LOW TEMPERATURE UNDERAGING OF LITHIUM BEARING ALUMINUM ALLOY

Abstract: The combination of strength and fracture toughness, properties of aluminium-lithium alloys are significantly en­ hanced by underaging the alloys at temperatures ranging from 200°F to 300°F for relatively long periods of time.

Description: LOW TEMPERATURE UNDERAGING OF LITHIUM BEARING ALUMINUM ALLOY Background of the Invention The present invention relates to aluminum alloys, more particularly to aluminum alloys containing lithium as an alloying element, and most particularly to a process for improving the fracture toughness of aluminumlithium alloys without detracting from their strength. It has been estimated that current large commercial transport aircraft may be able to save from 15 to 20 gallons of fuel per year for every pound of weight that can be saved when building the aircraft. Over the projected 20 year life of an airplane, this savings amounts to 300 to 400 gallons of fuel. At current fuel costs, a significant investment to reduce the structural weight of the aircraft can be made to improve overall economic efficiency of the aircraft. The need for improved performance in aircraft of various types can be satisfied by the use of improved engines, improved airframe design, and improved or new structural materials in the aircraft. Improvements in engines and aircraft design have generally pushed the limits of these technologies. However, the development of new and improved structural materials is now receiving increased attention, and is expected to yield further gains in performance. Materials have always played an important role in dictating aircraft structural concepts. In the early part of this century, aircraft structure was composed of wood, primarily spruce, and fabric. Because shortages of spruce developed in the early part of the century, lightweight metal alloys began to be used as aircraft structural materials. At about the same time, improvements in design brought about the development of the all metal cantilevered wing. It was not until the 1930's, however, that the metal skin wing design became standard, and firmly established metals, primarily aluminum alloys, as the major airframe structural material. Since that tirne, aircraft structural materials have remained remarkably consistent with aluminum structural materials being used primarily in the wing, body and empennage, and with steel comprising the material for the landing gear and certain other speciality applications requiring very high strength materials. Several new materials are currently being developed for incorporation into aircraft structure. These include new metallic materials, metal matrix composites and resin matrix composites. It is believed that improved aluminum alloys and carbon fiber composites will dominate aircraft structural materials in the coming decades. While composites will be used in increased percentages as aircraft structural materials1 new lightweight aluminum alloys, and especially aluminum-lithium alloys show great promise for extending the usefulness of aluminum alloys. Heretofore, aluminum-lithium alloys have been used only sparsely in aircraft structure. The relatively low use has been caused by casting difficulties associated with aluminum-lithium alloys and by their relatively low fracture toughness compared to other more conventional aluminum alloys. Aluminum-lithium alloys, however, provide a substantial lowering of the density of aluminum alloys (as well as a relatively high strength to weight ratio), which has been found to be very important in decreasing the overall weight of structural materials used in an aircraft. While substantial strides have been made in improving the aluminum-lithium processing technology, a major challenge is still to obtain a good blend of fracture toughness and high strength with an aluminum-lithium alloy. Summary of the Invention The present invention provides a method for aging aluminumlithium alloys of various composition at relatively low temperatures to develop a high fracture toughness without reducing the strength of the alloy to any significant extent. Simply, after the alloy is formed into an article, solution heat treated and quenched, the alloy is aged at a relatively low temperature for a relatively long time. This process may be generally referred to as low temperature underaging. More specifically, the alloy can be aged at temperatures ranging from 2000 F to 3000 F for a period of time ranging from 1 up to 70 or more hours. This low temperature aging regimen will result in an alloy having a strength level generally equivalent to or only slightly lower than that of peak aged material while maintaining a fracture toughness on the order of 150 to 200 percent greater than that of materials aged at conventional higher temperatures. Brief Description of the Drawings A better understanding of the present invention can be derived by reading the ensuing specification in conjunction with the accompanying drawings wherein: FIGURE 1 is a graph of several specimens of an aluminum-lithium alloy aged at various times and various temperatures described in more detail in conjunction with Example I; and FIGURE 2 is a graph showing the plateau velocity (crack growth rate) versus percent of peak age of various alüminum-lithium alloys at various times and temperatures described in conjunction with Example II herein. Detailed Description of the Invention An aluminum-lithium alloy formulated in accordance with the present invention can contain from about 1.0 to about 3.2 percent lithium. The current data indicates that the benefits of the low temperature aging are most apparent at lithium levels of 2.7 percent and below. All percentages herein are by weight percent based on the total weight of the alloy unless otherwise indicated. Additional alloying agents such as magnesium and copper can also be included in the alloy. The magnesium in the alloy functions to increase strength and slightly decrease density. It also provides solid solution strengthening. The copper adds strength to alloy, but unfortunately also serves to increase density. Grain refiners such as zirconium can also be also be included. Manganese can also be present alone or together with zirconium. The manganese functions to provide an improved combination of strength and fracture toughness. Iron and silicon can each be present in amounts up to 0.3 percent. It is preferred, however, that these elements be present only in trace amounts of less than 0.10 percent. Certain trace elements such as zinc may be present in amounts up to but not to exceed 0.25 percent. Certain other trace elements such as chromium must be held to levels of 0.05 percent or less. If these maximums are exceeded, the desired properties of the aluminum-lithium alloy will tend to deteriorate. The trace elements sodium and hydrogen are also thought to be harmful to the properties (fracture toughness in particular) of aluminum-lithium alloys and should be held to the lowest levels practically attainable, for example on the order of 15 to 30 ppm (0.0015-0.0030 wt. 6) for the sodium and less than 15 ppm (0.0015 wt. %) and preferably less than 1.0 ppm (0.0001 wt. %) for the hydrogen. The balance of the alloy, of course, comprises aluminum. The following table represents the proportions in which the alloying and trace elements may be present. The broadest ranges are acceptable under most circumstances, while the preferred ranges provide a better balance of fracture toughness, strength and corrosion resistance. The most preferred ranges yield alloys that presently provide the best set of overall properties for use in aircraft structure. Element Amount (wt. %) Acceptable Preferred Most Preferred Li 1.0 to 3.2 1.5 to 3.0 1.8 to 2.8 Mg O to 4.5 0 to 4.7 0 to 4.2 Cu 0 to 4.5 0 to 3.7 0 to 3.0 Zr. 0 to 0.2 0.07 to 0.15 0.08 to 0.14 Mn 0 to 1.2 0 to 0.8 0 to 0.6 Fe 0.3 max 0.15 max 0.10 max Si 0.5 max 0.12 max 0.10 max Na 0.0030 max 0.0015 max 0.0015 max H 0.0015 max 0.0005 max 0.0001 max Other trace elements 0.25 max 0.25 max 0.25 max Al Balance Balance Balance An even better mix of properties, especially fracture toughness and strength, can be maintained by holding the magnesium to within the range of 0 to 3.2 wt. % and the copper to 0.5 to 3.0 wt. 6. A most preferred alloy that is especially susceptible to property enhancement in accordance with the techniques of the present invention is an alloy containing 2.2 to 2.8 percent lithium, 0.4 to 0.8 percent magnesium, 1.5 to 2.1 percent copper and up to 0.15 percent zirconium as a grain refiner. The preferred limitations on iron, silicon and other trace elements also applies to this preferred alloy. An aluminum-lithium alloy formulated in the proportions set forth in the foregoing paragraphs is processed into an article utilizing known techniques. The alloy is formulated in molten form and cast into an ingot. The ingot is then homogenized at temperatures ranging from 925 F to 10DOOP. Thereafter, the alloy is converted into a usable article by conventional mechanical formation techniques such as rolling, extrusion or the like. Once an article is formed, the alloy is normally subjected to a solution treatment at temperatures ranging from 9500 F to 10000 F, quenched in a quenching medium such as water that is maintained at a temperature on the order of 70 F to 1500 F. If the alloy has been rolled or extruded, it is generally stretched on the order of 1 to 3 percent of its original length to relieve internal stresses. The aluminum alloy can then be further worked and formed into the various shapes for its final application. Additional heat treatments such as solution heat treatment can be employed if desired. For example, an extruded product after being cut to desired length are generally solution heat treated at temperatures on the order of 9750 F for 1 to 4 hours. The product is then quenched in a quenching medium held at temperatures ranging from about 700 F to 1500F. Thereafter, in accordance with the present invention, the article is subjected to an aging treatment that will increase the strength of the material, while maintaining its fracture toughness and other engineering properties at relatively high levels. In accordance with the present invention, the articles are subjected to a low temperature underage heat treatment at temperatures ranging from about 2000 F to about 3000 F. It is preferred that the alloy be heat treated in the range of from about 2500 F to 2750 F. At the higher temperatures, less time is needed to bring about the proper balance between strength and fracture toughness than at lower aging temperatures, but the overall property mix will be slightly less desirable. For example, when the aging is conducted at temperatures on the order of 2750 F to 3000 F, it is preferred that the product be subjected to the aging temperature for periods of from 1 to 40 hours. On the other hand, when aging is conducted at temperatures on the order of 250"F or below, aging times from 2 to 80 hours or more are preferred to bring about the proper balance between fracture toughness and strength. After the aging treatment, the aluminum-lithium articles are cooled to room temperature. When the low temperature underaging treatment is conducted in accordance with the parameters set forth above, the treatment will result in an aluminum-lithium alloy having an ultimate strength on the order of 65 to 95 ksi, depending on the detail composition of the alloy. The fracture toughness of the material, however, will be on the order of 1 1/2 to 2 times greater than that of similar aluminum-lithium alloys subjected to conventional aging treatments, which are normally conducted at temperatures greater than 300 F. The superior strength and toughness combination achieved by the low temperature underaging techniques in accordance with the present invention also surprisingly causes some aluminum-lithium alloys to exhibit an improvement in stress corrosion resistance when contrasted with the same alloy aged by standard aging practices. Examples of these improved characteristics will be set forth in more detail in conjunction with the ensuing examples. Examples The examples are presented to illustrate the superior characteristics of an aluminum-lithium alloy aged in accordance with the present invention and to assist one of ordinary skill in making and using the present invention. Moreover, they are intended to illustrate the signifcantly improved and unexpected characteristics of an aluminum-lithium alloy formulated and manufactured in accordance with the paramters of the present invention. The following examples are not intended in any way to otherwise limit the scope of this disclosure or the protection granted by Letters Patent hereon. Example I An aluminum alloy containing 2.4 lithium, 1 percent magnesium, 1.3 percent copper, 0.15 percent zirconium with the balance being aluminum was formulated. The trace elements present in the formulation constituted less than 0.25 percent of the total. The iron and silicon present in the formulation constituted less than 0.07 percent each of the formulation. The alloy was cast and homogenized at 9750 F. Thereafter, the alloy was hot rolled to a thickness of 0.2 inches. The resulting sheet was then solution treated at 9750 F for about 1 hour. It was then quenched in water maintained at about 700 F. Thereafter, the sheet was subjected to a stretch of 1 1/2 percent of its initial length and then material was then cut into specimens. The specimens were cut to a size of 0.5 inch by 2 1/2 inch by 0.2 inch for the precrack Charpy impact tests, a known method of measuring fracture toughness. The specimens prepared for the tensile strength tests were 1 inch by 4 inches by 0.2 inches. A plurality of specimens were then aged at 3500 F for 4, 8 and 16 hours; at 3250F for 8, 16, and 48 hours; at 3050 P for 8 hours; at 2758 for 16 and 40 hours; and at 2500 F for 40 and 72 hours. Each of the specimens aged at each of the temperatures and times were then subjected to the tensile strength and precrack Charpy impact tests in accordance with standard testing procedures. The values of each of the specimens aged at a particular time and temperatures were then averaged. These average values are set forth in the graph of FIGURE 1. By observing FIGURE 1 it will be readily observed that specimens aged at temperatures greater than 3000F exhibit a toughness on the order of from 225 to 525 inch-pounds per square inch as measured by the Charpy impact test. By contrast, the specimens underaged at a low temperature in accordance with the present invention exhibit toughnesses on the order of 650 to almost 850inch pounds per square inch as indicated by the Charpy impact test. At the same time, the average strength of the materials fall generally within the 64 to 71 ksi range, with the exception of the specimens aged at 3500 F for 16 hours. These specimens, however, exhibited the lowest toughness of any of the specimens. Thus, these results indicate that aging at a temperature less than 3000 F for a relatively long time will clearly provide a strength/toughness combination that is superior to that of specimens aged in accordance with conventional procedures at temperatures on the order of 325 to 3500 F or more for relatively short periods of time. The results also show that there is a consistent improvement in the strength-toughness combination of properties as the aging temperature is lowered, i.e., a higher fracture toughness for any given strength level. Example I1 An aluminum alloy containing from 2 percent lithium, 1 percent magnesium, 2.5 percent copper, 0.15 percent zirconium, and the balance aluminum was formulated. The trace elements totaled less than 0.25 percent of the total composition, while the iron and silicon were maintained at less than 0.07 percent of the total formulation. The alloy was cast and homogenized at a temperature of about 9750 F. The alloy was then extruded into a bar having cross-sectional dimensions of 0.75 inch by 2.5 inch. The bar was then cut into predetermined lengths and solution heat treated at about 9750 F for 1 hour. Thereafter, the articles were quenched in either 700 F or 1800 F water. Once the bars had cooled, they were stretched approximately 1 1/2 percent of their original length. The bars were then fabricated into double cantilever bean (DCB) test specimens for measuring crack growth velocity during stress corrosion cracking. These specimens have a length of approximately six (6) inches. Identical specimens were aged at various temperatures for various times. The specimens were then tested for stress corrosion crack growth velocity employing conventional testing procedures. The plateau velocity (the stress insensitive region of growth) was determined and the results plotted in the graph of FIGURE 2 as percent of peak age versus plateau velocity in inches per hour, which provides an indication of stress corrosion resistance. The data points in FIGURE 2 indicate that low temperature underaging of the aluminum-lithium alloy formulated in accordance with the present invention results in a lower plateau velocity (higher stress corrosion resistance) than when the alloy is aged for conventional times at conventional temperatures. The present invention has been described in relation to various embodiments, including the preferred formulation and processing parameters. One of ordinary skill after reading the foregoing specification will be able to effect various changes, substitutions equivalents and other alterations without departing from the broad concepts departed herein. It is therefore intended that the scope of Letters Patent granted hereon will be limited only by the definition contained in the appended claims and equivalents thereof.

Claims: CLAIMS The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows: 1. A process for improving the relative strength and fracture toughness of an aluminum alloy containing lithium as an alloying element, said alloy first being formed into an article, solution heat treated and quenched, said process comprising the step of aging said alloy at a relatively low temperature for a relatively long time. 2. The process of Claim 1 wherein said temperature is in the range of from about 2000 F to about 3000 F. 3. The process of Claim 2 wherein said alloy is aged for a period of at least 1 hour. 4. The process of Claim 2 wherein said temperature is less than about 2750 F. 5. The process of Claim 4 wherein said alloy is aged at least about 2 hours. 6. The process of Claim 2 wherein said temperature is less than about 2500 F. 7. The process of Claim 6 wherein said alloy is aged for at least about 4 hours. 8. The process of Claim 1 wherein said alloy consists essentially of: Element Amount (wt. %) Li 1.0 to 3.2 Mg 0 to 5.5 Cu 0 to 4.5 Zr 0 to 0.2 Mn 0 to 1.2 Fe 0.3 max Si 0.5 max Other Trace Elements 0.25 max. Al Balance 9. The process of Claim 8 wherein said alloy consists essentially of: Element Amount (wt. 6) Li 1.8 to 2.6 Mg 0 to 4.7 Cu 0 to 3.7 Zr 0.07 to 0.15 Mn Fe 0 to 0.8 Si 0.12 max Other trace elements 0.25 Max Al Balance 10. The process of Claim 9 wherein said alloy consists essentially of: Element Amount (wt. %) Li 1.8 to 2.8 Mg 0 to 4.2 Cu 0 to 3.0 Zr 0.08 to 0.14 Mn 0 to 0.6 Fe 0.10 max Si 0.10 max Other trace elements 0.25 max Al Balance 11. The process of Claim 9 wherein magnesium is present in an amount ranging from 0 to 3.2 wt. % and wherein copper is present in an amount ranging from 0.5 to 3.0 wt. 6. 12. The product produced by the process of Claim 1 13. The product produced by the process of Claim 2 14. The product produced by the process of Claim 5 15. The product produced by the process of Claim 7 16. The product produced by the process of Claim 9 17. The product produced by the process of Claim 10 18. The product produced by the process of Claim 11 19. The process of Claim 1 wherein said alloy coiisists essentially of: Element Amount (wt. (rb) Li 2.2 to 2.8 Mg 0.2 to 0.8 Cu 1.5 to 2.1 Zr 0.1 to 0.15 Be 0.10 max Si 0.10 max Other trace elements 0.25 max Al Balance 20. The product of Claim 19.

Inventors: CURTIS, R. EUGENE, NARAYANAN, G. HARI, QUIST, WILLIAM E.
Applicants: THE BOEING COMPANY
Application year: 1984
Main classification: C22F1
IPC codes: C22F1, C22C21