EP0723033A1 - Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung - Google Patents

Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung Download PDF

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Publication number
EP0723033A1
EP0723033A1 EP96200060A EP96200060A EP0723033A1 EP 0723033 A1 EP0723033 A1 EP 0723033A1 EP 96200060 A EP96200060 A EP 96200060A EP 96200060 A EP96200060 A EP 96200060A EP 0723033 A1 EP0723033 A1 EP 0723033A1
Authority
EP
European Patent Office
Prior art keywords
thickness
process according
hot rolling
width direction
forging
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.)
Ceased
Application number
EP96200060A
Other languages
English (en)
French (fr)
Inventor
Alfred Johann Peter Dipl.-Ing. Dipl.Oek. Haszler
Alfred Ludwig Dr.-Ing. Heinz
Otmar Martin Dr.-Ing. Muller
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.)
Novelis Koblenz GmbH
Original Assignee
Hoogovens Aluminium Walzprodukte GmbH
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 Hoogovens Aluminium Walzprodukte GmbH filed Critical Hoogovens Aluminium Walzprodukte GmbH
Priority to EP03076928A priority Critical patent/EP1378581A1/de
Priority to EP96200060A priority patent/EP0723033A1/de
Publication of EP0723033A1 publication Critical patent/EP0723033A1/de
Ceased legal-status Critical Current

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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

Definitions

  • the invention relates to a process for manufacturing thick aluminum alloy plate having improved properties comprising the step of hot deformation of an ingot.
  • the invention provides improved fatigue properties as well as improved mechanical properties but will be primarily described in terms of fatigue properties.
  • thick plate will be plate with a thickness of at least 2 inches. It is known in the art that the fatigue properties are reduced at larger gauges. In the present state of the art a thickness of 6 inches is about the limit in which acceptable fatigue properties can be produced.
  • US 5,277,719 discloses that the fatigue properties in a 5.7 inch thick plate can be improved by forging in the thickness direction of the plate with a thickness reduction of at least 30%.
  • a first objection of the invention is to provide a process for manufacturing thick aluminum alloy plate having improved properties.
  • a second object of the invention is to provide thick aluminum alloy plate with a thickness of more than 2 inches having improved properties.
  • a third object of the invention is to newly provide thick aluminum alloy plate with a thickness of more than 6 inches having excellent properties.
  • the hot deformation in the width direction is given in a first step of hot deformation by rolling and the second step of hot deformation comprises forging in the thickness direction.
  • the sequence of the steps of hot deformation of the first embodiment is reversed.
  • the hot deformation may be followed by hot rolling in the length direction.
  • the hot deformation in the width direction is by rolling and the hot deformation by forging in the thickness direction is limited to 30% to allow for a considerable hot deformation in the width direction.
  • the hot deformation in the width direction is, contrary to the first and second embodiment, by forging.
  • the forging in width direction results in a thickness dimension which is larger than the width direction, thereby forming a new width direction being the former thickness direction, and a new width direction being the former thickness direction.
  • the hot rolling may be in the new width direction and may be followed by hot rolling in the length direction.
  • the thickness reduction by hot rolling is in the range of 10 to 50%. In this way, starting from usual ingot dimensions, thick plates of 6" and more are obtained.
  • the invention is embodied in a thick aluminum alloy plate having a thickness in the range of 2-12 inches and having a log-average fatigue life at 35 ksi of at least 150 kcycles and preferably having a log-average fatigue life at 35 ksi of at least 300 kcycles and a thickness in the range of 6-12 inches.
  • the invention is embodied in a thick aluminum alloy plate having a thickness in the range of 2-12 inches and having a fracture toughness in dependency of its thickness as given by the following formula: K Ic T - L ⁇ - 1.2 X G + 31.2 in which K Ic T - L is the fracture toughness in the long transfer direction expressed in ksi inch 0,5 and G is the thickness of the plate expressed in inches.
  • the values for the fracture toughness according to this aspect of the invention are to be found at the right side of the sloped line in Fig. 5.
  • the aluminum alloy of the thick plate is preferably an alloy of the AA 2000 or AA 7000 series. More preferably the alloy is AA 7010, AA 7049, AA 7149, AA 7050, AA 7150, AA 7055, AA 7064, AA 7075, AA 7175, AA 7475, AA 7076, AA 7178. More preferably the alloy contains by weight 5-9% Zn, 0.3-3% Cu, 1-3% Mg, max. 0.4% Si, max. 0.6% Fe, max. 0.5% Mn, max. 0.3% Zr, max. 0.3% Cr., max. 0.3% V, max. 0.3% Nb, max. 0.3% Hf and max. 0.5% Sc.
  • Fig. 1 shows the lifetime of thick plate obtained by various processes in dependency of the thickness of the plate at 35 ksi.
  • Fig. 2 shows the ultimate tensile strength of thick plate obtained by various processes in dependency of the thickness of the plate.
  • Fig. 3 shows the tensile yield strength of thick plate obtained by various processes in dependency of the thickness of the plate.
  • Fig. 4 shows the elongation of the thick plate obtained by various processes in dependency of the thickness of the plate.
  • Fig. 5 shows the fracture toughness of thick plate obtained by various processes in dependency of the thickness of the plate.
  • AA 7050 T 7451 thick plates were manufactured by casting ingots having after scalping and sawing a thickness of about 400 mm, a width in the range of 1070 to 1470 mm and a length in the range of 1700 to 3300 mm, homogenization and preheating prior to hot deformation and solutionizing, quenching, stress relieve and ageing.
  • process no. 1' a thick plate with a thickness of 6.7 inches was manufactured also by hot rolling only. In process no. 1' the measures disclosed in NL 9400939 during casting and hot rolling were applied.
  • a thick plate with a thickness of 8.5 inches was manufactured by firstly hot rolling an ingot in the width direction to an intermediate thickness of 288 mm, cooling to room temperature, reheating and forging in the thickness direction to a final thickness of 8.5 inches.
  • the thickness reduction by forging was less than 30%.
  • a thick plate with a thickness of 8.8 inches was manufactured by firstly forging an ingot in the thickness direction from 400 to 320 mm (thickness reduction about 20%), cooling to room temperature, reheating and hot rolling in the width direction to a thickness of 280 mm (thickness reduction of about 12%) and finally hot rolling in the length direction to a thickness of 8.8 inches.
  • a thick plate with a thickness of 11.0 inches was manufactured by firstly forging an ingot in the width direction from 400 x 1300 (thickness x width) into 800 x 400 (new width x new thickness), cooling to room temperature, reheating and hot rolling in the length direction to a thickness of 11.0 inches.
  • Fig. 1 the lifetime results obtained by applicant at 35 ksi of thick plates manufactured by the processes 1, 1', 2, 3 and 4 are brought together. Symbols relate to the processes mentioned. Fig. 1 contains not only results obtained by the example but also further results for various thicknesses.
  • the log-average values of the conventional process no. 1 shows a sharp breakdown at a thickness of about 6 inches.
  • the horizontal line of process no. 1 at 300 kcycles represents that the tests were terminated at 300 kcycles. Actual values are unknown but are above 300 kcycles as indicated by arrows.
  • the sloped line of process no. 1 might be extrapolated as indicated by the dotted line to represent those unknown values.
  • sloped line representing process 1' in accordance with NL 9400939 represents already a substantial improvement for thick plates up to about 9 inches.
  • Fig. 1 shows clearly improvement of fatigue properties achieved by processes no. 2, 3 and 4 resulting in log-average values of over 300 kcycles at 35 ksi for plates 8.5, 8.8 and 11 inches thick respectively. This means that the decline in lifetime as with processes 1 and 1' is for process 2 beyond a thicknesses of 8.5 inches, and for processes 3 and 4 beyond thicknesses of 8.8 and 11 inches respectively.

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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)
  • Metal Rolling (AREA)
  • Forging (AREA)
EP96200060A 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung Ceased EP0723033A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03076928A EP1378581A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung
EP96200060A EP0723033A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP95200134 1995-01-19
EP95200134 1995-01-20
EP95201243 1995-05-15
EP95201243 1995-05-15
EP96200060A EP0723033A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP03076928A Division EP1378581A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung

Publications (1)

Publication Number Publication Date
EP0723033A1 true EP0723033A1 (de) 1996-07-24

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Family Applications (2)

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EP03076928A Withdrawn EP1378581A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung
EP96200060A Ceased EP0723033A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP03076928A Withdrawn EP1378581A1 (de) 1995-01-19 1996-01-12 Verfahren zur Herstellung eines Grobbleches aus Aluminium-Legierung

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EP (2) EP1378581A1 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000037702A1 (en) * 1998-12-22 2000-06-29 Corus Aluminium Walzprodukte Gmbh Damage tolerant aluminium alloy product and method of its manufacture
US6277219B1 (en) 1998-12-22 2001-08-21 Corus Aluminium Walzprodukte Gmbh Damage tolerant aluminum alloy product and method of its manufacture
FR2823767A1 (fr) * 2001-04-24 2002-10-25 Pechiney Rhenalu Blocs metalliques de forte epaisseur destines a l'usinage
US7323068B2 (en) 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US7494552B2 (en) 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
US7604704B2 (en) 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3137642B2 (de) * 2014-04-30 2022-01-12 Alcoa USA Corp. Verbesserte 7xx-aluminium-gusslegierungen

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2529578A1 (fr) * 1982-07-02 1984-01-06 Cegedur Procede pour ameliorer a la fois la resistance a la fatigue et la tenacite des alliages d'al a haute resistance
US4721537A (en) * 1985-10-15 1988-01-26 Rockwell International Corporation Method of producing a fine grain aluminum alloy using three axes deformation
US5277719A (en) * 1991-04-18 1994-01-11 Aluminum Company Of America Aluminum alloy thick plate product and method

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2529578A1 (fr) * 1982-07-02 1984-01-06 Cegedur Procede pour ameliorer a la fois la resistance a la fatigue et la tenacite des alliages d'al a haute resistance
US4721537A (en) * 1985-10-15 1988-01-26 Rockwell International Corporation Method of producing a fine grain aluminum alloy using three axes deformation
US5277719A (en) * 1991-04-18 1994-01-11 Aluminum Company Of America Aluminum alloy thick plate product and method

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000037702A1 (en) * 1998-12-22 2000-06-29 Corus Aluminium Walzprodukte Gmbh Damage tolerant aluminium alloy product and method of its manufacture
US6277219B1 (en) 1998-12-22 2001-08-21 Corus Aluminium Walzprodukte Gmbh Damage tolerant aluminum alloy product and method of its manufacture
FR2823767A1 (fr) * 2001-04-24 2002-10-25 Pechiney Rhenalu Blocs metalliques de forte epaisseur destines a l'usinage
WO2002085615A1 (en) * 2001-04-24 2002-10-31 Pechiney Rhenalu Metal blocks suitable for machining applications
US6777106B2 (en) 2001-04-24 2004-08-17 Pechiney Rhenalu Metal blocks suitable for machining applications
US7323068B2 (en) 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US7494552B2 (en) 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
US7604704B2 (en) 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
US7815758B2 (en) 2002-08-20 2010-10-19 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy

Also Published As

Publication number Publication date
EP1378581A1 (de) 2004-01-07

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