particular end use. Also, a minor amount of impurities may be picked up from the charge materials or in preparing the alloy. Additional insoluble, stable dispersoids or dispersoid forming agents may be incorporated in the system, e.g. for strengthening the alloy at elevated temperatures, so long as they do not otherwise adversely affect the alloy. The silicon content of the alloys is advantageously from 0.2 up to 2%. Preferably it is from 0.5 to 1.5%, and typically it is from 0.5 to 1%. Carbon is present in the system for increased strength. Typically the level of carbon to give increased strength ranges from 0.05 up to 2%, advantageously from 0.2 up to 1% or 1.5%. and preferably 0.5 up to 1.2%. During the formation of mechanically alloyed powders the carbon is generally provided by a process control agent. Preferred process control agents are methanol, stearic acid and graphite. In general the carbon present will form carbides, e.g. with one or more of the components of the system. Oxygen in amounts from 0.05% up to 1% contributes to increased strength and stability. Preferably it does not exceed 0.4 or 0.5%. The low oxygen content is believed to be critical. When the oxygen content is above 1% the alloy is found to have poor ductility. In alloys containing above 1.5% Li, the oxygen content preferably does not exceed about 0.5%. The dispersoid content of the alloys comprises oxides, carbides and silicides. The dispersoid content attributable to carbides and oxides is in a range of a small but effective amount for increased strength up to about 25 volume % (vol. %) calculated on the basis of carbides as Al₄C₃ and oxides as Al₂O₃. Advantageously it is less than 10 vol. %, and preferably is less than about 8 vol. %. Preferably the dispersoid level is as low as possible consistent with desired strength. Typically the dispersoid level is 1.5 to 7 vol. %, and preferably it is 2 to 6 vol. %. Other dispersoids may be present, for example, compounds or intermetallics of aluminum, lithium, silicon or combinations thereof. Carbide and silicide dispersoids can be formed during mechanical alloying and/or later during consolidation or thermomechanical processing and/or they may be added as such to the powder charge. Other dispersoids may be added or formed in situ. Beneficial dispersoids from the standpoint of strength and stability of the matrix system are stable in the aluminum alloy matrix at the ultimate temperature of service. Examples of oxide and carbide dispersoids that may be present are Al₂O₃, AlOOH, Li₂Al₂O₄, LiAlO₂, LiAl₅O₈, Li₅AlO₄, Al₄C₃. Other dispersoids may also be present depending on the alloy system, e.g. Al₂Cu, Al₂CuLi. The dispersion strengthened alloys are formed as powder, for example by mechanical alloying, by addition of dispersion forming elements in atomised powders or by a combination thereof. In a preferred embodiment the powdered alloys are converted to forged articles. In a preferred embodiment of the present invention a forged article composed of an alloy of this invention is prepared from a mechanically alloyed powder by a sequence of steps comprising: degassing and compacting the powder to obtain a compacted body of about substantially full density, e.g. by vacuum hot pressing; extrusion and forging. In one aspect of the invention the Al-Li alloys have a density of less than about 2.8 g/cc, e.g. about 2.3 to about 2.6 g/cc. Alloy Preparation Prior to Fabrication of End Use Product As indicated above the alloy is prepared as a dispersion strengthened powder, but is not limited in how the powder is prepared. Preferable routes are by mechanical alloying and/or atomization technique. The description below is given mainly with reference to formation of the powder by a mechanical alloying route. The use of powder metallurgy routes to produce high strength aluminum has been proposed and has been the subject of considerable research. Powder metallurgy techniques generally offer a way to produce homogenous materials, to control chemical composition and to incorporate dispersion strengthening particles into the alloy. Also, difficult-to-handle alloying elements can at times be more easily introduced by powder metallurgy than ingot melt techniques. The preparation of dispersion strengthened powders having improved properties by a powder metallurgy technique known as mechanical alloying has been disclosed, e.g., in U.S. Patent No. 3,591,362. Mechanically alloyed materials are characterized by fine grain structure which is stabilized by uniformly distributed dispersoid particles such as oxides and/or carbides. U.S. Patents Nos. 3,740,210, 3,816,080 pertain particularly to the preparation of mechanically alloyed dispersion strengthened aluminum. Other aspects of mechanically alloyed aluminum-base alloys have been disclosed in U.S. Patents Nos. 4,292,079, 4,297,136, 4,409,038, 4,532,106, 4,557,893 and 4,600,556. (1) Mechanical Alloying to Form Powders The mechanical alloying technique is a solid-state milling process, which is described in the aforementioned patents. Briefly, aluminum powder is prepared by subjecting a powder charge to dry, milling in the presence of a grinding media, e.g. balls, and a process control agent, under conditions sufficient to comminute the powder particles to the charge, and through a combination of comminution and welding actions caused repeatedly by the milling, to create new, dense composite particles containing fragments of the initial powder materials intimately associated and uniformly interdispersed. Milling is done in a protective atmosphere, e.g. under an argon blanket, thereby facilitating oxygen control since when carried out in this way virtually the only sources of oxygen are the starting powders and the process control agent. However, controlled amounts of oxygen can be admitted into the mill as a further source of oxygen if desired. The process control agent is a weld-controlling amount of a carbon-contributing agent and may be, for example, graphite or a volatilizable oxygen-containing hydrocarbon such as organic acids, alcohols, aldehydes and ethers. The formation of dispersion strengthened mechanically alloyed aluminum is given in detail in U.S. Patents No. 3,740,210 and 3,816,080, mentioned above. Suitably the powder is prepared in an attritor using a ball-to-powder weight ratio of 15:1 to 60:1. As indicated above, preferably process control agents are methanol, stearic acid, and graphite. Carbon from these organic compounds and/or graphite is incorporated in the powder and contributes to the dispersoid content. (2) Degassing and Compaction Before the dispersion strengthened mechanically alloyed powder is fabricated it must be degassed and compacted. Degassing and compacting are effected under vacuum and generally carried out at a temperature in the range of about 480°C (895°F) up to just below incipient liquefication of the alloy. The degassing temperature should be higher than any subsequently experienced by the alloy. Degassing is preferably carried out, for example, at a temperature in the range of from about 480°C (900°F) up to 545°C (1015°F) and more preferably above 500°C (930°F). Pressing is carried out at a temperature in the range of about 545°C (1015°F) to about 480°C (895°F). In a preferred embodiment the degassing and compaction are carried out by vacuum hot pressing (VHP). However, other techniques may be used. For example, the degassed powder may be upset under vacuum in an extrusion press. To enable the powder to be extruded to substantially full density, compaction should be such that the porosity is isolated, thereby avoiding internal contamination of the billet by the extrusion lubricant. This is achieved by carrying out compaction to at least 85% of full density, advantageously above 95% density, and preferably the material is compacted to over 99% of full density. Preferably the powders are compacted to 99% of full density and higher, that is, to substantially full density. The resultant compaction products formed in the degassing and compaction step or steps are then fabricated in forms appropriate for use. Fabrication Fabrication of the alloy into useful products comprises both consolidation and shaping. Consolidation and shaping to final form may be carried out by conventional fabrication methods, e.g., rolling, swaging, extruding, forging, and combinations thereof, and it will be understood that preparation of the alloy is not limited to any one method of production. However, the present alloys are described below mainly with reference to forging. As explained previously, for certain purposes forging has advantages. (1) Consolidation The purpose of consolidation in the fabrication steps is to insure full density in the alloy. Both achieving full density and breakup of any surface oxide can on the particles be obtained, for example, by extrusion. If the alloys are prepared in the forged condition, as explained in the aforementioned EP-A-0 180 144 the extrusion temperature is advantageously held within a narrow range and the lubrication practice and the conical die-type equipment used for the extrusion are important. For example, in a forged embodiment of the present invention, the extrusion temperature is in the range of above the incipient extrusion temperature up to about 400°C (750°F) said extrusion being carried out with lubrication, preferably through a conical die to provide an extruded billet of substantially full density is chosen so that the maximum temperature achieved in the extruder is no greater than 28°C (50°F) below the solidus temperature. Typically it will be in the range of about 230°C (450°F) and about 400°C (750°F). Advantageously, it should be carried out below about 370°C (700°F), preferably in the range of about 260°C (500°F) to about 300°C (675°F), and more preferably should not exceed about 345°C (650°F) or even should be lower than about 330°C (625°F). The temperature should be high enough so that the alloy can be pushed through the die at a reasonable pressure. Typically this will be above about 230°C (450°F). It has been found that a temperature of about 260°C (500°F) for extrusion is highly advantageous. By carrying out the extrusion at about 260°C (500°F), there is the added advantage of greater flexibility in conditions which may be used during the forging operation. This flexibility decreases at the higher end of the extrusion temperature range. By incipient extrusion temperature is meant the lowest temperature at which a given alloy can be extruded on a given extrusion press at a given extrusion ratio. The extrusion ratio is at least 3:1 and may range, for example, to about 20:1 and higher. The above given extrusion temperature ranges used for Al-Li-Si alloys are those which will maximise the alloy strength, since strength is currently the initial screening test for the forged parts made from the aluminum-base alloys. It will be appreciated that when the strength requirements are not as rigorous the teachings of this invention can be used to trade-off strength against some other property. The extrusion in the present process is preferably carried out in a conical-faced die as opposed to a shear-faced die. By a conical die is meant a die in which the transition from the extrusion liner to the extrusion die is gradual. Advantageously the angle of the head of the die with the liner is less than about 60°, and preferably it is about 45°. Lubrication is applied to the die or the compaction billet or both of them. The lubricants, which aid in the extrusion operation, must be compatible with the alloy compaction billet and the extrusion press, e.g. the liner and die. The lubricant applied to the billet further protects the billet from the lubricant applied to the extrusion press. Properly formulated lubricants for specific metals are well known in the art. Such lubricants take into account, for example, requirements to prevent corrosion and to make duration of contact of the billet with the extrusion press less critical. Examples of lubricants for the billets are kerosene, mineral oil, fat emulsion and mineral oil containing sulfurized fatty oils. Fillers such as chalk, sulfur and graphite may be added. An example of the lubricant for an extrusion press is colloidal graphite carried in oil or water, molybdenum disulfide, boron sulfide, and boron nitride. The extruded billets are then in condition to be forged. If necessary the billets may be machined to remove surface imperfections. (2) Forging In general forged aluminum alloys of the present invention will benefit from forging temperatures being as low as possible consistent with the alloy composition and equipment. Forging may be carried out as a single or multi-step operation. In multi-step forging the temperature control applied to the initial forging or blocking-type step. As in the extrusion step, it is believed that for high strength the aluminum alloys of this invention should be forged at a temperature below one where a decrease in strength will occur. Forging should be carried out below about 400°C (750°F), and preferably less than 370°C (700°F), e.g. in the range of 230°C (450°F) to about 345°C (650°F), typically about 260°C (500°F). Despite the fact that forgeability may increase with temperature, the higher forging temperatures have now been found to have an adverse effect on strength. In a multi-step forging operation it has been found that it is the initial step that is critical. In subsequent forging steps of a multi-step operation after the initial forging step the temperature range for forging may be above that recommended for this process. For maximizing strength forging is carried out at the lower end of the temperature range when the extrusion is carried out at the higher end of the extrusion range. For example, for this alloy system, the forging operation (or in a multi-step forging operation the initial forging step) is carried out at a temperature of about 230°C (450°F) to about 400°C (750°F) when extrusion is carried out at about 260°C, and the forging operation (or initial forging step) is carried out at a narrow range at the lower end of the extrusion temperature range, e.g. at about 260°C (500°F) when extrusion is previously carried out at 370°C (700°F). As noted in the aforementioned EP-A-0 180 144, while it is known in the art that conditions of forging aluminum alloys will vary with composition, it was surprising that the forging conditions - particularly the temperature - at which the alloys could be forged is related to the temperature at which the alloy is consolidated, and in particular extruded. (3) Age hardening As indicated above, with addition of silicon age hardening due to lithium is decreased, which has the beneficial effect of reducing embrittlement due to lithium additions while maintaining good ductility. As a result greater amounts of lithium can be added with attendant advantages of producing lower density alloys. Thus the addition of about 0.5% lithium has the effect of reducing the density of the alloy by about 0.02 - 0.03 g/cc. Silicon has substantially no effect on the density of the alloys. This enables other alloying elements, for example, heavier elements such as Cu, Co, Zn, Mn, Ni, Fe, Cr, Ti, Nb, Zn, V and/or rare earth elements be added to increase strength while maintaining satisfactory ductility and maintaining the density of the alloy in a permissible range. It is a particular advantage of the present invention that low density aluminum alloys can be made with high strength, e.g. an 0.2% offset YS of over 410 MPa (60 ksi) and an elongation greater than 3, in the forged condition without having to resort to precipitation hardening treatments which might result in alloys which have less attractive properties other than strength. However, a heat treatment may be carried out if desired on alloy systems susceptible to age hardening. It is noted that in the discussion above, in conversion from °F to °C the temperatures are rounded off as is the above conversion from ksi to MPa. With respect to conditions for commercial production, it is not practical or realistic to impose or require conditions to the extent possible in a research laboratory. Temperatures may stray, for example, 50°F from the target. Thus, having a wider window for processing conditions adds to the practical value of the process. (4) Examples Examples of Al-Li-Si alloy systems containing additional elements which may be dispersion strengthened according to the invention are given in the Table below. In each case, billets of the alloys may be prepared from dispersion strengthened alloy powder comprising aluminum, lithium, silicon, carbon and oxygen and any additional elements, prepared e.g. by a mechanical alloying technique. Typically such aluminium-base alloys contain, besides carbon and oxygen, 0.5 to 4% lithium, e.g. 1 to 3%; 0.3 to 4% silicon, e.g. 1 to 3%; 0 up to 6% cobalt, e.g. 2 to 4%; 0 up to 6% copper, e.g. 2 to 4%; 0 up to 7% zinc, e.g. 4 to 6%; 0 up to 2% manganese, e.g. 0.5 to 1.5%; 0 up to 6% nickel, e.g. 2 to 4%; 0 up to 8% iron, e.g. 4 to 6%; 0 up to 6% chromium, e.g. 3 to 5%; 0 up to 6% titanium, e.g. 3 to 5%; 0 up to 6% niobium, e.g. 3 to 5%; 0 up to 6% zirconium, e.g. 3 to 5%; 0 up to 6% vanadium, e.g. 3 to 5%; 0 up to 5% rare earth metals, e.g. 2 to 4%.

Claims: A dispersion-strengthened aluminum-lithium-silicon alloy comprising, by weight, lithium in an amount of at least 0.5% and above the solubility limit of lithium in the alloy at room temperature, but not exceeding 4%, silicon from 0.2 to 4%, carbon from 0.05 to 5%, and oxygen from 0.05 to 1%, with or without one or more of the following elements up to the maximum amounts indicated: cobalt up to 6%, copper up to 6%, zinc up to 7%, manganese up to 2%, chromium up to 6%, nickel up to 6%, iron up to 8%, titanium up to 6%, niobium up to 6%, zirconium up to 6%, vanadium up to 6%, rare earth metal up to 5%; the balance, apart from impurities, being aluminum. An alloy according to claim 1 containing lithium, silicon, carbon and oxygen in the amounts set forth, the balance, apart from impurities, being aluminum. An alloy according to claim 1 or claim 2 wherein the silicon content does not exceed 2%. An alloy according to any preceding claim wherein the carbon content does not exceed 2%. An alloy according to any preceding claim wherein the oxygen content does not exceed 0.5% An alloy according to any preceding claim wherein the content of dispersoid does not exceed 10 volume %. An alloy according to claim 6 wherein the content of dispersoid is from 2 to 6 volume %. An alloy according to any preceding claim in the form of mechanically alloyed powder. A method of producing a wrought product from an alloy according to any one of claims 1 to 7 which comprises preparing the alloy as a mechanically alloyed powder and consolidating and shaping the powder by vacuum hot pressing, extrusion and forging.

Inventors: DONACHIE STEPHEN JAMES, GILMAN PAUL SANDFORD, SCHELLENG ROBERT DOUGLAS, DONACHIE, STEPHEN JAMES, GILMAN, PAUL SANDFORD, SCHELLENG, ROBERT DOUGLAS
Applicants: INCO ALLOYS INT, INCO ALLOYS INTERNATIONAL, INC.
Application year: 1987
Main classification: C22C1
IPC codes: C22C1, C22C32, C22C21