US3856584A - Reducing the susceptibility of alloys, particularly aluminium alloys, to stress corrosion cracking - Google Patents

Reducing the susceptibility of alloys, particularly aluminium alloys, to stress corrosion cracking Download PDF

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US3856584A
US3856584A US00340757A US34075773A US3856584A US 3856584 A US3856584 A US 3856584A US 00340757 A US00340757 A US 00340757A US 34075773 A US34075773 A US 34075773A US 3856584 A US3856584 A US 3856584A
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    • 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

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  • the present invention relates to a method for reducing the susceptibility of certain alloys to stresscorrosion cracking.
  • the invention is particularly useful with respect to aluminum alloys of the 7,000 series aluminum alloys containing zinc, magnesium and copper, especially aluminum alloy 7075 and is therefore described in connection with such alloys, but it will be appreciated that it could be used also for improving the stress-corrosion resistance of other alloys, such as magnesium, stainless steel and titanium alloys.
  • High strength aluminum alloys for example of the 2,000 and 7,000 series, are subjected to a solution heat treatment at a high temperature followed by an ageing treatment at a considerably lower temperature in order to obtain their high strength.
  • a solution heat treatment normally produces a susceptibility to stress-corrosion cracking, that is the rupture of metal that occurs under the combined influence of a corrosive environment and applied or residual tensile stress.
  • the 7,000 series alloys such as 7075 are sometimes subjected to a modified ageing procedure, called overageing, likewise at only moderately elevated temperature to reduce this susceptibility to stress-corrosion cracking, but this further heat treatment also has the effect of reducing the strength of the alloy.
  • the solution heat treatment is usually effected at about 480C
  • the ageing heat treatment commonly called T6 temper
  • T73 temper is a two-stage over-ageing treatment, the details of which are described in U.S. Pat. No. 3,198,676.
  • the present invention provides a method for reducing the susceptibility of the 7,000 series aluminum alloys to stress-corrosion cracking while still retaining substantially the original strength of the alloy.
  • the alloy that has been subjected to a solution heat treatment at a high temperature and then to an ageing treatment (e.g., the T6 temper) at a lower temperature is subsequently subjected to (1) a retrogression heat treatment for a short period of time at a temperature above the agehardening temperature of the alloy but below the solution heat treatment, and (2) to a re-ageing heat treatment for a substantially longer period of time at the age-hardening temperature of the alloy.
  • an ageing treatment e.g., the T6 temper
  • the age-hardening temperature of the above step (2) is preferably the same as that of the normal ageing (e.g., T6) treatment but may be another suitable agehardening temperature applicable to the particular alloy being treated.
  • the present invention can therefore broadly be characterized by the combined steps of (1) retrogression and (2) re-ageing, rather than the heretofore used ageing alone (T6 temper) or over-ageing (T73 temper), for reducing susceptibility to stress-corrosion cracking.
  • the heat treatment of the present invention may therefore be termed as RR temper (retrogression and reageing).
  • the susceptibility to stress-corrosion cracking is believed to be due to networks of dislocations which are produced during the solution heat treatment of precipitation hardening alloys. For example, it has been found that such dislocations in the 7075 T6 alloy are formed during the quenching from the solution heat treatment temperature. These dislocations are substantially removed by the previously mentioned over-ageing treatment (T73 temper), but at the same time the strength of the alloy is reduced.
  • the retrogression treatment partially redissolves the precipitate responsible for the previous hardening of the material, resulting in a softening of the material.
  • the retrogression treatment is also believed to disperse the networks of dislocations responsible for the susceptibility to stress corrosion.
  • the subsequent re-ageing step re-hardens the material to recover its original maximum strength properties.
  • the T73 temper results in permanent and non-recoverable softening of the material due to a more advanced state of the age-hardening process, thereby producing a greater extend of precipitation and conversion of coherent to non-coherent precipitation.
  • the retrogression treatment is preferably effected from 200 to 260 C for a few seconds to a few minutes. More particularly, the preferred combinations of time and temperature are -120 seconds at 200 C; 15-60 seconds at 220C; 15 seconds at 240C; and 7 seconds at 260 C.
  • the subsequent re-ageing treatment is not as critical with respect to temperature or time, but preferably should be effected at the temperature of 1 15-1 25C for up to several days. In the preferred examples, the re-ageing was effected at 121C for 16-48 hours.
  • the retrogression heat treatment in the examples described below was carried out in a silicone oil bath in view of the very short time's involved. The samples were then air cooled or water quenched before being subjected to the re-ageing treatment.
  • the depth of the material affected by the novel heat treatment can be controlled by the retrogression conditions employed, the section thickness, and the heating medium.
  • a liquid bath could have effect only on a limited depth of the material, whereas induction heating in the retrogression step could considerably increase the effective depth.
  • the novel heat treatment is therefore particularly adaptable as a users heat treatment to be applied to an article in the final or nearfinal machined conditon.
  • step (a) a. subjecting the alloy to a retrogression heat treatment for a few seconds to a few minutes at a temperature of from 200C to 260C, which temperature is above the age-hardening temperature of the alloy but below the solution heat treatment temperature; and b. subsequently subjecting the alloy to a re-aging heat treatment at a temperature from C to C for a substantially longer period of time than in step (a) up to several days.
  • said alloy is aluminum alloy 7075.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
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  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
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  • Preventing Corrosion Or Incrustation Of Metals (AREA)

Abstract

A method is described of thermally treating the 7,000 series aluminum alloys that have been subjected to a solution heat treatment at a high temperature and then to an ageing treatment at a lower temperature, thereby hardening the alloy but likewise producing therein a susceptibility to stress-corrosion cracking. The novel method comprises the steps of (1) subjecting the alloy to a retrogression heat treatment for a short period of time at a temperature above the age-hardening temperature of the alloy but below the solution heat treatment temperature, and (2) subsequently subjecting the alloy to a re-ageing heat treatment for a substantially longer period of time at the age-hardening temperature of the alloy. This method substantially reduces the susceptibility of the alloy to stress-corrosion cracking while retaining its original strength.

Description

United States Patent Cina [11] 3,856,584 Dec. 24, 1974 REDUCING THE SUSCEPTIIBILITY OF ALLOYS, PARTICULARLY ALUMINIUM ALLOYS, TO STRESS CORROSION CRACKING Baruch M. Cina, Ramat Gan, Israel Israel Aircraft Industries Ltd., Lod Airport, Israel Filed: Mar. 13, 1973 Appl. No.: 340,757
Inventor:
Assignee:
Foreign Application Priority Data Apr. 12, 1972 Israel 39200 US. Cl. 148/159, 148/325 Int. Cl. C221 1/04 Field of Search 75/141, 142, 146;
References Cited UNITED STATES PATENTS 7/1933 Lyon 148/159 4/1941 Smith..... 7/1971 Nook 148/159 3,198,676 8/1965 Sprowls et al. 148/159 Primary Examiner-C. Lovell Attorney, Agent, or FirmBenjamin J. Barish [57] ABSTRACT hardening temperature of the alloy but below the solution heat treatment temperature, and (2) subsequently subjecting the alloy to a re-ageing heat treatment for a substantially longer period of time at the agehardening temperature of the alloy. This method substantially reduces the susceptibility of the alloy to stress-corrosion cracking while retaining its original strength.
2 Claims, No Drawings BACKGROUND OF THE INVENTION The present invention relates to a method for reducing the susceptibility of certain alloys to stresscorrosion cracking. The invention is particularly useful with respect to aluminum alloys of the 7,000 series aluminum alloys containing zinc, magnesium and copper, especially aluminum alloy 7075 and is therefore described in connection with such alloys, but it will be appreciated that it could be used also for improving the stress-corrosion resistance of other alloys, such as magnesium, stainless steel and titanium alloys.
High strength aluminum alloys, for example of the 2,000 and 7,000 series, are subjected to a solution heat treatment at a high temperature followed by an ageing treatment at a considerably lower temperature in order to obtain their high strength. However, such treatment normally produces a susceptibility to stress-corrosion cracking, that is the rupture of metal that occurs under the combined influence of a corrosive environment and applied or residual tensile stress. For this reason, the 7,000 series alloys such as 7075 are sometimes subjected to a modified ageing procedure, called overageing, likewise at only moderately elevated temperature to reduce this susceptibility to stress-corrosion cracking, but this further heat treatment also has the effect of reducing the strength of the alloy.
For example, taking the case of a high strength aluminum alloy 7075, the solution heat treatment is usually effected at about 480C, and the ageing heat treatment, commonly called T6 temper, is usually effected at about 121C for about 24 hours. Instead of the T6 temper, in which case the alloy still has a high susceptibility to stress-corrosion cracking, there is commonly used another heat treatment, called the T73 temper, which is a two-stage over-ageing treatment, the details of which are described in U.S. Pat. No. 3,198,676. While this over-ageing treatment (T73 temper) does reduce the susceptibility of the alloy to stress-corrosion cracking, it also reduces its strength about BRIEF SUMMARY OF THE INVENTION The present invention provides a method for reducing the susceptibility of the 7,000 series aluminum alloys to stress-corrosion cracking while still retaining substantially the original strength of the alloy.
According to the present invention, the alloy that has been subjected to a solution heat treatment at a high temperature and then to an ageing treatment (e.g., the T6 temper) at a lower temperature, is subsequently subjected to (1) a retrogression heat treatment for a short period of time at a temperature above the agehardening temperature of the alloy but below the solution heat treatment, and (2) to a re-ageing heat treatment for a substantially longer period of time at the age-hardening temperature of the alloy.
The age-hardening temperature of the above step (2) is preferably the same as that of the normal ageing (e.g., T6) treatment but may be another suitable agehardening temperature applicable to the particular alloy being treated.
The present invention can therefore broadly be characterized by the combined steps of (1) retrogression and (2) re-ageing, rather than the heretofore used ageing alone (T6 temper) or over-ageing (T73 temper), for reducing susceptibility to stress-corrosion cracking. The heat treatment of the present invention may therefore be termed as RR temper (retrogression and reageing).
The following explanation may be helpful in understanding the present invention. The susceptibility to stress-corrosion cracking is believed to be due to networks of dislocations which are produced during the solution heat treatment of precipitation hardening alloys. For example, it has been found that such dislocations in the 7075 T6 alloy are formed during the quenching from the solution heat treatment temperature. These dislocations are substantially removed by the previously mentioned over-ageing treatment (T73 temper), but at the same time the strength of the alloy is reduced.
In the present invention, the retrogression treatment partially redissolves the precipitate responsible for the previous hardening of the material, resulting in a softening of the material. The retrogression treatment is also believed to disperse the networks of dislocations responsible for the susceptibility to stress corrosion. The subsequent re-ageing step re-hardens the material to recover its original maximum strength properties. The T73 temper, on the other hand, results in permanent and non-recoverable softening of the material due to a more advanced state of the age-hardening process, thereby producing a greater extend of precipitation and conversion of coherent to non-coherent precipitation.
DESCRIPTION OF THE PREFERRED EMBODIMENTS Described below are a number of examples of which the novel heat treatment was effected on samples of 7075-T6 aluminum alloys. These are alloys of aluminum containing from 5.1-6.1 per cent zinc, 2.1-2.9% magnesium, 1.22.0% copper, and traces of other ele ments. Such an alloy had first been subjected to a solution heat treatment at a temperature of about 480C, and a subsequent T6 ageing treatment of a temperature of about 121C for about 24 hours. The samples were taken from material in the form of 3 inch thick rolled plate. All testing was carried out in the short transverse direction. Tensile type samples were loaded in tension to a stress corresponding to 75% of their yield point (0.2% proof stress) and subjected to a boiling solution of 6% NaCl in water until rupture occurred.
In the case of 7075-T6 aluminum alloys, it was found that the retrogression treatment is preferably effected from 200 to 260 C for a few seconds to a few minutes. More particularly, the preferred combinations of time and temperature are -120 seconds at 200 C; 15-60 seconds at 220C; 15 seconds at 240C; and 7 seconds at 260 C. The subsequent re-ageing treatment is not as critical with respect to temperature or time, but preferably should be effected at the temperature of 1 15-1 25C for up to several days. In the preferred examples, the re-ageing was effected at 121C for 16-48 hours.
The retrogression heat treatment in the examples described below was carried out in a silicone oil bath in view of the very short time's involved. The samples were then air cooled or water quenched before being subjected to the re-ageing treatment.
The results obtained in a series of tests performed as described above are set-forth in Table 1 below with re- TABLE 1 i What is claimed is:
l. A method of substantially reducing the susceptibil- HEAT TREATMENT* STRESS CORROSION LIFE, HOURS Samples A B C D 1. T6 alone 0.6 0.25 1.55 0.3 2v T6 120 secs/200C.W.Q. 26 35 22.7
16 hours/121C A.C. 3. T6 120 secs/200C A.C. 43.4 26.6
16 hours/121C A.C. 4. T6 120 secs/200C A.C. 16.0 39.0
48 hours/121C A.Cv 5. T6 -1- 15 secs/220C W.Q. 36.25 17.1
48 hours/121C A.C. 6. T6 60 secs/220C A.C. 42.8 31.2
24 hours/121C A.C. 7. T6 15 secs/240CW.Q 22.25 11.45 36.7 17.1
48 hours/121C A.C. 8. T6 15 secs/240C A.C. 31.1 34.8 11.8 74.4
48 hours/121C A.C. 9. T6 7 secs/260C W.Q. 29.4 48 hours/121C A.C.
Note: W1). water quenched; A.C. air cooled TABLE 2 HEAT TREATMENT MECHANICAL PROPERTIES Y.P.,KPS1. U.T.S.,1(PS1 EL.,%
1. T6 alone 70.4 74.1 2.4 2. T6 120 secs/200C W.Q. 69.3 73.8 3.2
16 hours/121C A.C. 3. T6 '1' l secs/220C W.Q. 69.2 73.1 2.4
48 hours/121C A.C. 4. T6 secs/240C W.Q. 68.2 73.1 2.4
48 hours/121C AC. 5. T6 7 secs/260C W.Q. 70.3 74.3 2.4
+ 48 hours/121C A.C.
The depth of the material affected by the novel heat treatment can be controlled by the retrogression conditions employed, the section thickness, and the heating medium. For example, a liquid bath could have effect only on a limited depth of the material, whereas induction heating in the retrogression step could considerably increase the effective depth. The novel heat treatment is therefore particularly adaptable as a users heat treatment to be applied to an article in the final or nearfinal machined conditon.
ity to stress-corrosion cracking of the 7,000 series aluminum alloys containing zinc, magnesium, and copper,
while still retaining their original mechanical strength, i
which alloys have been subjected to a solution heat treatment at a high temperature and then to an aging treatment at a lower temperature thereby hardening the alloy but likewise producing therein a susceptibility to stress-corrosion cracking, comprising the steps of:
a. subjecting the alloy to a retrogression heat treatment for a few seconds to a few minutes at a temperature of from 200C to 260C, which temperature is above the age-hardening temperature of the alloy but below the solution heat treatment temperature; and b. subsequently subjecting the alloy to a re-aging heat treatment at a temperature from C to C for a substantially longer period of time than in step (a) up to several days. 2. The method as defined in claim 1, wherein said alloy is aluminum alloy 7075.

Claims (2)

1. A METHOD OF SUBSTANTIALLY REDUCING THE SUSCEPTIBILITY TO STRESS-CORROSION CRACKING OF THE 7,000 SERIES ALUMINUM ALLOYS CONTAINING ZINC, MAGNESIUM, AND COPPER, WHILE STILL RETAINING THEIR ORIGINAL MECHANICAL STRENGTH, WHILE ALLOYS HAVE BEEN SUBJECTED TO A SOLUTION HEAT TREATMENT AT A HIGH TEMPERATURE AND THEN TO AN AGING TREATMENT AT A LOWER TEMPERATURE THEREBY HARDENING THE ALLOY BUT LIKEWISE PRODUCING THEREIN A SUSCEPTIBILITY TO STRESS-CORROSION CRACKING, COMPRISING THE STEPS OF: A. SUBJECTING THE ALLOY TO A RETROGRESSION HEAT TREATMENT FOR A FEW SECONDS TO A FEW MINUTES AT A TEMPERATURE OF FROM 200*C TO 260*C, WHICH TEMPERATURE IS ABOVE THE AGEHARDENING TEMPERATURE OF THE ALLOY BUT BELOW THE SOLUTION HEAT TREATMENT TEMPERATURE; AND B. SUBSEQUENTLY SUBJECTING THE ALLOY OT A RE-AGING HEAT TREATMENT AT A TEMPERATURE FROM 115*C TO 125*C FOR A SUBSTANTIALLY LONGER PERIOD OF TIME THAN IN STEP (A) UP TO A SEVERAL DAYS.
2. The method as defined in claim 1, wherein said alloy is aluminum alloy 7075.
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US4189334A (en) * 1977-11-21 1980-02-19 Cegedur Societe De Transformation De L'aluminium Pechiney Process for thermal treatment of thin 7000 series aluminum alloys and products obtained
EP0051549A1 (en) * 1980-11-05 1982-05-12 Cegedur Societe De Transformation De L'aluminium Pechiney Interrupted quenching method for aluminium alloys
US4477292A (en) * 1973-10-26 1984-10-16 Aluminum Company Of America Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu 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
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
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
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
FR2762329A1 (en) * 1997-04-18 1998-10-23 Kobe Steel Ltd Aluminium@ alloy of series seven thousand hardened by precipitation and of high resistance
US5948185A (en) * 1997-05-01 1999-09-07 General Motors Corporation Method for improving the hemmability of age-hardenable aluminum sheet
JP2982172B2 (en) 1989-04-14 1999-11-22 日本鋼管株式会社 Heat treatment method for high strength aluminum alloy material
US6033499A (en) * 1998-10-09 2000-03-07 General Motors Corporation Process for stretch forming age-hardened aluminum alloy sheets
US6045636A (en) * 1997-05-15 2000-04-04 General Motors Corporation Method for sliver elimination in shearing aluminum sheet
US20020114990A1 (en) * 2000-08-31 2002-08-22 Fly Gerald W. Fuel cell with variable porosity gas distribution layers
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US20040189049A1 (en) * 2003-03-28 2004-09-30 Krajewski Paul E. Crush zone and method for introducing crush zone into vehicle structure
US20050257865A1 (en) * 2000-12-21 2005-11-24 Chakrabarti Dhruba J Aluminum alloy products having improved property combinations and method for artificially aging same
US7028404B1 (en) 1999-09-09 2006-04-18 Dana Corporation Apparatus and method of manufacturing a vehicle frame assembly
US20080283163A1 (en) * 2007-05-14 2008-11-20 Bray Gary H 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
US20100068090A1 (en) * 2005-02-01 2010-03-18 Timothy Langan Aluminum-zinc-magnesium-scandium alloys and methods of fabricating same
CN101792891A (en) * 2010-04-28 2010-08-04 中南大学 Aging treatment process of Al-Zn-Mg-Cu aluminum alloy
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
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US4477292A (en) * 1973-10-26 1984-10-16 Aluminum Company Of America Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu 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
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
US4189334A (en) * 1977-11-21 1980-02-19 Cegedur Societe De Transformation De L'aluminium Pechiney Process for thermal treatment of thin 7000 series aluminum alloys and products obtained
EP0051549A1 (en) * 1980-11-05 1982-05-12 Cegedur Societe De Transformation De L'aluminium Pechiney Interrupted quenching method for aluminium alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
JP2982172B2 (en) 1989-04-14 1999-11-22 日本鋼管株式会社 Heat treatment method for high strength aluminum alloy material
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
FR2762329A1 (en) * 1997-04-18 1998-10-23 Kobe Steel Ltd Aluminium@ alloy of series seven thousand hardened by precipitation and of high resistance
US6048415A (en) * 1997-04-18 2000-04-11 Kabushiki Kaisha Kobe Seiko Sho High strength heat treatable 7000 series aluminum alloy of excellent corrosion resistance and a method of producing thereof
US5948185A (en) * 1997-05-01 1999-09-07 General Motors Corporation Method for improving the hemmability of age-hardenable aluminum sheet
US6045636A (en) * 1997-05-15 2000-04-04 General Motors Corporation Method for sliver elimination in shearing aluminum sheet
US6033499A (en) * 1998-10-09 2000-03-07 General Motors Corporation Process for stretch forming age-hardened aluminum alloy sheets
US7028404B1 (en) 1999-09-09 2006-04-18 Dana Corporation Apparatus and method of manufacturing a vehicle frame assembly
US20020114990A1 (en) * 2000-08-31 2002-08-22 Fly Gerald W. Fuel cell with variable porosity gas distribution layers
US7592089B2 (en) 2000-08-31 2009-09-22 Gm Global Technology Operations, Inc. Fuel cell with variable porosity gas distribution layers
US8524014B2 (en) 2000-12-21 2013-09-03 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US20050257865A1 (en) * 2000-12-21 2005-11-24 Chakrabarti Dhruba J Aluminum alloy products having improved property combinations and method for artificially aging same
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