EP1492895A2 - Pprodukte aus al-zn-mg-cu-legierung - Google Patents

Pprodukte aus al-zn-mg-cu-legierung

Info

Publication number
EP1492895A2
EP1492895A2 EP03740568A EP03740568A EP1492895A2 EP 1492895 A2 EP1492895 A2 EP 1492895A2 EP 03740568 A EP03740568 A EP 03740568A EP 03740568 A EP03740568 A EP 03740568A EP 1492895 A2 EP1492895 A2 EP 1492895A2
Authority
EP
European Patent Office
Prior art keywords
content
product according
elements
product
alloy
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.)
Granted
Application number
EP03740568A
Other languages
English (en)
French (fr)
Other versions
EP1492895B1 (de
Inventor
Timothy Warner
Christophe Sigli
Bernard Bes
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.)
Constellium Issoire SAS
Original Assignee
Pechiney Rhenalu SAS
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Filing date
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Application filed by Pechiney Rhenalu SAS filed Critical Pechiney Rhenalu SAS
Publication of EP1492895A2 publication Critical patent/EP1492895A2/de
Application granted granted Critical
Publication of EP1492895B1 publication Critical patent/EP1492895B1/de
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

Links

Classifications

    • 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
    • C22F1/053—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 present invention relates to Al-Zn-Mg-Cu alloys with compromise static mechanical characteristics - improved damage tolerance, with a Zn content greater than 8.3%, as well as structural elements for aeronautical construction incorporating half wrought products made from these alloys.
  • Alloys of the Al-Zn-Mg-Cu type (belonging to the family of 7xxx alloys) are commonly used in aeronautical construction, and in particular in the construction of the wings of civil aircraft.
  • These alloy designations well known to those skilled in the art. trade, correspond to those of The Aluminum Association.
  • alloys 7075 and 7175 have been known for decades, such as alloys 7075 and 7175 (zinc content between 5.1 and 6.1% by weight), 7050 (zinc content between 5.7 and 6.7%) , 7150 (zinc content between 5.9 and 6.9%) and 7049 (zinc content between 7.2 and 8.2%). They have a high elastic limit, as well as good toughness and good resistance to stress corrosion and exfoliating corrosion. More recently, it has become apparent that for certain applications, the use of an alloy with a higher zinc content may have advantages since this makes it possible to further increase the elastic limit. Alloys 7349 and 7449 contain between 7.5 and 8.7% zinc. of the wrought alloys richer in zinc have been described in the literature, but do not seem to be used in aeronautical construction.
  • EP 257 167 Al (German Métallurgique de Gerzat) notes that none of the known Al-Zn-Mg-Cu type alloys can safely and reproducibly meet the severe technical requirements imposed by this specific application; it proposes to move towards a lower zinc content, namely between 6.25% and 8.0%.
  • the problem to which the present invention is trying to respond is therefore to propose new wrought products of Al-Zn-Mg-Cu type alloy with high zinc content, greater than 8.3%, which are characterized by an improved compromise between toughness and static mechanical characteristics (yield strength, yield strength), which have sufficient corrosion resistance and high elongation at break, and which can be manufactured industrially under conditions of reliability compatible with the high requirements of the industry aeronautics.
  • a first object of the present invention consists of a rolled, extruded or forged product of Al-Zn-Mg-Cu alloy, characterized in that it contains (in percent by mass): a) Zn 8.3 - 14.0 Cu 0.3 - 4.0 and preferably 0.3 - 3.0 Mg 0.5 - 4.5 and preferably 0.5 - 3.0 Zr 0.03 - 0.15 Fe + Si ⁇ 0.25 b ) at least one element selected from the group consisting of Se, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, the content of each of said elements, if it is selected, being between 0.02 and 0.7%, c) the remainder of aluminum and inevitable impurities, and in that it satisfies the conditions
  • a second object of the present invention consists of a rolled, extruded or forged product of Al-Zn-Mg-Cu alloy, characterized in that it contains (in percent by mass): a) Zn 9.5 - 14.0 Cu 0.3 - 4.0 and preferably 0.3 - 3.0 Mg 0.5 - 4.5 and preferably 0.5 - 3.0
  • Fe + Si ⁇ 0.25 b) at least one element selected from the group consisting of Zr, Se, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, Cr , Mn, the content of each of said elements, if selected, being between 0.02 and 0.7%, c) the rest of the aluminum and inevitable impurities, and in that it satisfies the conditions d) Mg / Cu ⁇ 2.4 and e) (7.7 - 0.4 Zn)> (Cu + Mg)> (6.4 - 0.4 Zn).
  • a third object of the present invention is a structural element for aeronautical construction which incorporates one of the said products, and in particular a structural element used in the construction of wing boxes of civil aircraft, such as a wing upper surface.
  • Figure 1 schematically shows a wing box of an aircraft.
  • the benchmarks are as follows:
  • FIG. 2 represents the compromise between mechanical strength and damage tolerance in a diagram R p o, 2 - K app for the alloys of example 3.
  • FIG. 3 represents the compromise between mechanical strength and damage tolerance in a diagram R p o > 2 - K app for the alloys of example 5.
  • the parameter K app was measured according to the ASTM E561 standard on CT type testpieces of width W equal to 127 mm.
  • the term “spun product” includes so-called “drawn products”, that is to say products which are produced by spinning followed by drawing. The applicant, in the course of a number of preparatory studies, has come to the conclusion that a new material presenting a significantly better compromise should in any event have a sufficient zinc content, typically greater than approximately 8.3 %. This condition is however not sufficient.
  • the problem is solved by fine adjustment of the contents of the alloying elements and certain impurities, and by adding a controlled concentration of certain other elements to the composition of the alloy.
  • the present invention applies to Al-Zn-Mg-Cu alloys containing:
  • the alloys according to the invention must contain at least 0.5% magnesium, since it is not possible to obtain satisfactory static mechanical characteristics with a lower magnesium content. According to the Applicant's observations, with a zinc content of less than 8.3%, no result is obtained which is better than those obtained with known alloys.
  • the zinc content is greater than 9.0%, and even more preferably greater than 9.5%. However, it is necessary to respect certain relationships between certain elements, as explained below.
  • the zinc content is between 9.0 and 11.0%. In any event, it is not desired to exceed a zinc content of approximately 14%, because above this value, whatever the magnesium and copper content, the results are not satisfactory.
  • the alloy must be sufficiently loaded with addition elements capable of precipitating during maturation or tempering treatment, in order to be able to exhibit advantageous static mechanical characteristics.
  • addition elements capable of precipitating during maturation or tempering treatment, in order to be able to exhibit advantageous static mechanical characteristics.
  • the content of these addition elements must fulfill the condition Mg + Cu> 6.4 - 0.4 Zn.
  • anti-recrystallizing elements More specifically, for alloys with more than 9.5% zinc, at least one element selected from the group comprising the elements Zr, Se, Hf, La, Ti, Y, Ce, Nd, Eu, Gd, must be added. Tb, Dy, Ho, Er, Yb, Cr, Mn with, for each element present, a concentration of between 0.02 and 0.7%. It is preferable that the concentration of all the elements of said group does not exceed 1.5%.
  • zirconium with a content of between 0.03% and 0.15%, and in addition at least an element selected from the group comprising the elements Se, Hf, La, Ti, Y, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Yb, with, for each element present, a concentration of between 0, 02 and 0.7%.
  • the said anti-recrystallizing elements it is advantageous, whatever the zinc content, not to exceed the following maximum contents: Cr 0.40; Mn 0.60; Se 0.50; Zr 0.15; Hf 0.60; Ti 0.15; This 0.35 and preferably 0.30; Nd 0.35 and preferably 0.30; Eu 0.35 and preferably 0.30; Gd 0.35; Tb 0.35; Ho 0.40; Dy 0.40; Er 0.40; Yb 0.40; Y 0.20; The 0.35 and preferably 0.30.
  • the total of these elements does not exceed 1.5%.
  • This criterion is called in the context of the present invention the "flowability criterion".
  • the alloys produced according to this variant of the invention complete their solidification at a temperature of between 473 ° C and 478 ° C, and make it possible to achieve industrial reliability in the processes for preparing the metal (that is to say a consistency of the quality of the cast plates) compatible with the high requirements of the aeronautical industry.
  • Another technical characteristic of the invention is linked to the need to minimize as much as possible the amount of insoluble precipitates after the homogenization and dissolution treatments, since this reduces the toughness; for this, we choose a content of Mg, Cu and Zn such that Mg + Cu ⁇ 7.7 - 0.4 Zn. Said precipitates are typically ternary or quaternary Al-Zn-Mg-Cu phases of type S, M or T. And finally, the Applicant has found that the incorporation of a small amount, between 0.02 and 0.15% per element, of one or more elements chosen from the group composed of Sn, Cd, Ag, Ge, In improves the response of the alloy to the tempering treatment, and has beneficial effects on the mechanical strength and on the corrosion resistance of the product. A content of between 0.05 and 0.10% is preferred. Among these elements, money is the preferred element.
  • the products according to the invention are in particular laminated or extruded products. They can be advantageously used for the manufacture of structural elements in aircraft construction.
  • a preferred application of the products according to the invention is the application as a structural element in a wing box, and in particular in its upper part (upper surface) which is first of all dimensioned in resistance to compression.
  • Figure 1 schematically shows a section of the wing box of a civil aircraft.
  • a wing box typically has a length of between 10 m and 40 m and a width of between 2 m and 10 m; its height varies depending on the location on the wing and is typically between 0.2 m and 2 m.
  • the box consists of the upper surface (1) and the lower surface (2).
  • the upper surface (1) of a civil aircraft consists of a heavy plate of a typical thickness during delivery of between 15 mm and 60 mm, and stiffeners (5) which can be made from profiles and attached to the skin using mechanical fasteners (such as rivets or bolts) or by welding techniques (such as arc welding, laser beam welding, or friction welding).
  • the upper surface structure can also be obtained by assembling other semi-products of aluminum alloy. It can also be obtained by integral machining of heavy plates or profiles, that is to say without assembly.
  • the length of aircraft wings can exceed 20 m and even 30 m, which requires the use of sheets or profiles longer than 20 m or 30 m, in order to minimize assembly of structural elements.
  • the manufacture of sheets or profiles of such a size from highly loaded Al-Zn-Mg-Cu alloys requires excellent mastery of the casting, rolling and thermal and thermo-mechanical treatment processes, and requires an adaptation of the chemical composition according to the invention.
  • the products according to the invention can be used as structural elements in aeronautical construction.
  • a metallurgical state of type T6, for example T651 is preferred.
  • the product according to the invention is particularly suitable for use as a structural element in a wing box, for example in the form of an upper surface or a stiffener.
  • the advantages of the products according to the invention allow in particular their use as structural elements of very large planes, in particular of civil planes, and in particular in the form of rolled and spun products. In a particularly advantageous application, these structural elements are manufactured from sheets of thickness greater than 60 mm.
  • the addition of one or more anti-recrystallizing elements, such as scandium, is particularly advantageous; such an effect is also observed in the case of heavy plates.
  • the anti-recrystallizing element added is scandium, a content of between 0.02 and 0.50% is advantageous.
  • Adding a small amount of silver or other element such as Cd, Ge, In, Sn improves the efficiency of income, and a positive effects on the mechanical resistance and resistance to corrosion under stress of the product.
  • Alloy A is an alloy 7449 according to the state of the art
  • alloys B and C are alloys with a high content of Zn, not respecting the technical characteristics of the invention
  • alloy D is an alloy according to l 'invention.
  • alloy according to the invention has a better compromise between static characteristics and toughness than alloy 7449 according to the prior art (R p02 in higher tension and compression and K ⁇ similar), and that the alloys with high zinc content not respecting the technical characteristics of the invention are less efficient.
  • Alloy E is an alloy 7449
  • alloy F is an alloy according to the invention, containing an addition of 0.083% of Scandium.
  • Alloy R is an alloy 7449
  • alloy S is an alloy according to the invention, containing an addition of 0.078% of scandium.
  • the toughness in plane deformation Kic was determined according to standard ASTM E399, at mid-thickness.
  • the toughness under plane stresses was characterized at mid-thickness using the parameter K app , measured according to standard ASTM E561 on CCT type test pieces of width W equal to 406 mm.
  • the results of the toughness measurements carried out during this test are presented in Table 8 below.
  • FIG. 2 The compromise between mechanical strength and damage tolerance is shown in FIG. 2 in a diagram R p0> 2 - K app for the alloys of example 3.
  • the reference alloy “R” presents the usual compromise (the toughness decreases when the mechanical resistance increases).
  • the alloy according to the invention “S” exhibits a very slight decrease (thickness 10 mm) or even a clear increase (thickness 25 mm) in toughness when the mechanical strength increases.
  • the alloy according to the invention has levels of mechanical resistance clearly higher than those of the reference alloy and a comparable or even higher toughness.
  • the alloys G1, G2, G3 and G4 are outside the present invention, as well as the alloys B and C, described in example 1.
  • the alloy D is an alloy according to the invention described in example 1. All of these alloys showed satisfactory flowability during the tests, that is to say that cracks or cracks were not observed during the casting tests on an industrial scale.
  • the alloys G5, G6, G7, G8 are outside the present invention, and the alloy G9 is an alloy 7060 according to the state of the art; these alloys presented cracks during the casting tests.
  • Lamination plates were produced by a process similar to that described in Example 1.
  • the chemical composition is given in Table 10.
  • it was prepared by hot rolling sheets with a thickness of 25 mm. They were dissolved for 2 hours at a temperature between 472 and 480 ° C. (these temperatures are determined by preliminary calorimetry tests on the raw rolling sheets, a standard procedure for those skilled in the art), quenched by spraying and pulled with a permanent elongation between 1, 5 and 2%. Then, the sheets were subjected to a tempering treatment at a temperature of 135 ° C.
  • the K sheet with a lower Mg / Cu ratio shows significantly better toughness values than the N sheet.
  • Spinning billets 291 mm in diameter were prepared by vertical casting with an alloy according to the invention, the composition of which is given in table 12.
  • the homogenized (7h 460 ° C + 23h 466 ° C) and peeled billets were extradited, the temperature of the container and the tool being greater than 400 ° C, and the spinning speed being less than 0.50 m / min .
  • the geometry of the profiles includes a sole (thickness 15 mm, width 152 mm), a rib (thickness 15 mm, height 38 mm) and a reinforcement (thickness 23 mm, width 76 mm).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Heat Treatment Of Steel (AREA)
  • Conductive Materials (AREA)
  • Laminated Bodies (AREA)
  • Extrusion Of Metal (AREA)
  • Metal Rolling (AREA)
  • Forging (AREA)
  • Contacts (AREA)
EP03740568A 2002-04-05 2003-04-04 Produkte aus al-zn-mg-cu-legierung Revoked EP1492895B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0204257A FR2838136B1 (fr) 2002-04-05 2002-04-05 PRODUITS EN ALLIAGE A1-Zn-Mg-Cu A COMPROMIS CARACTERISTIQUES STATISTIQUES/TOLERANCE AUX DOMMAGES AMELIORE
FR0204257 2002-04-05
PCT/FR2003/001062 WO2003085145A2 (fr) 2002-04-05 2003-04-04 Produits en alliages al-zn-mg- cu

Publications (2)

Publication Number Publication Date
EP1492895A2 true EP1492895A2 (de) 2005-01-05
EP1492895B1 EP1492895B1 (de) 2009-12-16

Family

ID=28052141

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03740568A Revoked EP1492895B1 (de) 2002-04-05 2003-04-04 Produkte aus al-zn-mg-cu-legierung

Country Status (9)

Country Link
US (1) US7550110B2 (de)
EP (1) EP1492895B1 (de)
JP (1) JP4535731B2 (de)
AT (1) ATE452216T1 (de)
AU (1) AU2003260001A1 (de)
DE (2) DE03740568T1 (de)
ES (1) ES2338314T3 (de)
FR (1) FR2838136B1 (de)
WO (1) WO2003085145A2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111057920A (zh) * 2020-01-07 2020-04-24 西南交通大学 一种超高强铝合金及其制备方法

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CN114990395B (zh) * 2022-04-13 2024-01-16 山东南山铝业股份有限公司 一种含稀土元素的高强度变形铝合金及其制备方法
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US20030219353A1 (en) 2003-11-27
AU2003260001A1 (en) 2003-10-20
WO2003085145A3 (fr) 2004-04-01
WO2003085145A2 (fr) 2003-10-16
DE60330547D1 (de) 2010-01-28
FR2838136B1 (fr) 2005-01-28
DE03740568T1 (de) 2005-07-14
EP1492895B1 (de) 2009-12-16
JP2005528521A (ja) 2005-09-22
ES2338314T3 (es) 2010-05-06
JP4535731B2 (ja) 2010-09-01
ATE452216T1 (de) 2010-01-15
FR2838136A1 (fr) 2003-10-10
US7550110B2 (en) 2009-06-23

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