EP2981631A1 - Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion - Google Patents
Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avionInfo
- Publication number
- EP2981631A1 EP2981631A1 EP14719034.2A EP14719034A EP2981631A1 EP 2981631 A1 EP2981631 A1 EP 2981631A1 EP 14719034 A EP14719034 A EP 14719034A EP 2981631 A1 EP2981631 A1 EP 2981631A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- weight
- mpa
- sheet according
- less
- sheet
- 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
Links
- 239000001989 lithium alloy Substances 0.000 title description 9
- -1 Aluminium-copper-lithium Chemical compound 0.000 title description 6
- 229910000733 Li alloy Inorganic materials 0.000 title description 6
- 239000000203 mixture Substances 0.000 claims abstract description 20
- 238000010791 quenching Methods 0.000 claims abstract description 12
- 230000000171 quenching effect Effects 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims abstract description 11
- 238000005098 hot rolling Methods 0.000 claims abstract description 9
- 229910052742 iron Inorganic materials 0.000 claims abstract description 9
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 9
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 9
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 8
- 238000005097 cold rolling Methods 0.000 claims abstract description 8
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 7
- 239000012535 impurity Substances 0.000 claims abstract description 7
- 229910052711 selenium Inorganic materials 0.000 claims abstract description 7
- 238000005496 tempering Methods 0.000 claims abstract description 7
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 7
- 238000005266 casting Methods 0.000 claims abstract description 6
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 5
- 239000010949 copper Substances 0.000 claims description 21
- 239000011777 magnesium Substances 0.000 claims description 17
- 229910052802 copper Inorganic materials 0.000 claims description 9
- 238000004519 manufacturing process Methods 0.000 claims description 9
- 229910052744 lithium Inorganic materials 0.000 claims description 8
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 7
- 238000004090 dissolution Methods 0.000 claims description 7
- 229910052749 magnesium Inorganic materials 0.000 claims description 7
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 6
- 229910001338 liquidmetal Inorganic materials 0.000 claims description 6
- 229910052709 silver Inorganic materials 0.000 claims description 6
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 5
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 5
- 238000000265 homogenisation Methods 0.000 claims description 5
- 239000004332 silver Substances 0.000 claims description 5
- 238000010030 laminating Methods 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 description 19
- 239000000956 alloy Substances 0.000 description 19
- 230000035882 stress Effects 0.000 description 18
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 11
- 229910052782 aluminium Inorganic materials 0.000 description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 9
- 238000005096 rolling process Methods 0.000 description 9
- 238000012360 testing method Methods 0.000 description 9
- 239000011701 zinc Substances 0.000 description 8
- 239000010936 titanium Substances 0.000 description 7
- 239000010455 vermiculite Substances 0.000 description 7
- 230000003068 static effect Effects 0.000 description 5
- 229910017539 Cu-Li Inorganic materials 0.000 description 4
- 229910052725 zinc Inorganic materials 0.000 description 4
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 3
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 3
- 238000012512 characterization method Methods 0.000 description 3
- 238000001953 recrystallisation Methods 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- 229910052719 titanium Inorganic materials 0.000 description 3
- 229910052726 zirconium Inorganic materials 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 210000003041 ligament Anatomy 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229910000754 Wrought iron Inorganic materials 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
- B22D21/002—Castings of light metals
- B22D21/007—Castings of light metals with low melting point, e.g. Al 659 degrees C, Mg 650 degrees C
-
- 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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
-
- 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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
Definitions
- the invention relates to rolled products aluminum-copper-lithium alloys, more particularly, such products, their manufacturing processes and use, intended in particular for aeronautical and aerospace construction.
- Aluminum alloy rolled products are being developed to produce fuselage elements for the aerospace industry and the aerospace industry in particular.
- Aluminum - copper - lithium alloys are particularly promising for this type of product.
- U.S. Patent 5,032,359 discloses a broad family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, particularly between 0.3 and 0.5 percent by weight, increases the mechanical strength. .
- US Pat. No. 5,455,003 describes a process for manufacturing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, in particular through appropriate work-hardening and tempering.
- US Pat. No. 7,438,772 describes alloys comprising, in percentage by weight, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourages the use of higher lithium contents due to degradation of the compromise between toughness and mechanical strength.
- US Pat. No. 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0, 1-2.5) Li, (0.2-1.0) Mg, (0, 2-0.8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Se, V.
- US patent application 2009/142222 A1 discloses alloys comprising (in% by weight), 3.4 to 4.2% Cu, 0.9 to 1.4% Li, 0.3 to 0.7% of Ag, 0.1 to 0.6% Mg, 0.2 to 0.8% Zn, 0.1 to 0.6% Mn and 0.01 to 0.6% of at least one element. for the control of the granular structure. This application also describes a process for manufacturing spun products.
- the patent application US 2011/0247730 describes alloys comprising (in% by weight), 2.75 to 5.0% Cu, 0.1 to 1.1% Li, 0.3 to 2.0% Ag, 0.2 to 0.8% Mg, 0.50 to 1.5% Zn, up to 1.0% Mn, with a Cu Mg ratio of between 6.1 and 17, this alloy being not very sensitive to wrought iron.
- the patent application CN101967588 describes alloys of composition (in% by weight) Cu 2.8 - 4.0; Li 0.8 - 1.9; Mn 0.2-0.6; Zn 0.20-0.80, Zr 0.04-0.20, Mg 0.20-0.80, Ag 0.1-0.7, Si ⁇ 0.10, Fe ⁇ 0.10, Ti ⁇ 0.12.
- EP 1 891 247 discloses an alloy comprising 2.1 to 2.8% by weight of Cu, 1.1 to 1.7% by weight of Li, 01 to 0.8% by weight of Ag, 0.2 0.6% by weight of Mg, 0.2 to 0.6% by weight of Mn, an amount of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities at a lower level. or equal to 0.05% by weight each and 0.15% by weight in total, the alloy being substantially free of zirconium, particularly suitable for obtaining recrystallized thin sheets.
- Damage tolerance design consists in determining a limitable, detectable size of defects that can be guaranteed to not break during a defined time interval. To achieve this dimensioning it is necessary to know the behavior of cracks subjected to a representative load on panels of sufficient size. In addition, in the case of the large damage capability assessment for which the undetected failure of a stiffener is assumed, the width of the crack can be high and it is useful to have accurate data of toughness for very long cracks.
- the characterization of toughness of the thin sheets is generally carried out on panels with a width of less than or equal to 760 mm by the R curve test.
- the curve test R is a widely recognized means for characterizing the tenacity properties.
- the curve R represents the evolution of the critical effective stress intensity factor for the crack propagation as a function of the effective crack extension, under monotonically increasing stress. It allows the determination of the critical load for unstable failure for any configuration relevant to cracked aircraft structures.
- the values of the effective stress intensity factor and the effective crack extension are actual values as defined in ASTM E561. It is generally believed that the width of the panel should not change the level of the R curve, namely the effective stress intensity factor for a given effective crack growth, but only the valid length of the curve. However, it has been found in the context of the present invention that this hypothesis is not always verified and that in fact the characterization on larger panels, such as panels of width 1220 mm, accounts for certain specific properties. material that can not be deduced from the characterizations performed on smaller panels. Thus the knowledge of the state of the art It is not possible to predict which alloys and which thermomechanical treatments will achieve the most advantageous properties for K app and for the level of the R curve on wide panels, but these properties will influence the dimensioning in damage tolerance.
- the toughness be high in the L-T direction. Indeed, in some configurations the bending stresses on the fuselage around the axis of the wings become critical, especially for the upper part of the fuselage. The cracks on the plates whose longitudinal direction and also the longitudinal direction of the fuselage are then biased in the L-T direction.
- the object of the invention is a sheet of thickness 0.5 to 8 mm of aluminum-based alloy comprising
- said sheet being obtained by a process comprising casting, homogenization, hot rolling and optionally cold rolling, dissolving, quenching and tempering, the composition and the income being combined so that the yield strength in the direction longitudinal dimension R p0i2 (L) is between 395 and 435 MPa
- Another subject of the invention is the method for manufacturing a sheet according to the invention with a thickness of 0.5 to 8 mm of aluminum-based alloy in which, successively a) a liquid metal bath comprising
- said plate is homogenized at a temperature between 450 ° C and 535 ° C;
- the sheet is controlledly tensile with a permanent deformation of 0.5 to 5%, the total cold deformation after dissolution and quenching is less than 15%;
- an income is made comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably from 10 to 40h, the composition and the income being combined so that the yield strength in the longitudinal direction R p o , 2 (L) is between 395 and 435 MPa
- Yet another object of the invention is the use of a sheet according to the invention in an aircraft fuselage panel.
- Figure 1 - R curves obtained in the direction L-T on sheets of thickness 4 to 5 mm for specimens of width 760 mm and 1220 mm.
- Figure 2 - R curves obtained in the direction L-T on sheets of thickness 1.5 to 2.5 mm for specimens of width 760 mm and 1220 mm.
- alloys are in accordance with the regulations of The Aluminum Association, known to those skilled in the art. The density depends on the composition and is determined by calculation rather than by a method of measuring weight. The values are calculated in accordance with the procedure of The Aluminum Association, which is described on pages 2-12 and 2-13 of "Aluminum Standards and Data". Unless otherwise stated, the definitions of the metallurgical states given in the European standard EN 515 apply.
- the static mechanical characteristics in tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0; 2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard. In the context of the invention, the mechanical characteristics are measured in full thickness.
- substantially uncrystallized granular structure refers to a granular structure such that the degree of recrystallization at 1 ⁇ 2-thickness is less than 30% and preferably less than 10%, and a substantially recrystallized granular structure is called a structure. granular such that the recrystallization rate at 1 ⁇ 2 thickness is greater than 70% and preferably greater than 90%. The recrystallization rate is defined as the surface fraction on a metallographic section occupied by recrystallized grains.
- a curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R curve, is determined according to ASTM E 561.
- the critical stress intensity factor Kc in others terms the intensity factor that makes the crack unstable, is calculated from the curve R.
- the stress intensity factor Kco is also calculated by assigning the crack length initial at the beginning of the monotonic load, at the critical load. These two values are calculated for a specimen of the required form. app represents the Kco factor corresponding to P specimen that was used to perform the curve test R.
- Keff represents the Kc factor corresponding to the specimen that was used to perform the curve test R.
- Aa eff (max) represents the crack extension of the last point of the curve R, valid according to ASTM E561.
- the crack size at the end of the fatigue pre-cracking stage is W / 3 for M (T) type specimens, where W is the specimen width as defined in ASTM E561.
- Sheet thickness 0.5 to 8 mm Al-Cu-Li alloy according to the composition of the invention, when their elastic limit in the longitudinal direction R p0j2 (L) is between 395 and 435 MPa d obtain toughness measured on wide panels especially in the LT direction, particularly advantageous.
- the present inventors have found, surprisingly, that the toughness measured in the LT direction on panels of width 1220 mm is improved for a precise range of elastic limit values in the longitudinal direction R p0j2 (L) while this effect is not observed when the measurement is made on panels of width 760 mm.
- the sheets have the advantageous properties when the income is made "at the peak".
- the so-called "peak income” is an income for which the yield strength in the transverse direction R p o , 2 (TL) has a value of at least 95 % of the yield strength in the transverse direction R p o, 2 (TL) obtained for an income having a time equivalent to 155 ° C of 48 h.
- a "peak" income is preferred.
- thermal stability is understood to mean the stability of the mechanical properties during a temperature exposure representative of the conditions experienced in civil aviation, this being for example simulated by an aging of 1000 hours at 85 ° C. vs. Therefore, it is chosen to perform, if necessary, an under-income for which the elastic limit in the transverse direction R P o, 2 (TL) has a value of between 88% and 94% and preferably of at least 91%. of the value obtained for an income having a time equivalent to 155 ° C of 48 hours.
- the copper content of the products according to the invention is between 2.6 and 3.0% by weight. In an advantageous embodiment of the invention, the copper content is between 2.8 and 3.0% by weight. In an advantageous embodiment of the invention, the copper content is at most 2.95% by weight and advantageously at most 2.9% by weight.
- the elastic limit R p o, 2 (L) is too high to reach the advantageous range under the under-feed conditions according to the invention.
- the copper content is too low, the minimum static mechanical characteristics are not reached, even for a peak income.
- the lithium content of the products according to the invention is between 0.5 and 0.8% by weight.
- the lithium content is between 0.55% and 0.75% by weight.
- the lithium content is between 0.60% and 0.73% by weight.
- the addition of lithium can contribute to the increase of the mechanical strength and the toughness, a content that is too high or too low does not make it possible to obtain a high value of tenacity and / or a sufficient limit of elasticity.
- the magnesium content of the products according to the invention is between 0.2 and 0.7% by weight, preferably between 0.25 and 0.50% by weight and preferably between 0.30 and 0.45% by weight. in weight. In an advantageous embodiment of the invention, the magnesium content is at most 0.4% by weight.
- the zirconium content is between 0.06 and 0.20% by weight and preferably between 0.10 and 0.18% by weight. When an essentially non-recrystallized granular structure is preferred, the zirconium content is advantageously between 0.14 and 0.17% by weight.
- the silver content is between 0.1 and 0.4% by weight. In an advantageous embodiment of the invention, the silver content is between 0.2 and 0.3% by weight. In one embodiment of the invention the silver content is between 0.15 and 0.28% by weight.
- the titanium content is between 0.01 and 0.15% by weight.
- the addition of titanium helps to control the granular structure, especially during casting.
- the alloy may optionally contain at least one element selected from Mn, V, Cr, Se, and Hf, the amount of the element, if selected, being from 0.01 to 0.8% by weight for Mn 0.05 to 0.2% by weight for V, 0.05 to 0.3% by weight for Cr, 0.02 to 0.3% by weight for Se, 0.05 to 0.5% by weight for Hf.
- Mn, V, Cr or Se are not added and their content is less than or equal to 0.05% by weight.
- the iron and silicon contents are each at most 0.1% by weight.
- the iron and silicon contents are at most 0.08% and preferably at most 0.04% by weight.
- a controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
- the zinc content is less than 0.2% by weight and preferably less than 0.1% by weight.
- the zinc content is advantageously less than 0.04% by weight.
- the unavoidable impurities are maintained at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total.
- the manufacturing process of the sheets according to the invention comprises steps of production, casting, rolling, dissolution, quenching controlled traction and income.
- a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
- the bath of liquid metal is then cast into a form of rolling plate.
- the rolling plate is then homogenized at a temperature between 450 ° C and 535 ° and preferably between 480 ° C and 530 ° C.
- the homogenization time is preferably between 5 and 60 hours.
- the rolling plate is generally cooled to room temperature before being preheated to be hot deformed. Preheating aims to achieve a temperature preferably between 400 and 500 ° C for deformation by hot rolling.
- the hot rolling and optionally cold rolling is carried out so as to obtain a sheet thickness of 0.5 to 8 mm.
- Intermediate heat treatments during rolling and / or after rolling can be carried out in some cases. However, preferably, the process does not include intermediate heat treatment during rolling and / or after rolling.
- the sheet thus obtained is then put in solution by heat treatment between 450 and 535 ° C, preferably for 5 min to 8 h, and then quenched. It is known to those skilled in the art that the precise conditions of dissolution must be chosen according to the thickness and the composition so as to solubilize the hardening elements.
- the sheet then undergoes cold deformation by controlled traction with a permanent deformation of 0.5 to 5% and preferably of 1 to 3%.
- Known steps such as rolling, planing, straightening and shaping may optionally be carried out after dissolution and quenching and before or after the controlled pull, however total cold deformation after dissolution and quenching must remain less than 15% and preferably less than 10%.
- High cold deformation after dissolution and quenching cause the appearance of many shear bands passing through several grains, these shear bands being undesirable.
- An income is made comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably from 10 to 40h so as to achieve a limit of elasticity in the direction longitudinal R p0j 2 (L) between 395 and 435 MPa.
- a yield strength in the longitudinal direction R p0; 2 (L) of 395 and 415 MPa may be preferred in some cases.
- a yield strength in the longitudinal direction R p0; 2 (L) of 415 and 435 MPa may be preferred in some cases.
- the composition makes it possible to reach the desired longitudinal elasticity limit with a time equivalent to 155 ° C. of less than 48 hours and preferably less than 30 hours.
- the final metallurgical state is a T8 state.
- the equivalent time t at 155 ° C is defined by the formula:
- T in Kelvin
- T ref is a reference temperature set at 428 K.
- tj is expressed in hours.
- the present inventors have found in particular that the preferred field of magnesium content makes it possible to limit the duration of the income by reaching a favorable property compromise.
- a short heat treatment is performed after controlled pulling and before tempering so as to improve the formability of the sheets.
- the sheets can thus be shaped by a process such as stretch-forming before being returned.
- the most favorable granular structure depends on the thickness of the products.
- the sheets according to the invention, the thickness of which is between 0.5 and 3.3 mm advantageously have the following properties:
- the present inventors have furthermore found that for the sheets of the invention, the thickness of which is between 0.5 and 3.3 mm and preferably between 1.0 and 3.0 mm, the Kapp plane stress toughness in the LT direction is higher for sheets whose structure is essentially recrystallized.
- the sheets whose thickness is between 0.5 and 3.3 mm and preferably between 1.0 and 3.0 mm and whose granular structure is substantially recrystallized advantageously have the following properties:
- the sheets according to the invention advantageously have the following properties:
- the granular structure of the sheets whose thickness is between 3.4 and
- the resistance to intergranular corrosion of the sheets according to the invention is high.
- the sheet of the invention can be used without plating.
- the use of sheets according to the invention in an aircraft fuselage panel is advantageous.
- the sheets according to the invention are also advantageous in aerospace applications such as the manufacture of rockets.
- compositions B, C, D and E are according to the invention.
- the plates were homogenized for 12 hours at 505 ° C.
- the plates were hot-rolled to obtain sheets having a thickness of between 4.2 and 6.3 mm. Some sheets were then cold rolled to a thickness of between 1.5 and 2.5 mm.
- the details of the sheets obtained and the income conditions are given in Table 2.
- the granular structure of the samples was characterized from microscopic observation of cross sections after anodic oxidation under polarized light.
- the granular structure of the sheets was essentially non-recrystallized for all sheets except D # 2 and E # 2 sheets for which the granular structure was essentially recrystallized.
- Table 4 summarizes the results of the tenacity tests on CCT test pieces of width 760 mm for these samples. Table 4 results of the R curves for 760 mm wide specimens.
- Table 5 summarizes the results of the toughness tests for the R curves obtained from the 1220 mm wide CCT specimens in the L-T direction.
- Table 5 results of the R curves for specimens of width 1220 mm in the L-T direction.
- the curves R obtained for the sheets whose thickness is of the order of 4 mm are presented in FIG. 1.
- the curves R obtained for the sheets whose thickness is 1.5 to 2.5 mm are presented on FIG. Figure 2.
- the points obtained after the last valid point according to the ASTM E561 standard were represented.
- K ap LT is substantially identical for specimens with a width of 760 mm and for test specimens with a width of 1220 mm for certain sheets, whereas for other K app plates LT is lower for specimens with a width of 760 mm. and for specimens with a width of 1220 mm.
- Table 7 results of the R curves for specimens of width 760 mm and 1220 mm in the L-T direction.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Heat Treatment Of Steel (AREA)
- Conductive Materials (AREA)
- Metal Rolling (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1300763A FR3004196B1 (fr) | 2013-04-03 | 2013-04-03 | Toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion. |
PCT/FR2014/000069 WO2014162068A1 (fr) | 2013-04-03 | 2014-04-01 | Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2981631A1 true EP2981631A1 (fr) | 2016-02-10 |
EP2981631B1 EP2981631B1 (fr) | 2017-08-02 |
Family
ID=49000974
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14719034.2A Active EP2981631B1 (fr) | 2013-04-03 | 2014-04-01 | Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion |
Country Status (7)
Country | Link |
---|---|
US (1) | US20160060741A1 (fr) |
EP (1) | EP2981631B1 (fr) |
CN (1) | CN105102647B (fr) |
BR (1) | BR112015024820B1 (fr) |
CA (1) | CA2907807C (fr) |
FR (1) | FR3004196B1 (fr) |
WO (1) | WO2014162068A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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WO2021111069A1 (fr) | 2019-12-06 | 2021-06-10 | Constellium Issoire | Tôles minces en alliage d'aluminium-cuivre-lithium à tenacite ameliorée et procédé de fabrication d'une tôle mince en alliage d'aluminium-cuivre-lithium |
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MX2019001802A (es) | 2016-08-26 | 2019-07-04 | Shape Corp | Proceso de modelacion en caliente y aparato para flexion transversal de una viga de aluminio extrudida para modelar en caliente un componente estructural del vehiculo. |
WO2018078527A1 (fr) | 2016-10-24 | 2018-05-03 | Shape Corp. | Procédé de formage et de traitement thermique d'un alliage d'aluminium en plusieurs étapes pour la production de composants pour véhicules |
FR3059578B1 (fr) * | 2016-12-07 | 2019-06-28 | Constellium Issoire | Procede de fabrication d'un element de structure |
US20180291489A1 (en) * | 2017-04-11 | 2018-10-11 | The Boeing Company | Aluminum alloy with additions of copper, lithium and at least one alkali or rare earth metal, and method of manufacturing the same |
DE102017116785B3 (de) * | 2017-07-25 | 2019-01-24 | P3 Aero Systems Gmbh | Verfahren zum Überprüfen funktechnischer Eigenschaften eines Verkehrsmittels |
US20190233921A1 (en) * | 2018-02-01 | 2019-08-01 | Kaiser Aluminum Fabricated Products, Llc | Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application |
FR3082210B1 (fr) * | 2018-06-08 | 2020-06-05 | Constellium Issoire | Toles minces en alliage d’aluminium-cuivre-lithium pour la fabrication de fuselages d’avion |
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JPH0517843A (ja) * | 1991-07-11 | 1993-01-26 | Arishiumu:Kk | 耐SCC性が優れた高強度Al−Li系合金 |
US7438772B2 (en) * | 1998-06-24 | 2008-10-21 | Alcoa Inc. | Aluminum-copper-magnesium alloys having ancillary additions of lithium |
CN101189353A (zh) | 2005-06-06 | 2008-05-28 | 爱尔康何纳吕公司 | 用于飞机机身的高韧度的铝-铜-锂合金板材 |
RU2415960C2 (ru) * | 2005-06-06 | 2011-04-10 | Алкан Реналю | Алюминиево-медно-литиевый лист с высокой вязкостью разрушения для фюзеляжа самолета |
FR2925523B1 (fr) * | 2007-12-21 | 2010-05-21 | Alcan Rhenalu | Produit lamine ameliore en alliage aluminium-lithium pour applications aeronautiques |
FR2947282B1 (fr) * | 2009-06-25 | 2011-08-05 | Alcan Rhenalu | Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees |
CN102021457B (zh) | 2010-10-27 | 2012-06-27 | 中国航空工业集团公司北京航空材料研究院 | 一种高强韧铝锂合金及其制备方法 |
CN101967588B (zh) * | 2010-10-27 | 2012-08-29 | 中国航空工业集团公司北京航空材料研究院 | 一种耐损伤铝锂合金及其制备方法 |
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- 2013-04-03 FR FR1300763A patent/FR3004196B1/fr not_active Expired - Fee Related
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- 2014-04-01 EP EP14719034.2A patent/EP2981631B1/fr active Active
- 2014-04-01 CA CA2907807A patent/CA2907807C/fr active Active
- 2014-04-01 US US14/781,097 patent/US20160060741A1/en not_active Abandoned
- 2014-04-01 BR BR112015024820-9A patent/BR112015024820B1/pt active IP Right Grant
- 2014-04-01 WO PCT/FR2014/000069 patent/WO2014162068A1/fr active Application Filing
- 2014-04-01 CN CN201480020260.3A patent/CN105102647B/zh active Active
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021111069A1 (fr) | 2019-12-06 | 2021-06-10 | Constellium Issoire | Tôles minces en alliage d'aluminium-cuivre-lithium à tenacite ameliorée et procédé de fabrication d'une tôle mince en alliage d'aluminium-cuivre-lithium |
FR3104172A1 (fr) | 2019-12-06 | 2021-06-11 | Constellium Issoire | Tôles minces en alliage d’aluminium-cuivre-lithium à ténacité améliorée et procédé de fabrication |
Also Published As
Publication number | Publication date |
---|---|
WO2014162068A1 (fr) | 2014-10-09 |
CA2907807C (fr) | 2021-06-01 |
BR112015024820B1 (pt) | 2020-05-12 |
CN105102647A (zh) | 2015-11-25 |
CA2907807A1 (fr) | 2014-10-09 |
CN105102647B (zh) | 2017-10-13 |
FR3004196B1 (fr) | 2016-05-06 |
EP2981631B1 (fr) | 2017-08-02 |
BR112015024820A2 (pt) | 2017-07-18 |
FR3004196A1 (fr) | 2014-10-10 |
US20160060741A1 (en) | 2016-03-03 |
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