EP0848073A1 - Stress relieving of an age hardenable aluminium alloy product - Google Patents

Stress relieving of an age hardenable aluminium alloy product Download PDF

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Publication number
EP0848073A1
EP0848073A1 EP97203934A EP97203934A EP0848073A1 EP 0848073 A1 EP0848073 A1 EP 0848073A1 EP 97203934 A EP97203934 A EP 97203934A EP 97203934 A EP97203934 A EP 97203934A EP 0848073 A1 EP0848073 A1 EP 0848073A1
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EP
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Prior art keywords
product
stress
cold
relieving
permanent
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Granted
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EP97203934A
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German (de)
French (fr)
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EP0848073B1 (en
Inventor
Alfred Johann Peter Haszler
Alfred Ludwig Heinz
Otmar Martin Müller
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Novelis Koblenz GmbH
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Hoogovens Aluminium Walzprodukte GmbH
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Priority to EP19970203934 priority Critical patent/EP0848073B1/en
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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
    • 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
    • C22F1/043—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 silicon 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
    • C22F1/053—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
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C21D1/30—Stress-relieving

Definitions

  • the invention relates to a method of stress relieving an age hardenable aluminium alloy product by a permanent cold plastic deformation operation after solution heat treatment and quenching.
  • the invention also relates to a stress relieved product of an age hardenable aluminium alloy, and to uses of such a product.
  • US-A-4294625 for example describes a process in which aluminium alloy is cast, hot worked into plate, solution treated, quenched, pre-aged, cold rolled to reduce thickness by 11 ⁇ 2% and then stretched for stress relieving prior to ageing.
  • the product is for use in aircraft.
  • WO 95/24514 similarly briefly mentions stretching a quenched thick aluminium alloy product to improve flatness and reduce residual stress.
  • JP-A-54-102214 describes manufacture of aluminium alloy pipe or rod with low residual stress, by hardening followed by stretch levelling by 0.5 - 1.0%, then roll levelling and further stretch levelling by 0.5 - 1.0%, followed by tempering at 210 - 250°C for 1 - 2 hours to relieve stress further.
  • GB-A-2025818 discusses manufacture of aluminium alloy rings by hot ring rolling, solution heat treatment, quenching, cold rolling for stress relieving and ageing. The diameter expansion in the cold rolling is 1 to 3%.
  • JP-A-3-2359 describes cold compression of a complex shaped hollow conical billet of aluminium alloy, after solution heat treatment and prior to ageing.
  • JP-A-4-187747 describes two-axis cold compression carried out on an aluminium alloy block of complex shape having insert parts located in apertures.
  • the strength of the stretcher machine may be insufficient to achieve the desired stretching degree. This of course depends not only on the dimensions of the plate but also on the plate alloy or - more precisely - on the flow stress of the plate material in the solutionized and quenched condition.
  • the object of the invention is therefore to provide a method of stress relieving of an age hardenable aluminium alloy product which is especially applicable to alloy product of large cross-section.
  • a method of stress relieving an age hardenable aluminium alloy product after solution heat treatment and quenching comprising applying a permanent cold plastic deformation by the steps of:-
  • the invention provides a method of manufacture of a product of an age hardenable aluminium alloy comprising the steps of:
  • the age hardening may be natural ageing or artificial ageing.
  • the product is a plate product, having length, width and thickness directions, which is stretched in the length direction and compressed in the thickness reduction.
  • the stress relieving permanent deformation by stretching defined as the permanent elongation in the direction of stretching should be not more than 15 %, should more preferably be in the range of 0.3 - 5 %, and most preferably be in the range of 0.5 - 3 %.
  • the stress relieving permanent deformation by compression defined as the permanent reduction in the direction of compression should be in the range of 0.2 - 5 %, and should more preferably be in the range of 0.5 - 3 %.
  • the cold compression may be given by forging, e.g. by a forging tool in overlapping steps.
  • the stress relieving stretching of the product preferably takes place before the compression.
  • the deformation is preferably given before substantially any age hardening after quenching.
  • Full advantage of the invention is obtained when the product is a thick plate having a final thickness of 2 inches (5cm) or more, preferably 4 inches (10cm) or more and most preferably 6 inches (15cm) or more.
  • the invention is particularly effective in meeting requirements of strength and toughness properties and distortion when the aluminium alloy belongs to the Aluminium Association AA 2XXX, the AA 6XXX or the AA 7XXX series.
  • the invention also consists in the product of the method of the invention described above.
  • the invention provides a product made of an age hardenable aluminium alloy suitable for use in an aircraft construction and being stress relieved after solution heat treatment and quenching by a combination of a cold mechanical stretching and a cold compression, having in the age hardened condition, as compared with a product which has been stress relieved by said cold mechanical stretching only but has otherwise the same manufacturing history, similar strength and toughness properties and an improved property of distortion after machining.
  • the invention provides a product made of an age hardenable aluminium alloy suitable for use in one of a tooling construction and a moulding construction and being stress relieved after solution heat treatment and quenching by a combination of a cold mechanical stretching and a cold compression, having in the age hardened condition, as compared with a product which has been stress relieved by said cold compression only but has otherwise the same manufacturing history, improved strength and toughness properties and a similar property of distortion after machining.
  • the distortion after machining is less than 50 ⁇ m.
  • L, S, T, LT, L-T, etc. denote the testing directions in accordance with ASTM E399.
  • Tensile testing was performed in accordance with ASTM E8 and ASTM B557.
  • TYS is tensile yield strength.
  • UTS is ultimate tensile strength.
  • a 4d is elongation at fracture for a round tensile specimen with a gauge length of four times diameter.
  • Fracture toughness testing for K Ic values was performed according to ASTM B645 and ASTM E399. Machining distortion testing was carried out in accordance with Boeing Materials Specification BMS 7-323B, para. 8.6 and Figs. 4 and 5.
  • Table 2 gives the deformation degrees and the results of tests on the products.
  • Property Cold deformation cold compressed 1.6 - 1.9 % stretched 0.6 - 0.7 % and cold compressed 0.9 - 1.1 % tension L T/4 TYS [MPa] 421 431 UTS [MPa] 498 505 A 4d [%] 11.0 9.5 tension LT, T/4 TYS [MPa] 420 421 UTS [MPa] 491 493 A 4d [%] 10.0 10.9 tension ST, T/2 TYS [MPa] 375 382 UTS [MPa] 480 485 A 4d [%] 7.0 5.7 K Ic L-T, T/4 [MPa m 0.5 ] 26.2 27.7 K Ic T-L, T/4 [MPa m 0.5 ] 26.1 27.2 K Ic S-L, T/2 [MPa m 0.5 ] 21.6 24.2 Machining distortion [10 -6 m] 50 50

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Forging (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)

Abstract

Stress relieving of an age hardenable aluminium alloy product after solution heat treatment and quenching, is carried out by a permanent cold plastic deformation applied by the steps of:-
  • (a) applying a stress-relieving cold mechanical stretch to said product, and
  • (b) applying a stress-relieving cold compression to said product.
    • This combined treatment gives improved strength and toughness and at least comparable distortion after machining.

    Description

    BACKGROUND OF THE INVENTION 1. FIELD OF THE INVENTION
    The invention relates to a method of stress relieving an age hardenable aluminium alloy product by a permanent cold plastic deformation operation after solution heat treatment and quenching. The invention also relates to a stress relieved product of an age hardenable aluminium alloy, and to uses of such a product.
    2. DESCRIPTION OF THE PRIOR ART
    Manufacture of age hardenable aluminium alloy products requires solution heat treatment and quenching of the product. Since residual stresses due to the quenching operation do not allow for machining operations without simultaneous distortion of the machined parts, the products are stress relieved. In case of flat products (e.g. rolled plate) this has been accomplished by a stretching operation using a permanent plastic deformation of a few percent of the original dimension. Usually this stretching is done in the length direction which is normally also the rolling direction.
    US-A-4294625 for example describes a process in which aluminium alloy is cast, hot worked into plate, solution treated, quenched, pre-aged, cold rolled to reduce thickness by 11 ± 2% and then stretched for stress relieving prior to ageing. The product is for use in aircraft. WO 95/24514 similarly briefly mentions stretching a quenched thick aluminium alloy product to improve flatness and reduce residual stress. JP-A-54-102214 describes manufacture of aluminium alloy pipe or rod with low residual stress, by hardening followed by stretch levelling by 0.5 - 1.0%, then roll levelling and further stretch levelling by 0.5 - 1.0%, followed by tempering at 210 - 250°C for 1 - 2 hours to relieve stress further.
    It has also been proposed to employ cold compression as a stress-relieving step. GB-A-2025818 discusses manufacture of aluminium alloy rings by hot ring rolling, solution heat treatment, quenching, cold rolling for stress relieving and ageing. The diameter expansion in the cold rolling is 1 to 3%. Similarly JP-A-3-2359 describes cold compression of a complex shaped hollow conical billet of aluminium alloy, after solution heat treatment and prior to ageing. JP-A-4-187747 describes two-axis cold compression carried out on an aluminium alloy block of complex shape having insert parts located in apertures.
    In conventional cold stretching, if the cross-section of the product (plate) is large (e.g. very thick or very wide plate) the strength of the stretcher machine may be insufficient to achieve the desired stretching degree. This of course depends not only on the dimensions of the plate but also on the plate alloy or - more precisely - on the flow stress of the plate material in the solutionized and quenched condition.
    SUMMARY OF THE INVENTION
    The object of the invention is therefore to provide a method of stress relieving of an age hardenable aluminium alloy product which is especially applicable to alloy product of large cross-section.
    According to the invention in one aspect there is provided a method of stress relieving an age hardenable aluminium alloy product after solution heat treatment and quenching, comprising applying a permanent cold plastic deformation by the steps of:-
  • (a) applying a stress-relieving cold mechanical stretch to the product, and
  • (b) applying a stress-relieving cold compression to the product.
    • In another aspect, the invention provides a method of manufacture of a product of an age hardenable aluminium alloy comprising the steps of:
  • (i) casting said age hardenable alloy
  • (ii) shaping the cast alloy to form a shaped product
  • (iii) solution heat treating said shaped product
  • (iv) quenching the solution heat treated product
  • (v) performing stress relieving of the quenched product by applying a permanent cold plastic deformation by the steps of
  • (a) applying a stress-relieving cold mechanical stretch to said product, and
  • (b) applying a stress-relieving cold compression to said product.
    • In this method, the age hardening may be natural ageing or artificial ageing.
    In a preferred embodiment the product is a plate product, having length, width and thickness directions, which is stretched in the length direction and compressed in the thickness reduction.
    It has been found, as will be shown below, that replacement of the conventional mechanical stretching as a stress relieving method by cold compression alone results in loss of strength and toughness properties of the final product, although distortion after machining is improved. By applying combined stretching and compression the loss of properties is recovered while at the same time the improved distortion is retained.
    To obtain full advantage of the invention the stress relieving permanent deformation by stretching, defined as the permanent elongation in the direction of stretching should be not more than 15 %, should more preferably be in the range of 0.3 - 5 %, and most preferably be in the range of 0.5 - 3 %.
    Similarly preferably the stress relieving permanent deformation by compression, defined as the permanent reduction in the direction of compression should be in the range of 0.2 - 5 %, and should more preferably be in the range of 0.5 - 3 %.
    In practice the cold compression may be given by forging, e.g. by a forging tool in overlapping steps. The stress relieving stretching of the product preferably takes place before the compression. The deformation is preferably given before substantially any age hardening after quenching.
    Full advantage of the invention is obtained when the product is a thick plate having a final thickness of 2 inches (5cm) or more, preferably 4 inches (10cm) or more and most preferably 6 inches (15cm) or more.
    The invention is particularly effective in meeting requirements of strength and toughness properties and distortion when the aluminium alloy belongs to the Aluminium Association AA 2XXX, the AA 6XXX or the AA 7XXX series.
    The invention also consists in the product of the method of the invention described above.
    In another aspect the invention provides a product made of an age hardenable aluminium alloy suitable for use in an aircraft construction and being stress relieved after solution heat treatment and quenching by a combination of a cold mechanical stretching and a cold compression, having in the age hardened condition, as compared with a product which has been stress relieved by said cold mechanical stretching only but has otherwise the same manufacturing history, similar strength and toughness properties and an improved property of distortion after machining.
    In still another aspect the invention provides a product made of an age hardenable aluminium alloy suitable for use in one of a tooling construction and a moulding construction and being stress relieved after solution heat treatment and quenching by a combination of a cold mechanical stretching and a cold compression, having in the age hardened condition, as compared with a product which has been stress relieved by said cold compression only but has otherwise the same manufacturing history, improved strength and toughness properties and a similar property of distortion after machining.
    Preferably the distortion after machining is less than 50µm.
    DESCRIPTION OF PREFERRED EMBODIMENTS
    An example of the invention and comparative examples will now be described, but the invention is not limited to the particular example given.
    Experiment 1 (Comparative)
    There were manufactured two 6 inch (15cm) plates of the aluminium alloy AA 7050 T 745X by casting, homogenizing, hot rolling, solution heat treating and quenching, stress relieving (immediately after quenching) and age hardening. The manufacturing procedure for both plates was the same except for the stress relieving which for one plate was executed by a conventional mechanical stretching in the length direction of the plate and for the other plate by cold compression. The cold compression was performed in the through thickness direction in order to achieve a stress relieved or stress reduced material. The compression was performed using a forging press. Because the product (plate) was much longer than the forging tool the cold compression operation was performed in a number of steps with an overlapping zone in each step in order to guarantee that the entire volume of the product was compressed and therefore stress relieved or stress reduced.
    The two plates were tested. The amount of cold deformation and the test results are shown in Table 1.
    Property Cold deformation
    Stretching 1.9 - 2.0% Compression 2.2 - 2.4%
    Tensile L, s/4 TYS [MPa] 460 445
    UTS [MPa] 513 510
    A4d [%] 10.7 10.3
    Tensile LT, s/4 TYS [MPa] 456 451
    UTS [MPa] 521 516
    A4d [%] 7.7 8.1
    Tensile ST, s/2 TYS [MPa] 424 401
    UTS [MPa] 490 487
    A4d [%] 4.0 4.1
    KIc L-T, s/4 [MPa m0.5] 28.33 28.34
    KIc T-L, s/4 [MPa m0.5] 24.41 23.67
    KIc S-L, s/2 [MPa m0.5] 24.22 24.0
    Machining distortion [10-6m] 70 - 100 40 - 50
    L, S, T, LT, L-T, etc. denote the testing directions in accordance with ASTM E399. Tensile testing was performed in accordance with ASTM E8 and ASTM B557. TYS is tensile yield strength. UTS is ultimate tensile strength. A4d is elongation at fracture for a round tensile specimen with a gauge length of four times diameter. Fracture toughness testing for KIc values was performed according to ASTM B645 and ASTM E399. Machining distortion testing was carried out in accordance with Boeing Materials Specification BMS 7-323B, para. 8.6 and Figs. 4 and 5.
    This experiment shows that the cold compression results in lower distortion after machining when compared to stretched material of same history and similar level of cold deformation. At the same time it was found that the cold compressed material has a lower tensile strength both in the direction of cold compression (the thickness direction) and in the length direction. This at best results in a narrow manufacturing window to obtain the required properties.
    Experiment 2
    This includes another comparative example and an example of the invention.
    Two identical plates similar to those used in Experiment 1 (same alloy) were made by the same procedure as in Experiment 1 except that their thickness was 8.6 inches (21.8cm) and that the stress relieving for one plate was a cold compression in the thickness direction only and for the other plate a combination of mechanical stretching in the length direction and cold forging in the thickness direction.
    Table 2 gives the deformation degrees and the results of tests on the products.
    Property Cold deformation
    cold compressed 1.6 - 1.9 % stretched 0.6 - 0.7 % and cold compressed 0.9 - 1.1 %
    tension L, T/4 TYS [MPa] 421 431
    UTS [MPa] 498 505
    A4d [%] 11.0 9.5
    tension LT, T/4 TYS [MPa] 420 421
    UTS [MPa] 491 493
    A4d [%] 10.0 10.9
    tension ST, T/2 TYS [MPa] 375 382
    UTS [MPa] 480 485
    A4d [%] 7.0 5.7
    KIc L-T, T/4 [MPa m0.5] 26.2 27.7
    KIc T-L, T/4 [MPa m0.5] 26.1 27.2
    KIc S-L, T/2 [MPa m0.5] 21.6 24.2
    Machining distortion [10-6m] 50 50
    The loss in strength experienced with a cold compression alone was avoided by the combined process both for the L and the ST testing direction. Surprisingly it was found also that the toughness level of the combined stretched/cold compressed material was much better as compared to the product cold compressed only. This effect is more pronounced for the S-L than for the T-L and the L-T testing direction. The degree of distortion after machining is virtually the same for the two different processes. Therefore the process of invention permits manufacture of large cross-sections (wide and thick) of high strength age hardenable alloys with an improved property combination with respect to strength and toughness and simultaneously a similar level of distortion after machining when compared to the material which is cold compressed only, but otherwise has the same manufacturing history.

    Claims (16)

    1. Method of stress relieving an age hardenable aluminium alloy product after solution heat treatment and quenching, comprising applying a permanent cold plastic deformation,
         characterised in that said permanent cold plastic deformation is obtained by the steps of:-
      (a) applying a stress-relieving cold mechanical stretch to said product, and
      (b) applying a stress-relieving cold compression to said product.
    2. Method of manufacture of a product of an age hardenable aluminium alloy comprising the steps of:
      (i) casting said age hardenable alloy
      (ii) shaping said cast alloy to form a shaped product
      (iii) solution heat treating said shaped product
      (iv) quenching the solution heat treated product
      (v) performing stress relieving of said quenched product by applying a permanent cold plastic deformation,
         characterised in that said stress relieving is performed by the steps of:-
      (a) applying a stress-relieving cold mechanical stretch to said product, and
      (b) applying a stress-relieving cold compression to said product.
    3. Method according to claim 1 or 2, wherein said step (a) is performed before said step (b).
    4. Method according to any one of claims 1 to 3, wherein said steps (a) and (b) are performed substantially before age hardening has taken place following the quenching.
    5. Method according to any one of claims 1 to 4, wherein said product is a plate having a length direction, a width direction and a thickness direction, said mechanical stretch being applied in said length direction and said compression being applied in said thickness direction.
    6. Method according to any one of claims 1 to 5, wherein permanent deformation in said step (a), defined as the permanent elongation in the direction of stretching, is not more than 15 %.
    7. Method according to claim 6, wherein said permanent deformation in step (a) is in the range 0.3 - 5%.
    8. Method according to claim 7, wherein said permanent deformation in step (a) is in the range 0.5 - 3 %.
    9. Method according to any one of claims 1 to 8, wherein permanent deformation in said step (b), defined as the permanent reduction in the direction of compression, is in the range 0.2 - 5 %.
    10. Method according to claim 9, wherein said permanent deformation in step (b) is in the range 0.5 - 3 %.
    11. Method according to any one of claims 1 to 10, wherein in step (b) said cold compression is applied by a forging tool in overlapping steps.
    12. Method according to any one of claims 1 to 11, in which the product is a thick plate having a final thickness of at least 2 inches (5cm).
    13. Method according to claim 12, wherein said final thickness is at least 4 inches (10cm).
    14. Method according to claim 13, wherein said final thickness is at least 6 inches (15cm).
    15. Method according to any one of claims 1 to 14, wherein the aluminium alloy of said product belongs to one of the AA 2XXX, AA 6XXX and AA 7XXX series.
    16. Use of a product made by the method of any one of claims 1 to 15 in an aircraft construction, a tooling construction or a moulding construction.
    EP19970203934 1996-12-16 1997-12-15 Stress relieving of an age hardenable aluminium alloy product Expired - Lifetime EP0848073B1 (en)

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    EP96203563 1996-12-16
    EP96203563 1996-12-16
    EP19970203934 EP0848073B1 (en) 1996-12-16 1997-12-15 Stress relieving of an age hardenable aluminium alloy product

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    EP0848073A1 true EP0848073A1 (en) 1998-06-17
    EP0848073B1 EP0848073B1 (en) 2002-05-08

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    Cited By (8)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    DE19956895C1 (en) * 1999-11-26 2000-11-16 Daimler Chrysler Ag Stress relieving aluminum alloy cylinder head casting, by plastic deformation to create elastic compressive stress in shaft regions facing combustion chambers
    WO2002010482A2 (en) * 2000-08-01 2002-02-07 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'vserossiysky Nauchno-Issledovatelsky Institut Aviatsionnykh Materialov' Method for producing half-finished products made of aluminium alloys and an article manufactured with the aid of said method
    FR2879217A1 (en) * 2004-12-13 2006-06-16 Pechiney Rhenalu Sa STRONG ALLOY SHEETS AI-ZN-CU-MG WITH LOW INTERNAL CONSTRAINTS
    EP1059363B2 (en) † 1999-06-10 2010-11-03 Hydro Aluminium Deutschland GmbH Method for process integrated heat treatment
    CN102528397A (en) * 2012-01-31 2012-07-04 西南铝业（集团）有限责任公司 Method for producing aluminium alloy row material used for shoe mold
    WO2015002177A1 (en) * 2013-07-04 2015-01-08 昭和電工株式会社 Method for producing starting material for cutting
    CN111218629A (en) * 2020-02-28 2020-06-02 株洲中车天力锻业有限公司 High section of thick bamboo aluminum alloy ring destressing device
    CN111455295A (en) * 2020-04-24 2020-07-28 西北工业大学 Stress aging heat treatment process for titanium alloy

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    GB2025818A (en) * 1978-07-19 1980-01-30 Doncaster & Sons Ltd D Method of Producing Rings from Aluminium-based Alloys
    US4294625A (en) * 1978-12-29 1981-10-13 The Boeing Company Aluminum alloy products and methods
    JPH032359A (en) * 1989-05-26 1991-01-08 Nissan Motor Co Ltd Production of flanged cylindrical member
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    Cited By (13)

    * Cited by examiner, † Cited by third party
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    EP1059363B2 (en) † 1999-06-10 2010-11-03 Hydro Aluminium Deutschland GmbH Method for process integrated heat treatment
    DE19956895C1 (en) * 1999-11-26 2000-11-16 Daimler Chrysler Ag Stress relieving aluminum alloy cylinder head casting, by plastic deformation to create elastic compressive stress in shaft regions facing combustion chambers
    WO2002010482A2 (en) * 2000-08-01 2002-02-07 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'vserossiysky Nauchno-Issledovatelsky Institut Aviatsionnykh Materialov' Method for producing half-finished products made of aluminium alloys and an article manufactured with the aid of said method
    WO2002010482A3 (en) * 2000-08-01 2002-09-26 Federalnoe G Unitarnoe Predpr Method for producing half-finished products made of aluminium alloys and an article manufactured with the aid of said method
    EP1838891B1 (en) 2004-12-13 2015-12-09 Constellium Issoire High strength sheet made from al-zn-cu-mg alloy with low internal stresses
    FR2879217A1 (en) * 2004-12-13 2006-06-16 Pechiney Rhenalu Sa STRONG ALLOY SHEETS AI-ZN-CU-MG WITH LOW INTERNAL CONSTRAINTS
    WO2006064113A1 (en) * 2004-12-13 2006-06-22 Alcan Rhenalu High strength sheet made from al-zn-cu-mg alloy with low internal stresses
    CN102528397A (en) * 2012-01-31 2012-07-04 西南铝业（集团）有限责任公司 Method for producing aluminium alloy row material used for shoe mold
    WO2015002177A1 (en) * 2013-07-04 2015-01-08 昭和電工株式会社 Method for producing starting material for cutting
    JPWO2015002177A1 (en) * 2013-07-04 2017-02-23 昭和電工株式会社 Manufacturing method of cutting material
    CN111218629A (en) * 2020-02-28 2020-06-02 株洲中车天力锻业有限公司 High section of thick bamboo aluminum alloy ring destressing device
    CN111218629B (en) * 2020-02-28 2024-02-09 株洲中车天力锻业有限公司 High section of thick bamboo aluminum alloy ring destressing device
    CN111455295A (en) * 2020-04-24 2020-07-28 西北工业大学 Stress aging heat treatment process for titanium alloy

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