US3305410A - Heat treatment of aluminum - Google Patents

Heat treatment of aluminum Download PDF

Info

Publication number
US3305410A
US3305410A US362493A US36249364A US3305410A US 3305410 A US3305410 A US 3305410A US 362493 A US362493 A US 362493A US 36249364 A US36249364 A US 36249364A US 3305410 A US3305410 A US 3305410A
Authority
US
United States
Prior art keywords
aging
alloy
temperature
hours
corrosion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US362493A
Inventor
Sublett George Robert
Fien Michael Waldemar
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Reynolds Metals Co
Original Assignee
Reynolds Metals Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Reynolds Metals Co filed Critical Reynolds Metals Co
Priority to US362493A priority Critical patent/US3305410A/en
Priority to GB11604/65A priority patent/GB1103322A/en
Application granted granted Critical
Publication of US3305410A publication Critical patent/US3305410A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • Heat-treatable aluminum base alloys especially the aluminum-copper and the aluminum-zinc-magnesium copper alloys, are extensively employed by the aircraft and aerospace industries. In these and other applications, such alloys must meet stringent corrosion requirements. However, experience has shown that these aloys frequently exhibit a tendency toward the development of undesirable forms of corrosion, such as intergranular corrosion which results in drastic reduction of the mechanical properties of these alloys, and stress corrosion which may result in sudden and possibly catastrophic failures.
  • An object of the invention was, therefore, to find a way of minimizing the tendency toward intergranular and stress corrosion in the case of artificially aged aluminum base alloys; and a further object was to find an optimum aging procedure, which would change the tendency toward intergranular corrosion to a shallow, pitting type of attack when the alloy was exposed to accelerated corrosion, and which would also produce typical mechanical properties.
  • the conventional practices previously known may be classified in three categories: (1) constant temperature aging treatments, in which the metal is aged at a suitable temperature which is not intentionally varied during the aging operation; (2) interrupted aging treatments, in which the metal is aged at one temperature for a period of time, then cooled to room temperature, and thereafter is heated at a higher temperature for an additional period of time; and (3) progressive aging treatments, in which the metal is aged at one temperature for a period of time, then is heated and held at a higher temperature for an additional period of time.
  • the tendency toward intergranular and stress corrosion of aluminum base alloys of the type which are susceptible to artificial aging can be minimized by performing the aging treatment in two stages, whereby the first stage is conducted at a higher temperature than the second stage.
  • the metal may be either cooled directly to the second stage temperature, or cooled to room temperature and subsequently reheated to the temperature of the second stage of the treatment, the former practice oridinarily being preferred because it reduces the overall processing time.
  • a typical high-low aging treatment in accordance with the invention is to maintain the alloy at about 400 F.
  • the conventional aging treatment normally specified for 2024 alloy (Military Specification MIL-H-6088C, October 15, 1962) consists of a constant aging temperature of 370 to 380 F. for a time of 7 to 16 hours, the aging time varying with the temper desired.
  • the first stage aging temperature in accordance with the present inven- 3,305,410 Patented Feb. 21, 1967 tion is preferably higher than the usual constant-temperature aging practice for the alloy, and the second stage temperature is ordinarily lower than the conventional aging temperature.
  • the initial high temperature is believed to have the effect to starting a controlled precipitation of the strengthening constituents in a generally uniform manner throughout the alloy, with the result that concentration of precipitated constituents at the grain boundaries (and consequent depletion thereof in the adjoining portions) is avoided or at least minimized.
  • the final aging at a reduced temperature completes the precipitation begun at the favorable locations, without causing the reduction in mechanical properties which ordinarily is associated with long aging times at higher temperatures.
  • the method of the invention is applicable to a variety of heat-treatable aluminum base alloys, including copperbearing alloys as well as zinc-bearing alloys.
  • the conventional solution heat treating practice for such alloys involves heating at a temperature which ranges from about 840 F. to 1050" F., followed by water quenching.
  • the novel process of the invention produces particularly favorable results with aluminum base alloys which are low in silicon content, preferably below about 0.5% by weight.
  • alloy 2024 which has a silicon content of 0.50% maximum is virtually completely protected against intergranular corrosion by the method of the invention, whereas alloy 2017, which has 0.8% maximum silicon content and ordinarily contains more silicon than 2024 alloy, responds less favorably.
  • the most favorable high-low aging treatment comprises maintaining the alloy in a first aging step at a temperature of from about 375 F. to about 425 F. for about 3 hours, and in a second aging step, maintaining the alloy at a temperature from about 275 F. to about 325 F. for about 10 hours.
  • the preferred treatment for alloy 2024 is a first step aging at 400 F. for 3 hours, followed by a second step aging at 300 F. for 10 hours.
  • the time periods for the two steps can vary somewhat according to the temperature used. Thus, the aging time can be shorter for a temperature of 425 F. than the 3 hour period for 400 F.
  • the preferred treatment is a first aging step at about 350 F. for about 5 hours, followed by a lower temperature aging step at about 250 F. for about 10 hours.
  • the temperature ranges for zincbearing alloys in general are about 325-400 F. for the initial aging step, and about 200-300 F. for the second step.
  • each sample is immersed for 1 minute in an etching solution at 200 F. to produce a uniform surface condition.
  • the etching solution is composed of 50 ml. 70% HNO 5 ml. 48% HF, balance distilled water.
  • the sample is rinsed in dis tilled water, immersed for 1 minute in concentrated HNO (70%) at room temperature to remove surface plated copper, rinsed in distilled water and allowed to dry.
  • the sample is then corroded by immersion in a minimum of 30 ml.
  • a solution having the composition Sodium chloride 57 grams, hydrogen peroxide (30%) ml., diluted to 1 liter with distilled water.
  • the immersion period is six hours. At the end of the immersion period, the sample is removed, washed and dried.
  • a cross-section specimen is cut and subjected to microscopic examination at 100 to 500 diameters magnification. The microscopic examination is made both before and after etching the specimen, using a metallurgical microscope. The etching is done by immersion for 6 to seconds in a solution having the composition: 70% HNO 2.5 ml., HCl (conc.) 1.5 ml., 48% HF 1 ml., distilled water 95 ml. There should be no evidence of excessive intergranular corrosion.
  • the heat-treated test samples are also tested for tensile strength, yield strength, and elongation properties.
  • Different diameter 2024 rods ranging from 2.5" to 3.5 diameter were cut into corrosion specimens. The corrosion tests were carried out as specified previously. Average and maximum depths of corrosion and type of corrosion were determined.
  • EXAMPLE 3 A 3% diameter rod of alloy 2017-T4 was cut into standard tensile and corrosion test specimens. The alloy had the chemical composition: Si 0.52, Fe 0.55, Cu 3.74, Mn 0.61, Mg 0.65, balance substantially Al.
  • EXAMPLE 2 The purpose of this example was to provide two ets of comparative corrosion tests in aging alloy 2024, the
  • the specimens were aged at 450 F. for 2 hours, followed by aging at 325 F. for 4 hours.
  • the mechanical properties were tested while the corrosion specimens were subjected to the standard NaCl-H O accelerated test described above. Average and maximum values and type of corrosion were determined.
  • the specimens tested typically showed a tensile strength (k.s.i.) of 58.7, a yield strength (k.s.i.) of 46.0, and elongation of 13%.
  • the corrosion depth in mils was 3.7 average, 10.2 maximum.
  • the corrosion was entirely of the pitting type.-
  • EXAMPLE 4 High-low aging of alloy 7075
  • samples of zincbearing alloy 7075 rod in solution heat treated condition were aged, and standard tensile and corrosion test specimens were tested as described previously.
  • the high-low aging practices used and the results obtained are compared in Table 4 with the results obtained by conventional aging practice at 245255 F. for 24 hours.
  • the aging practice of the present invention may follow conventional preparation of the alloy in solution heat treated condition, after which the alloy is heated from substantially ambient temperature to a suitable aging temperature for the initial aging step previously discussed.
  • the temperature is maintained for a substantial proportion of the total aging time, not less than about one hour.
  • the subsequent lower temperature aging step accounts for at least half (e.g. about 50-90%) of the total aging time.
  • copper-bearing and zinc-bearing aluminum base alloys are used herein to specify alloys which are predominantly aluminum and contain, respectively, copper and zinc as their major alloying addition, which is consistent with Aluminum Association designations for the 2000 and 7000-series alloys.
  • the method of treating a copper-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition comprising the steps of: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 400 F., maintaining said temperature for about 3 hours, cooling the alloy to a lower temperature of about 300 F., and aging the alloy at said lower temperature for about hours.
  • the method of treating a copper-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition comprising the steps off: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 450 F., maintaining said temperature for about 2 hours, cooling the alloy to a lower temperature of about 325 F., and aging the alloy at said lower temperature for about 4 hours.
  • the method of treating a zinc-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition comprising the steps of: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 350 F., maintaining said temperature for about 5 hours, cooling the alloy to a lower temperature of about 250 F., and aging the alloy at said lower temperature for about 10 hours.
  • the method of treating a copper-bearing or zinc-bearing aluminum base alloy of the type which exhibits a tendency toward the development of intergranular corrosion following constant-temperature aging comprising the steps of: providing-the alloy in solution heat treated c011- dition, by heating said alloy in the temperature range from about 840 to about 1050 F. for sufiicient time to dissolve the soluble constituents and thereafter quenching the alloy substantially to room temperature; heating the solution treated alloy to an aging temperature in the range from about 325 F.
  • the method of treating an aluminum base alloy which is susceptible to solution heat treatment and artificial aging comprising the steps of:
  • the alloy in solution heat treated condition substantially at room temperature, including the step of quenching the alloy in water from a solution temperature in the range from about 840 F., to about 1050- F heating the solution treated alloy to an aging temperature in the range from 325 F. to 475 F., and maintaining the temperature of the alloy in that range during a first aging period of at least an hour;
  • said first aging period constituting from about 10% to about 50% of the total aging time in said first and second aging periods.
  • the method of treating a zinc-bearing aluminum base alloy in accordance with claim 5, including the steps of maintaining the alloy during said first aging period for about 5 hours in the temperature range of 325 400 F., and thereafter maintaining the alloy during said second aging period for about 10 hours in the temperature range of 200-300" F.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Battery Electrode And Active Subsutance (AREA)
  • Preventing Corrosion Or Incrustation Of Metals (AREA)

Description

United States Patent M 3,305,410 HEAT TREATMENT OF ALUMINUM George Robert Sublett, Sheffield, and Michael Waldemar Fien, Florence, Ala., assignors to Reynolds Metals Company, a corporation of Delaware No Drawing. Filed Apr. 24, 1964, Ser. No. 362,493 12 Claims. (Cl. 148-159) This invention relates to a novel method for improveing the corrosion resistance of aluminum base alloys. More particularly, the invention concerns a novel twostage method of aging such aluminum base alloys subsequent to their solution heat treatment.
Heat-treatable aluminum base alloys, especially the aluminum-copper and the aluminum-zinc-magnesium copper alloys, are extensively employed by the aircraft and aerospace industries. In these and other applications, such alloys must meet stringent corrosion requirements. However, experience has shown that these aloys frequently exhibit a tendency toward the development of undesirable forms of corrosion, such as intergranular corrosion which results in drastic reduction of the mechanical properties of these alloys, and stress corrosion which may result in sudden and possibly catastrophic failures.
Previous attempts to alleviate this tendency to corrode have either failed to adequate improve corrosion resistance or have done so only at the expense of reducing mechanical properties. An object of the invention was, therefore, to find a way of minimizing the tendency toward intergranular and stress corrosion in the case of artificially aged aluminum base alloys; and a further object was to find an optimum aging procedure, which would change the tendency toward intergranular corrosion to a shallow, pitting type of attack when the alloy was exposed to accelerated corrosion, and which would also produce typical mechanical properties.
The conventional practices previously known may be classified in three categories: (1) constant temperature aging treatments, in which the metal is aged at a suitable temperature which is not intentionally varied during the aging operation; (2) interrupted aging treatments, in which the metal is aged at one temperature for a period of time, then cooled to room temperature, and thereafter is heated at a higher temperature for an additional period of time; and (3) progressive aging treatments, in which the metal is aged at one temperature for a period of time, then is heated and held at a higher temperature for an additional period of time.
In accordance with the invention, it has been found that the tendency toward intergranular and stress corrosion of aluminum base alloys of the type which are susceptible to artificial aging can be minimized by performing the aging treatment in two stages, whereby the first stage is conducted at a higher temperature than the second stage. After the first stage the metal may be either cooled directly to the second stage temperature, or cooled to room temperature and subsequently reheated to the temperature of the second stage of the treatment, the former practice oridinarily being preferred because it reduces the overall processing time. Thus, for example, in the case of 2024 alloy, which is a copper-bearing aluminum base alloy and will serve for purposes of illustration, a typical high-low aging treatment in accordance with the invention is to maintain the alloy at about 400 F. for about three hours, followed by holding the alloy at about 300 F. for about ten hours. For comparison purposes, the conventional aging treatment normally specified for 2024 alloy (Military Specification MIL-H-6088C, October 15, 1962) consists of a constant aging temperature of 370 to 380 F. for a time of 7 to 16 hours, the aging time varying with the temper desired. Thus, the first stage aging temperature in accordance with the present inven- 3,305,410 Patented Feb. 21, 1967 tion is preferably higher than the usual constant-temperature aging practice for the alloy, and the second stage temperature is ordinarily lower than the conventional aging temperature.
By carrying out the aging practice in this high-low sequence, resistance to intergranular and stress corrosion is appreciable improved. The initial high temperature is believed to have the effect to starting a controlled precipitation of the strengthening constituents in a generally uniform manner throughout the alloy, with the result that concentration of precipitated constituents at the grain boundaries (and consequent depletion thereof in the adjoining portions) is avoided or at least minimized. The final aging at a reduced temperature completes the precipitation begun at the favorable locations, without causing the reduction in mechanical properties which ordinarily is associated with long aging times at higher temperatures.
The method of the invention is applicable to a variety of heat-treatable aluminum base alloys, including copperbearing alloys as well as zinc-bearing alloys. The conventional solution heat treating practice for such alloys involves heating at a temperature which ranges from about 840 F. to 1050" F., followed by water quenching.
The novel process of the invention produces particularly favorable results with aluminum base alloys which are low in silicon content, preferably below about 0.5% by weight. Thus, in the copper-bearing alloy series, alloy 2024, which has a silicon content of 0.50% maximum is virtually completely protected against intergranular corrosion by the method of the invention, whereas alloy 2017, which has 0.8% maximum silicon content and ordinarily contains more silicon than 2024 alloy, responds less favorably.
In the case of alloy 2024, the most favorable high-low aging treatment comprises maintaining the alloy in a first aging step at a temperature of from about 375 F. to about 425 F. for about 3 hours, and in a second aging step, maintaining the alloy at a temperature from about 275 F. to about 325 F. for about 10 hours. The preferred treatment for alloy 2024 is a first step aging at 400 F. for 3 hours, followed by a second step aging at 300 F. for 10 hours. The time periods for the two steps can vary somewhat according to the temperature used. Thus, the aging time can be shorter for a temperature of 425 F. than the 3 hour period for 400 F.
In the case of alloy 2017, it has been found that a first aging step at 450 F. for about 2 hours, followed by a second aging step at 325 F. for about 4 hours, yielded satisfactory results. These temperatures are similarly subject to variations in range of about 25 F. upward or downward.
In the case of alloy 7075, the preferred treatment is a first aging step at about 350 F. for about 5 hours, followed by a lower temperature aging step at about 250 F. for about 10 hours. The temperature ranges for zincbearing alloys in general are about 325-400 F. for the initial aging step, and about 200-300 F. for the second step.
In evaluating the improvement in intergranular corrosion produced by the method of the invention, there may be employed the procedure outlined in Military Specification MIL-H-6088C, October 15, 1962. In this procedure, each sample is immersed for 1 minute in an etching solution at 200 F. to produce a uniform surface condition. The etching solution is composed of 50 ml. 70% HNO 5 ml. 48% HF, balance distilled water. After this etching treatment, the sample is rinsed in dis tilled water, immersed for 1 minute in concentrated HNO (70%) at room temperature to remove surface plated copper, rinsed in distilled water and allowed to dry. The sample is then corroded by immersion in a minimum of 30 ml. per square inch of surface area of a solution having the composition: Sodium chloride 57 grams, hydrogen peroxide (30%) ml., diluted to 1 liter with distilled water. The immersion period is six hours. At the end of the immersion period, the sample is removed, washed and dried. A cross-section specimen is cut and subjected to microscopic examination at 100 to 500 diameters magnification. The microscopic examination is made both before and after etching the specimen, using a metallurgical microscope. The etching is done by immersion for 6 to seconds in a solution having the composition: 70% HNO 2.5 ml., HCl (conc.) 1.5 ml., 48% HF 1 ml., distilled water 95 ml. There should be no evidence of excessive intergranular corrosion.
The heat-treated test samples are also tested for tensile strength, yield strength, and elongation properties.
The following examples illustrate the practice of the novel method of the invention, but are not to be considered as limiting:
EXAMPLE 1 High-low aging of alloy 2024 A length of (solution heat treated) 2024 alloy rod, 1% inches in diameter, was cut into tensile strength and corrosion test specimens. The corrosion specimens consisted of inch disc, cut in half and machined along the cut face. The tensile strength specimens were standard size. The chemical analysis of the rod was Si 0.15, Fe 0.30, Cu 4.20, Mn 0.60, Mg 1.48, balance substantially Al.
Various individual specimens were subjected to aging cycles as shown in Table 1. The aged tensile strength specimens were tested for tensile strength, yield strength, and elongation, using standard tests. The corrosion specimens were subjected to the standard accelerated Nam-H 0 corrosion test, mounted, etched and examined microscopically, as described above. The results are summarized in Table 1.
first employing the standard aging treatment of 13 hours at 375 F., the control group, and a second series according to the preferred method of the invention, aging at 400 F. for 3 hours followed by a second aging at 300 F. for 10 hours.
Different diameter 2024 rods, ranging from 2.5" to 3.5 diameter were cut into corrosion specimens. The corrosion tests were carried out as specified previously. Average and maximum depths of corrosion and type of corrosion were determined.
The results as shown in Table 3 clearly demonstrate the superior properties imparted by the high-low aging treatment of the invention, as compared with the standard one-step aging treatment. They show that all specimens that had received the high-low aging treatment of the invention exhibited a pitting type of corrosion attack. The control specimens were more susceptible to intergranular corrosion.
TABLE 3 [Corrosion depth in mils] Standard Aging 1 High-Low Aging Dirt. (in.)
Avg. Max. Type Avg. Max. Type 2.500 3.7 7.3 PandI 3.6 7.5 P 2.562 5. l 6. 8 P and I 3. 2 4. 7 P 2.875 4. 2 7. 0 P and I 2. 9 4. 7 I 3.00. 5.5 9.0 PandI 2.9 5.8 I 3.125 4.3 8.2 PandI 2.9 5.8 P 3.250 4. 6 7. l P and I 2. 4 4. 7 P 3.500 4. 5 7. 2 P and I 2.3 4. 5 I
l Pitting; I, Intergranular-Attack.
EXAMPLE 3 A 3% diameter rod of alloy 2017-T4 was cut into standard tensile and corrosion test specimens. The alloy had the chemical composition: Si 0.52, Fe 0.55, Cu 3.74, Mn 0.61, Mg 0.65, balance substantially Al.
TABLE 2 Sample No. Depth (mils), Depth (mils), Type 015 Avg. Max. Corrosion 3. 4 6.1 Fitting. 3.4 5.3 Do. 3. 5 7.5 Do.
EXAMPLE 2 The purpose of this example was to provide two ets of comparative corrosion tests in aging alloy 2024, the
The specimens were aged at 450 F. for 2 hours, followed by aging at 325 F. for 4 hours. The mechanical properties were tested while the corrosion specimens were subjected to the standard NaCl-H O accelerated test described above. Average and maximum values and type of corrosion were determined.
The specimens tested typically showed a tensile strength (k.s.i.) of 58.7, a yield strength (k.s.i.) of 46.0, and elongation of 13%. The corrosion depth in mils was 3.7 average, 10.2 maximum. The corrosion was entirely of the pitting type.-
EXAMPLE 4 High-low aging of alloy 7075 In order to illustrate the applicability of the high-low aging treatment to other alloy systems, samples of zincbearing alloy 7075 rod in solution heat treated condition were aged, and standard tensile and corrosion test specimens were tested as described previously. The high-low aging practices used and the results obtained are compared in Table 4 with the results obtained by conventional aging practice at 245255 F. for 24 hours.
The comparison shows that high-low aging practices can be employed to substantially eliminate intergranular corrosion, with only a slight reduction in mechanical properties.
The aging practice of the present invention may follow conventional preparation of the alloy in solution heat treated condition, after which the alloy is heated from substantially ambient temperature to a suitable aging temperature for the initial aging step previously discussed. The temperature is maintained for a substantial proportion of the total aging time, not less than about one hour. The subsequent lower temperature aging step accounts for at least half (e.g. about 50-90%) of the total aging time.
The expressions copper-bearing and zinc-bearing aluminum base alloys are used herein to specify alloys which are predominantly aluminum and contain, respectively, copper and zinc as their major alloying addition, which is consistent with Aluminum Association designations for the 2000 and 7000-series alloys.
The published composition limits for various commercial alloys discussed herein are given below:
Others, each. Others, Tota 0.15. Al Balance.
Balance.
While present preferred examples of the practice of the invention have been described, it will be understood that the invention may be otherwise variously embodied and practiced within the scope of the following claims.
What is claimed is:
1. The method of treating a copper-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition, comprising the steps of: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 400 F., maintaining said temperature for about 3 hours, cooling the alloy to a lower temperature of about 300 F., and aging the alloy at said lower temperature for about hours.
2. The method of treating a copper-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition, comprising the steps off: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 450 F., maintaining said temperature for about 2 hours, cooling the alloy to a lower temperature of about 325 F., and aging the alloy at said lower temperature for about 4 hours.
3. The method of treating a zinc-bearing aluminum base alloy so as to reduce its tendency toward the development of intergranular corrosion in the aged condition, comprising the steps of: providing the alloy in solution heat treated condition, substantially at room temperature, heating the solution treated alloy to an aging temperature of about 350 F., maintaining said temperature for about 5 hours, cooling the alloy to a lower temperature of about 250 F., and aging the alloy at said lower temperature for about 10 hours.
4. In the treatment of aluminum alloys which are susceptible to solution heat treatment and artificial aging, the method of treating a copper-bearing or zinc-bearing aluminum base alloy of the type which exhibits a tendency toward the development of intergranular corrosion following constant-temperature aging, comprising the steps of: providing-the alloy in solution heat treated c011- dition, by heating said alloy in the temperature range from about 840 to about 1050 F. for sufiicient time to dissolve the soluble constituents and thereafter quenching the alloy substantially to room temperature; heating the solution treated alloy to an aging temperature in the range from about 325 F. to about 475 R, and maintaining said temperature substantially constant in a first aging step for a period of time representing about onethird of the total aging time; and completing the aging of said alloy in a second aging step by maintaining the alloy for the remaining aging time at a lower aging temperature in the range from about 200 F. to about 350 F. 5. The method of treating an aluminum base alloy which is susceptible to solution heat treatment and artificial aging, comprising the steps of:
providing the alloy in solution heat treated condition, substantially at room temperature, including the step of quenching the alloy in water from a solution temperature in the range from about 840 F., to about 1050- F heating the solution treated alloy to an aging temperature in the range from 325 F. to 475 F., and maintaining the temperature of the alloy in that range during a first aging period of at least an hour;
cooling the alloy directly to a lower temperature in the range from 200 F. to 350 F. and maintaining the temperature of the alloy in the latter range during a second aging period;
said first aging period constituting from about 10% to about 50% of the total aging time in said first and second aging periods.
6. The method of claim 5, wherein said first aging period constitutes about one-third of the total aging time.
7. The method of treating a copper-bearing aluminum base alloy in accordance with claim 5, including the steps of maintaining the alloy during said first aging period in the temperature range of about 375-475 F., and thereafter maintaining the alloy during said second aging period in the temperature range of about 275350 F.
8. The method of treating a copper-bearing aluminum base alloy in accordance with claim 5, said alloy containing not more than 0.5% silicon, by weight, including the steps of maintaining the alloy during said first aging period for about 3 hours in the temperature range of 375425 F., and thereafter maintaining the alloy during said second aging period for about 10 hours in the temperature range of 275-325 F.
9. The method of treating a zinc-bearing aluminum base alloy in accordance with claim 5, including the steps of maintaining the alloy during said first aging period for about 5 hours in the temperature range of 325 400 F., and thereafter maintaining the alloy during said second aging period for about 10 hours in the temperature range of 200-300" F.
10. The method of treating a Zinc-bearing aluminum base alloy in accordance with claim 5, said alloy containing 5.1 to 6.1% zinc, 2.1 to 2.9% magnesium and 1.2 to 2.0% copper, by weight, including the steps of maintaining the alloy during said first aging period at about 350 F. for approximately 5 hours, and, during said second aging period, at about 250 F.
11. The method of treating a copper-bearing aluminum base alloy in accordance with claim 5, said alloy containing 3.8 to 4.9% copper, 1.2 to 1.8% magnesium and 0.30 to 0.9% manganese, by weight, including the steps of maintaining the alloy during said first aging period at about 400 F. for approximately 3 hours, and, during said second aging period, at about 300 F.
12. The method of treating a copper-bearing aluminum 0 base alloy in accordance with claim 5, said alloy containing 3.5 to 4.5% copper, 0.4 to 1.0% manganese and 0.20 to 0.8% magnesium, by weight, including the steps of maintaining the alloy during said first aging period References Cited by the Examiner UNITED STATES PATENTS 2,159,010 5/1939 Dix et al 148-l59 2,242,944 5/1941 Dix et a1. 148159 3,133,839 5/1964 Thomas 14811.5 X
FOREIGN PATENTS 432,815 12/1936 Great Britain.
at about 450 F. for approximately 2 hours, and, during 10 DAVID RECK Examine"- said second aging period, at about 325 F.
C. N. LOVELL, Assistant Examiner.

Claims (1)

1. THE METHOD OF TREATING A COPPER-BEARING ALUMINUM BASE ALLOY SO AS TO REDUCE ITS TENDENCY TOWARD THE DEVELOPMENT OF INTERGRANULAR CORROSION IN THE AGED CONDITION, COMPRISING THE STEPS OF PROVIDING THE ALLOY IN SOLUTION HEAT TREATED CONDITION, SUBSTANTIALLY AT ROOM TEMPERATURE, HEATING THE SOLUTION TREATED ALLOY TO AN AGING TEMPERATURE OF ABOUT 400*F., MAINTAINING SAID TEMPERATURE FOR ABOUT 3 HOURS, COOLING THE ALLOY TO A LOWER TEMPERATURE OF ABOUT 300*F., AND AGING THE ALLOY AT SAID LOWER TEMPERATURE FOR ABOUT 10 HOURS.
US362493A 1964-04-24 1964-04-24 Heat treatment of aluminum Expired - Lifetime US3305410A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US362493A US3305410A (en) 1964-04-24 1964-04-24 Heat treatment of aluminum
GB11604/65A GB1103322A (en) 1964-04-24 1965-03-18 Aging of aluminum base alloys

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US362493A US3305410A (en) 1964-04-24 1964-04-24 Heat treatment of aluminum

Publications (1)

Publication Number Publication Date
US3305410A true US3305410A (en) 1967-02-21

Family

ID=23426334

Family Applications (1)

Application Number Title Priority Date Filing Date
US362493A Expired - Lifetime US3305410A (en) 1964-04-24 1964-04-24 Heat treatment of aluminum

Country Status (2)

Country Link
US (1) US3305410A (en)
GB (1) GB1103322A (en)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4323399A (en) * 1978-09-08 1982-04-06 Cegedur Societe De Transformation De L'aluminium Pechiney Process for the thermal treatment of aluminium - copper - magnesium - silicon alloys
US4832758A (en) * 1973-10-26 1989-05-23 Aluminum Company Of America Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys
US4861391A (en) * 1987-12-14 1989-08-29 Aluminum Company Of America Aluminum alloy two-step aging method and article
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
WO1995024514A1 (en) * 1994-03-10 1995-09-14 Reynolds Metals Company Heat treatment for thick aluminum plate
US5496426A (en) * 1994-07-20 1996-03-05 Aluminum Company Of America Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product
US5643372A (en) * 1993-09-28 1997-07-01 Pechiney Rhenalu Process for the desensitisation to intercrystalline corrosion of 2000 and 6000 series Al alloys and corresponding products
US5785777A (en) * 1996-11-22 1998-07-28 Reynolds Metals Company Method of making an AA7000 series aluminum wrought product having a modified solution heat treating process for improved exfoliation corrosion resistance
US6869490B2 (en) 2000-10-20 2005-03-22 Pechiney Rolled Products, L.L.C. High strength aluminum alloy
US20060174980A1 (en) * 2004-10-05 2006-08-10 Corus Aluminium Walzprodukte Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US20070125460A1 (en) * 2005-10-28 2007-06-07 Lin Jen C HIGH CRASHWORTHINESS Al-Si-Mg ALLOY AND METHODS FOR PRODUCING AUTOMOTIVE CASTING
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
WO2008003503A3 (en) * 2006-07-07 2008-02-21 Aleris Aluminum Koblenz Gmbh Method of manufacturing aa2000 - series aluminium alloy products
US20080173378A1 (en) * 2006-07-07 2008-07-24 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminum alloy products and a method of manufacturing thereof
US20080283163A1 (en) * 2007-05-14 2008-11-20 Bray Gary H Aluminum Alloy Products Having Improved Property Combinations and Method for Artificially Aging Same
US20090269608A1 (en) * 2003-04-10 2009-10-29 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu ALLOY WITH IMPROVED DAMAGE TOLERANCE-STRENGTH COMBINATION PROPERTIES
US20090320969A1 (en) * 2003-04-10 2009-12-31 Aleris Aluminum Koblenz Gmbh HIGH STENGTH Al-Zn ALLOY AND METHOD FOR PRODUCING SUCH AN ALLOY PRODUCT
US20100037998A1 (en) * 2007-05-14 2010-02-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
US9249487B2 (en) 2013-03-14 2016-02-02 Alcoa Inc. Methods for artificially aging aluminum-zinc-magnesium alloys, and products based on the same
US9765419B2 (en) 2014-03-12 2017-09-19 Alcoa Usa Corp. Methods for artificially aging aluminum-zinc-magnesium alloys, and products based on the same
WO2022129806A1 (en) 2020-12-18 2022-06-23 Constellium Issoire Wrought products made of 2xxx alloy having an optimized corrosion resistance, and method for obtaining same
WO2023028070A1 (en) 2021-08-24 2023-03-02 Arconic Technologies Llc Methods of producing 2xxx aluminum alloys
CN117364001A (en) * 2023-10-24 2024-01-09 河北科技大学 A submicron ultra-high strength and corrosion-resistant aluminum alloy processing technology

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB432815A (en) * 1934-03-01 1935-08-02 Horace Campbell Hall Improvements in heat treatment of aluminium alloys
US2159010A (en) * 1937-04-30 1939-05-23 Aluminum Co Of America Thermal treatment of aluminum base alloys
US2242944A (en) * 1939-05-05 1941-05-20 Aluminum Co Of America Thermal treatment of aluminum base alloys
US3133839A (en) * 1961-05-11 1964-05-19 Thomas Gareth Process for improving stress-corrosion resistance of age-hardenable alloys

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB432815A (en) * 1934-03-01 1935-08-02 Horace Campbell Hall Improvements in heat treatment of aluminium alloys
US2159010A (en) * 1937-04-30 1939-05-23 Aluminum Co Of America Thermal treatment of aluminum base alloys
US2242944A (en) * 1939-05-05 1941-05-20 Aluminum Co Of America Thermal treatment of aluminum base alloys
US3133839A (en) * 1961-05-11 1964-05-19 Thomas Gareth Process for improving stress-corrosion resistance of age-hardenable alloys

Cited By (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4832758A (en) * 1973-10-26 1989-05-23 Aluminum Company Of America Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
US4323399A (en) * 1978-09-08 1982-04-06 Cegedur Societe De Transformation De L'aluminium Pechiney Process for the thermal treatment of aluminium - copper - magnesium - silicon alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
US4861391A (en) * 1987-12-14 1989-08-29 Aluminum Company Of America Aluminum alloy two-step aging method and article
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5643372A (en) * 1993-09-28 1997-07-01 Pechiney Rhenalu Process for the desensitisation to intercrystalline corrosion of 2000 and 6000 series Al alloys and corresponding products
WO1995024514A1 (en) * 1994-03-10 1995-09-14 Reynolds Metals Company Heat treatment for thick aluminum plate
US5496426A (en) * 1994-07-20 1996-03-05 Aluminum Company Of America Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product
US5785777A (en) * 1996-11-22 1998-07-28 Reynolds Metals Company Method of making an AA7000 series aluminum wrought product having a modified solution heat treating process for improved exfoliation corrosion resistance
US6869490B2 (en) 2000-10-20 2005-03-22 Pechiney Rolled Products, L.L.C. High strength aluminum alloy
US20050189048A1 (en) * 2000-10-20 2005-09-01 Alex Cho High strength aluminum alloy
US7125459B2 (en) 2000-10-20 2006-10-24 Pechiney Rolled Products Llc High strength aluminum alloy
US20090269608A1 (en) * 2003-04-10 2009-10-29 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu ALLOY WITH IMPROVED DAMAGE TOLERANCE-STRENGTH COMBINATION PROPERTIES
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
US20090320969A1 (en) * 2003-04-10 2009-12-31 Aleris Aluminum Koblenz Gmbh HIGH STENGTH Al-Zn ALLOY AND METHOD FOR PRODUCING SUCH AN ALLOY PRODUCT
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US20060174980A1 (en) * 2004-10-05 2006-08-10 Corus Aluminium Walzprodukte Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
US9353430B2 (en) 2005-10-28 2016-05-31 Shipston Aluminum Technologies (Michigan), Inc. Lightweight, crash-sensitive automotive component
US8721811B2 (en) 2005-10-28 2014-05-13 Automotive Casting Technology, Inc. Method of creating a cast automotive product having an improved critical fracture strain
US20070125460A1 (en) * 2005-10-28 2007-06-07 Lin Jen C HIGH CRASHWORTHINESS Al-Si-Mg ALLOY AND METHODS FOR PRODUCING AUTOMOTIVE CASTING
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8088234B2 (en) 2006-07-07 2012-01-03 Aleris Aluminum Koblenz Gmbh AA2000-series aluminum alloy products and a method of manufacturing thereof
US20080173378A1 (en) * 2006-07-07 2008-07-24 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminum alloy products and a method of manufacturing thereof
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
WO2008003503A3 (en) * 2006-07-07 2008-02-21 Aleris Aluminum Koblenz Gmbh Method of manufacturing aa2000 - series aluminium alloy products
US20080210349A1 (en) * 2006-07-07 2008-09-04 Aleris Aluminum Koblenz Gmbh Aa2000-series aluminum alloy products and a method of manufacturing thereof
US20080173377A1 (en) * 2006-07-07 2008-07-24 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US20080283163A1 (en) * 2007-05-14 2008-11-20 Bray Gary H Aluminum Alloy Products Having Improved Property Combinations and Method for Artificially Aging Same
US8840737B2 (en) 2007-05-14 2014-09-23 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8673209B2 (en) 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US20100037998A1 (en) * 2007-05-14 2010-02-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
US9249487B2 (en) 2013-03-14 2016-02-02 Alcoa Inc. Methods for artificially aging aluminum-zinc-magnesium alloys, and products based on the same
GB2526758B (en) * 2013-03-14 2020-08-26 Alcoa Usa Corp Methods for artificially aging aluminum-zinc-magnesium alloys, and products based on the same
US9765419B2 (en) 2014-03-12 2017-09-19 Alcoa Usa Corp. Methods for artificially aging aluminum-zinc-magnesium alloys, and products based on the same
WO2022129806A1 (en) 2020-12-18 2022-06-23 Constellium Issoire Wrought products made of 2xxx alloy having an optimized corrosion resistance, and method for obtaining same
FR3118065A1 (en) * 2020-12-18 2022-06-24 Constellium Issoire Wrought 2xxx alloy products with optimized corrosion resistance and process for obtaining
US12421587B2 (en) 2020-12-18 2025-09-23 C-Tec Constellium Technology Center Wrought products made of 2XXX alloy having an optimized corrosion resistance, and method for obtaining same
WO2023028070A1 (en) 2021-08-24 2023-03-02 Arconic Technologies Llc Methods of producing 2xxx aluminum alloys
EP4392591A4 (en) * 2021-08-24 2025-08-27 Arconic Tech Llc PROCESS FOR THE PRODUCTION OF 2XXX ALUMINUM ALLOYS
CN117364001A (en) * 2023-10-24 2024-01-09 河北科技大学 A submicron ultra-high strength and corrosion-resistant aluminum alloy processing technology

Also Published As

Publication number Publication date
GB1103322A (en) 1968-02-14

Similar Documents

Publication Publication Date Title
US3305410A (en) Heat treatment of aluminum
US3856584A (en) Reducing the susceptibility of alloys, particularly aluminium alloys, to stress corrosion cracking
CA2014970C (en) Oxidation resistant titanium-base alloy
US2248185A (en) Heat treatment of aluminum base alloys
CN105612266A (en) Method for transforming al-cu-li alloy sheets improving formability and corrosion resistance
US3947297A (en) Treatment of aluminum alloys
US3703367A (en) Copper-zinc alloys
US2101087A (en) Copper base alloy
JPS5948859B2 (en) Method for improving mechanical properties and corrosion resistance under pressure of aluminum alloys
US3334998A (en) Magnesium base alloys
US4063936A (en) Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
US2789900A (en) Copper base alloys containing iron and aluminum
US3133839A (en) Process for improving stress-corrosion resistance of age-hardenable alloys
JP2005076098A (en) HIGH-STRENGTH alpha-beta TITANIUM ALLOY
US3231435A (en) Method of eliminating stress corrosion cracking in copper-magnesium-zinc series aluminum alloys
US2122535A (en) Duplex metal article
US3640777A (en) Heat treatment of high-chromium alloys to improve ductility
NO852962L (en) COPPER-NICKEL-TINN COBALT Alloy.
USRE26907E (en) Aluminum alloys and articles made therefrom
US4612166A (en) Copper-silicon-tin alloys having improved cleanability
US3532559A (en) Cold reduced titanium-base alloy
US2454312A (en) High-strength corrosion-resistant aluminum alloy sheets
Itoh et al. Suppression of intergranular fracture in 7000 series aluminum alloys
US3880679A (en) Method of forming zinc-aluminum alloys with good machinability
NO791834L (en) ALUMINUM ALLOYS WITH IMPROVED ELECTRICAL CONDUCTIVITY AND PROCEDURE FOR MANUFACTURE OF SUCH ALLOY