EP1382698B1 - Knetprodukt aus Al-Cu-Mg-Legierung für das Strukturbauteil eines Flugzeugs - Google Patents
Knetprodukt aus Al-Cu-Mg-Legierung für das Strukturbauteil eines Flugzeugs Download PDFInfo
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- EP1382698B1 EP1382698B1 EP03356108A EP03356108A EP1382698B1 EP 1382698 B1 EP1382698 B1 EP 1382698B1 EP 03356108 A EP03356108 A EP 03356108A EP 03356108 A EP03356108 A EP 03356108A EP 1382698 B1 EP1382698 B1 EP 1382698B1
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 78
- 239000000956 alloy Substances 0.000 title claims abstract description 78
- 229910017818 Cu—Mg Inorganic materials 0.000 title 1
- 239000000203 mixture Substances 0.000 claims abstract description 14
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 238000005096 rolling process Methods 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 claims abstract description 7
- 238000012360 testing method Methods 0.000 claims description 21
- 230000007797 corrosion Effects 0.000 claims description 18
- 238000005260 corrosion Methods 0.000 claims description 18
- 229910052751 metal Inorganic materials 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 13
- 238000010791 quenching Methods 0.000 claims description 10
- 230000000171 quenching effect Effects 0.000 claims description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 6
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 claims description 6
- 238000005482 strain hardening Methods 0.000 claims description 6
- 239000010455 vermiculite Substances 0.000 claims description 4
- 238000005266 casting Methods 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 239000011780 sodium chloride Substances 0.000 claims description 3
- 238000005242 forging Methods 0.000 claims description 2
- VSCWAEJMTAWNJL-UHFFFAOYSA-K aluminium trichloride Chemical compound Cl[Al](Cl)Cl VSCWAEJMTAWNJL-UHFFFAOYSA-K 0.000 claims 2
- 230000001131 transforming effect Effects 0.000 claims 2
- 230000005587 bubbling Effects 0.000 claims 1
- 238000005253 cladding Methods 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 claims 1
- 230000009466 transformation Effects 0.000 abstract description 3
- 238000010622 cold drawing Methods 0.000 abstract 2
- 238000005496 tempering Methods 0.000 abstract 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 29
- 239000010949 copper Substances 0.000 description 28
- 239000000047 product Substances 0.000 description 26
- 239000011777 magnesium Substances 0.000 description 25
- 239000011572 manganese Substances 0.000 description 23
- 239000011701 zinc Substances 0.000 description 15
- 229910052802 copper Inorganic materials 0.000 description 10
- 230000003068 static effect Effects 0.000 description 9
- 229910052782 aluminium Inorganic materials 0.000 description 8
- 229910052749 magnesium Inorganic materials 0.000 description 8
- 238000007747 plating Methods 0.000 description 8
- 239000000243 solution Substances 0.000 description 8
- 229910052725 zinc Inorganic materials 0.000 description 8
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 7
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 7
- 229910052742 iron Inorganic materials 0.000 description 7
- 229910052710 silicon Inorganic materials 0.000 description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 6
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 6
- 229910052748 manganese Inorganic materials 0.000 description 6
- 239000010703 silicon Substances 0.000 description 6
- 230000035882 stress Effects 0.000 description 6
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 5
- 229910052709 silver Inorganic materials 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000004090 dissolution Methods 0.000 description 4
- 238000004064 recycling Methods 0.000 description 4
- 239000004332 silver Substances 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 238000005336 cracking Methods 0.000 description 3
- 230000035800 maturation Effects 0.000 description 3
- 238000009864 tensile test Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 150000003839 salts Chemical class 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- 239000003351 stiffener Substances 0.000 description 2
- 229910052720 vanadium Inorganic materials 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000004210 cathodic protection Methods 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229940082150 encore Drugs 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000005098 hot rolling Methods 0.000 description 1
- -1 i.e. Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 229910001338 liquidmetal Inorganic materials 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 238000003303 reheating Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000005070 ripening Effects 0.000 description 1
- 229910052706 scandium Inorganic materials 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000001757 thermogravimetry curve Methods 0.000 description 1
- 238000012345 traction test Methods 0.000 description 1
- 150000003751 zinc Chemical class 0.000 description 1
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
- C22C21/12—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
-
- 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
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12736—Al-base component
- Y10T428/12764—Next to Al-base component
Definitions
- the invention relates to aircraft structural elements, in particular sheet metal for large commercial aircraft fuselage made from rolled, spun or forged alloy AlCuMg in the treated state by dissolving, quenching and cold work hardening, and having, compared to the products of the prior art used for the same application, an improved compromise between the different properties required.
- the fuselage of commercial aircraft of large capacity is typically made of an AlCuMg alloy sheet skin, as well as longitudinal stiffeners and circumferential frames.
- a type 2024 alloy is used which, according to the designation of the Aluminum Association or the standard EN 573-3, has the following chemical composition (% by weight): If ⁇ 0.5 Fe ⁇ 0.5 Cu: 3.8 - 4.9 Mg: 1.2 - 1.8 Mn: 0.3 - 0.9 Cr ⁇ 0.10 Zn ⁇ 0.25 Ti ⁇ 0 15.
- Variants of this alloy are also used. These elements are asked structures a compromise between several properties such as: resistance mechanical (i.e. static mechanical characteristics), tolerance to damage (toughness and speed of fatigue cracking), fatigue resistance (especially oligocyclic), resistance to different forms of corrosion, fitness ability. In some cases, especially for airplanes supersonic, creep resistance can be critical.
- US Patent 5,652,063 (Alcoa) relates to an aircraft structural element made from a composition alloy (% by weight): Cu: 4.85 - 5.3 Mg: 0.51 - 1.0 Mn: 0.4 - 0.8 Ag: 0.2 - 0.8 If ⁇ 0.1 Fe ⁇ 0.1 Zr ⁇ 0, With Cu / Mg between 5 and 9.
- the sheet of this alloy in the T8 state has a yield strength> 77 ksi (531 MPa).
- the alloy is particularly intended for supersonic aircraft.
- the patent application EP 0 731 185 of the Applicant relates to an alloy, subsequently recorded under No. 2024A, of composition: Si ⁇ 0.25 Fe ⁇ 0.25 Cu: 3.5 - 5 Mg: 1 - 2 Mn ⁇ 0.55 with the relation: 0 ⁇ Mn - 2Fe ⁇ 0.2
- the thick plates in this alloy have both improved toughness and a reduced level of residual stresses, without loss on the other properties.
- the alloy may also contain: Zr ⁇ 0.20% V ⁇ 0.20% Mn ⁇ 0.80% Ti ⁇ 0.05% Fe ⁇ 0.15% Si ⁇ 0.10%.
- the present invention aims to obtain aircraft structural elements, and in particular fuselage elements made of AlCuMg alloy having, compared to the prior art, improved damage tolerance, mechanical resistance to less equal, an improved resistance to corrosion, and this without resorting to expensive and troublesome addition elements for recycling.
- the subject of the invention is a wrought product, in particular a laminated, spun or forged product, made of an alloy of composition (% by weight): Cu 3.80 - 4.30, Mg 1.25 - 1.45, Mn 0.20 - 0.50, Zn 0.40 - 1.30, Zr ⁇ 0.05, Fe ⁇ 0.15, Si ⁇ 0.15, Ag ⁇ 0.01 other elements ⁇ 0.05 each and ⁇ 0.15 in total, remain Al, said product can be treated by dissolving, quenching, and cold working, with a permanent deformation of between 0.5% and 15%, preferably between 1% and 5%, and even more preferably between 1.5% and 3.5%.
- Cold working can be obtained by controlled pulling and / or cold processing, for example rolling or drawing.
- the invention also relates to a structural element for construction aeronautical equipment, in particular an aircraft fuselage element, manufactured from such an aircraft wrought product, and especially from such a rolled product.
- the copper content of the alloy according to the invention is between 3.80 and 4.30 %, and preferably between 4.05 and 4.30%; so it's in the low half of the content range of alloy 2024, so as to limit the volume fraction residual coarse copper particles.
- the interval of magnesium content which must be between 1.25 and 1.45% and preferably between 1.28 and 1.42%, is shifted downwards compared to that of 2024.
- the manganese is maintained between 0.20 and 0.50%, preferably between 0.30 and 0.50, and more preferably between 0.35 and 0.48%.
- the implementation of the invention does not require significant addition of zirconium at a content greater than 0.05%.
- the present invention requires careful control of the zinc content, the alloy being discharged into copper, magnesium and manganese.
- the zinc content must be between 0.40 and 1.30%, preferably between 0.50 and 1.10%, and still between more preferably between 0.50 and 0.70%.
- the zinc content at least equal to (1.2Cu - 0.3Mg + 0.3Mn - 3.75).
- the silicon and iron contents are each kept below 0.15%, and preferably below 0.10%, to have good toughness.
- this is only in very cases (depending on the type of alloy and the intended application) that the gain in damage tolerance related to the use of aluminum containing less than 0.06 % iron and silicon each is large enough to be valued.
- the implementation of the present invention does not require that the content of iron and silicon less than 0.06% each, because in the selected composition range, the Damage tolerance is very good.
- the alloy contains no silver addition, nor any other element likely to increase the production cost of the alloy and to pollute the other alloys produced on the same site by recycling manufacturing scrap.
- the preferred method of manufacture comprises casting of plates, in the case where the product to be made is a rolled sheet, or billets in the case where it is a spun section or a forged part.
- the plate or the billet is scalped, then homogenized between 450 and 500 ° C.
- the hot transformation is then carried out by rolling, spinning or forging, optionally completed by a cold transformation step.
- the laminated, spun or forged half-product is then dissolved between 480 and 505 ° C., so that this dissolution is as complete as possible, that is to say that the maximum of potentially soluble phases , in particular the precipitates Al 2 Cu and Al 2 CuMg, are effectively put back in solution.
- the quality of the dissolution can be assessed by differential enthalpy analysis (AED) by measuring the specific energy using the area of the peak on the thermogram. This specific energy must preferably be less than 2 J / g.
- AED differential enthalpy analysis
- This hardening cold can be a controlled pull with a permanent elongation between 1 and 5% bringing the product to a T351 state. Controlled traction with a permanent elongation of between 1.5% and 3.5%. It can also be a cold rolling by rolling in the case of sheets or by drawing in the case profiles, with a permanent elongation of up to 15%, bringing the in the T39 state, or in the T3951 state if the rolling or drawing is combined with the traction.
- the product finally undergoes natural aging at room temperature.
- the final microstructure is in general largely recrystallized, with grains relatively thin and fairly equiaxed.
- the product according to the present invention is well suited for use as an aircraft structural element, for example as a fuselage skin element, and especially as an element for the fuselage skin panel (skin).
- These sheets preferably plated, have a thickness of between 1 and 16 mm, and have good resistance to intergranular corrosion and corrosion on riveted assembly. They have a breaking strength in the L direction and / or TL direction greater than 430 MPa, and preferably greater than 440 MPa, and a yield strength in the L and / or TL direction greater than 300 MPa, and preferably greater than 320. MPa.
- the sheet according to the invention may be a sheet plated with at least one face with an alloy of the 1xxx series, and preferably with an alloy selected from the group consisting of alloys 1050, 1070, 1300 and 1145.
- plated sheets according to the invention which are particularly resistant to corrosion by galvanic coupling. in a riveted assembly. More particularly, plated sheets which exhibit a galvanic corrosion current of less than 4 ⁇ A / cm 2 , and preferably less than 2.5 ⁇ A / cm 2 , for exposure of up to 200 hours, during corrosion tests in a riveted assembly, placing the core alloy in a non-deaerated solution containing 0.06 M NaCl and the plating alloy in a 0.02 M AlCl 3 solution deaerated by nitrogen sparging.
- N0, N1, N2 and N3 alloys were developed with chemical composition was in accordance with the invention.
- the liquid metal was first treated in the furnace maintaining by injection of gas using a rotor of a type known under the brand IRMA, and then in a pocket of type known as Alpur.
- the refining has been done online, that is to say between the holding oven and the Alpur pocket, with wire AT5B (0.7 kg / t for N0, N1 and N3, 0.3 kg / t for N2).
- 3.0 plates were cast m length and section 1450 mm x 377 mm (except for N3: section 1450 x 446 mm). They were relaxed for 10h at 350 ° C.
- alloy plating 1050 corresponds to about 2% of thickness.
- alloys E and F For the alloys according to the prior art (alloys E and F), the plates have been heated to around 450 ° C, then hot-rolled at the reversing mill up to a thickness of about 20 mm. The resulting strips were rolled on a tandem rolling mill with three cages up to a final thickness close to 5 mm, then wound (at temperatures of 320 ° C and 260 ° C, respectively for alloys F and E). In the case of alloy F, the coil thus obtained was laminated to cold to a thickness of 3.2 mm.
- Sheet metal was cut, put in solution in a salt bath oven at a temperature of 498.5 ° C for a duration of 30 minutes (sheet metal E thickness 5 mm) or 25 min (sheet F thickness 3.2 mm), then completed (wrinkling followed by controlled traction with permanent elongation included between 1.5 and 3%).
- the N0 plate has undergone the following homogenization cycle: 8h at 495 ° C + 12h at 500 ° C (nominal values) while alloys N1, N2 and N3 have been homogenized for 12 hours at 500 ° C.
- the plates After reheating (approximately 18 h at 425-445 ° C), the plates were hot-rolled (inlet temperature: 413 ° C) to a thickness of about 90 mm.
- the N0 band thus obtained was cut in half in the direction perpendicular to the rolling direction. There were thus obtained two bands, labeled N01 and N02. These strips were rolled on a hot rolling mill tandem 3 cages up to a final thickness of 6 mm (winding temperature approximately 320 - 325 ° C).
- N1 and N3 alloy plate and a N3 alloy plate were laminated to to 5.5 mm before being cold-rolled to the final thickness of 3.2 mm, and a Another N1 alloy plate was hot rolled to 4.5 mm before being rolled to cold to the final thickness of 1.6 mm.
- N2 alloy plate was hot rolled to a final thickness of 6 mm (tandem winding temperature 270 ° C).
- the coil N01 has not undergone any other rolling pass, while the coil N02 was cold rolled to a final thickness of 3.2 mm.
- the plates once cut were dissolved in a salt bath oven (thickness 6 mm: 60 minutes at 500 ° C., thickness 3.2 mm: 40 minutes at 500 ° C.; thickness 1, 6 mm: 30 minutes at 500 ° C) followed by quenching with water to about 23 ° C. After quenching, the sheets have undergone wrinkling and pulling with elongation cumulative standing between 1.5 and 3.5%. The waiting time between quenching and wrinkling did not exceed 6 hours.
- the tensile strength R m (in MPa), the conventional yield stress at 0.2% elongation R p0.2 (in MPa) and the elongation at break A (in%) were measured by a tensile test according to EN 10002-1.
- the product according to the invention therefore has a better breaking strength in the case of a cracked panel.
- the plates of 2024 in particular for ⁇ K ⁇ 20 MPa ⁇ m, exhibit a cracking rate two to three times higher than for the product according to the invention. The latter therefore allows longer inspection intervals (to mass given structure) or reductions in the inspection interval structure fixed.
- the breaking K values for a limiting load greater than 200 MPa are greater than about 120 MPa ⁇ m for the described R curves, with apparent K (K r ) greater than about 110 MPa m.
- K r apparent K
- the corrosion resistance of the sheets has also been characterized.
- the alloy according to the invention shows intrinsically, that is to say after displacement by machining, resistance to intergranular corrosion, measured according to ASTM standard G 110, substantially comparable to that of the reference 2024.
- the test consists in measuring the current which is established naturally between the anode (alloy of plating placed in a cell containing a solution of AlCl 3 (0,02 M, deaerated by sparging of nitrogen)) and the cathode (alloy core placed in a cell containing a solution of NaCl (0.06 M, aerated)), a salt bridge ensuring the electrolytic contact between the two cells. Both elements (veneer and core) have the same surface (2.54 cm 2 ). The coupling current densities are recorded throughout the duration of the test. It is observed that the current reaches a plateau after about 55 hours and hardly changes during the tests (200 hours or 15 days, depending on the sample). The results are summarized in Table 6.
- state F From hot-rolled and possibly cold-rolled sheets (state F) of the alloy according to the invention (see example 1), several other metallurgical states were developed in the form of a size of 600 mm (L-direction) x 160 mm (TL direction) x thickness.
- the marks ending in A, D, F and I correspond to T351 states.
- the different samples were characterized by tensile tests (L and TL directions) as well as toughness tests.
- the tenacity was first evaluated in the TL and LT directions using the maximum stress R e (in MPa) and the flow energy E ec according to the Kahn test.
- the stress Kahn is equal to the ratio of the maximum load F max that the specimen can withstand on the section of the specimen (product of the thickness B by the width W).
- the flow energy is determined as the area under the force-displacement curve up to the maximum force F max supported by the specimen.
- the test is described in the article "Kahn-Type Tear Test and Crack Toughness of Aluminum Alloy Sheet", published in the journal Materials Research & Standards, April 1964, p. 151- 155.
- the sample used for the test of tenacity Kahn is described, for example, in the "Metals Handbook", 8 th Edition, vol. 1, American Society for Metals, pp. 241-242.
- the tenacity was also approached for sheets of thickness 6 mm, using a curve-type test R, in the TL direction, but on smaller specimens than that described in Example 1.
- Sheets made according to Example 2 were subjected to a 5% cold work (by controlled pulling) after quenching.
- Tables 10 and 11 show the results of the characterizations.
- Static mechanical characteristics sheet metal Ep [mm] Meaning L TL direction rm [MPa] R p0,2 [MPa] AT [%] rm [MPa] R p0,2 [MPa] AT [%] N1 1.6 468 404 20.1 456 341 20.6 N1 3.2 472 408 18.2 464 348 19.3 N2 6 488 422 19.1 475 368 20.2
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Thermal Sciences (AREA)
- Physics & Mathematics (AREA)
- Heat Treatment Of Steel (AREA)
- Metal Rolling (AREA)
- Conductive Materials (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Laminated Bodies (AREA)
- Powder Metallurgy (AREA)
Claims (23)
- Knetprodukt, insbesondere Walz-, Strangpress- oder Schmiedeprodukt aus AlCuMg-Legierung, dadurch gekennzeichnet, dass es enthält (Gew.-%):
Cu: 3,80 - 4,30 Mg: 1,25 - 1,45 Mn: 0,20 - 0,50 Zn: 0,40 - 1,30 Fe < 0,15 Si < 0,15 Zr ≤ 0,05 Ag < 0,01,
weitere Elemente jeweils < 0,05 und insgesamt < 0,15, Rest Al. - Produkt nach Anspruch 1, mit Cu 4,05 - 4,30.
- Produkt nach Anspruch 1 oder 2, mit Mg 1,28 - 1,42.
- Produkt nach irgendeinem der Ansprüche 1 bis 3, mit Mn 0,30 - 0,50 und bevorzugt Mn 0,35 - 0,48.
- Produkt nach irgendeinem der Ansprüche 1 bis 4, mit Zn 0,50 - 1,10 und bevorzugt 0,50 - 0,70.
- Produkt nach irgendeinem der Ansprüche 1 bis 5, mit Fe < 0,10.
- Produkt nach irgendeinem der Ansprüche 1 bis 6, mit Si < 0,10.
- Produkt nach Anspruch 1, mit
Cu < 4,20 Mg < 1,38 Mn < 0,42 Zn ≥ (1,2 Cu - 0,3 Mg + 0,3 Mn - 3,75). - Produkt nach irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass es lösungsgeglüht, abgeschreckt und kaltverfestigt wurde mit einer bleibenden Verformung zwischen 0,5 und 15 %, bevorzugt zwischen 1 und 5 % und besonders bevorzugt zwischen 1,5 und 3,5 %.
- Produkt nach irgendeinem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass das Produkt ein Blech ist mit einer Dicke zwischen 1 und 16 mm.
- Produkt nach irgendeinem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass das Blech ein wenigstens einseitig mit einer Legierung der Serie 1xxx und bevorzugt mit einer aus der Gruppe der Legierungen 1050, 1070, 1300 und 1145 gewählten Legierung plattiertes Blech ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass seine Bruchfestigkeit in Längsrichtung und/oder Quer-Längsrichtung größer als 430 MPa und bevorzugt größer als 440 MPa ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 12, dadurch gekennzeichnet, dass seine Elastizitätsgrenze in Längsrichtung und/oder Quer-Längsrichtung größer als 300 MPa und bevorzugt größer als 320 MPa ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 13, dadurch gekennzeichnet, dass seine Bruchdehnung in Längsrichtung und/oder Quer-Längsrichtung größer als 19 % und bevorzugt größer als 20 % ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 14, dadurch gekennzeichnet, dass seine Schadentoleranz Kr, berechnet aus einer nach ASTM E 561 bei einem Wert Δaeff von 60 mm erhaltenen Kurve R, größer als 165 MPa√m in Quer-Längsrichtung und Längs-Querrichtung ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 15, dadurch gekennzeichnet, dass seine Schadentoleranz Kr, berechnet aus einer nach ASTM E 561 bei einem Wert Δaeff von 60 mm erhaltenen Kurve R, größer als 180 MPa√m in Längs-Querrichtung ist.
- Produkt nach irgendeinem der Ansprüche 1 bis 16, dadurch gekennzeichnet, dass seine Rissausbreitungsgeschwindigkeit da/dn, ermittelt nach der Norm ASTM E 647 in Quer-Längsrichtung oder Längs-Querrichtung bei einem Lastverhältnis R = 0,1 und einem Wert ΔK von 50 MPa√m, kleiner als 2,5 10-2 mm / Zyklus und bevorzugt kleiner als 2,0 10-2 mm / Zyklus ist.
- Plattiertes Blech nach irgendeinem der Ansprüche 1 bis 17, dadurch gekennzeichnet, dass der galvanische Korrosionsstrom geringer ist als 4µA/cm2 bei einer Expositionszeit von bis zu 200 Stunden während Korrosionsprüfungen in einer Nietverbindung, bei denen die Kernlegierung in eine belüftete Lösung mit 0,06 M NaCl und die Plattierungslegierung in eine durch Stickstoffspülung entlüftete Lösung mit 0,02 M AlCl3 eingebracht wird.
- Plattiertes Blech nach Anspruch 18, dadurch gekennzeichnet, dass der galvanische Korrosionsstrom geringer ist als 2,5µA/cm2.
- Strukturbauteil für ein Luftfahrzeug, hergestellt aus mindestens einem Produkt nach irgendeinem der Ansprüche 1 bis 19.
- Strukturbauteil nach Anspruch 20, dadurch gekennzeichnet, dass das Strukturbauteil ein Rumpfhautbauteil ist.
- Verfahren zur Herstellung eines Knetproduktes nach einem der Ansprüche 1 bis 19 mit folgenden Schritten:(a) Gießen einer Platte oder eines Pressbarrens(b) Homogenisierung zwischen 450°C und 500°C(c) Warmumformung durch Strangpressen, Walzen oder Schmieden(d) eventuell eine Kaltumformung(e) Lösungsglühen zwischen 480°C und 505°C(f) Abschrecken(g) Kaltverfestigung, bei der eine bleibende Verformung zwischen 0,5 % und 15 % entsteht.
- Verfahren nach Anspruch 22, bei dem die Kaltverfestigung so durchgeführt wird, dass eine bleibende Verformung zwischen 1 und 5 % und bevorzugt zwischen 1,5 und 3,5 % entsteht.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE60300004T DE60300004T3 (de) | 2002-07-11 | 2003-07-09 | Knetprodukt aus Al-Cu-Mg-Legierung für das Strukturbauteil eines Flugzeugs |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0208737A FR2842212B1 (fr) | 2002-07-11 | 2002-07-11 | Element de structure d'avion en alliage a1-cu-mg |
FR0208737 | 2002-07-11 |
Publications (3)
Publication Number | Publication Date |
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EP1382698A1 EP1382698A1 (de) | 2004-01-21 |
EP1382698B1 true EP1382698B1 (de) | 2004-05-26 |
EP1382698B2 EP1382698B2 (de) | 2013-01-09 |
Family
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Application Number | Title | Priority Date | Filing Date |
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EP03356108A Expired - Lifetime EP1382698B2 (de) | 2002-07-11 | 2003-07-09 | Knetprodukt aus Al-Cu-Mg-Legierung für das Strukturbauteil eines Flugzeugs |
Country Status (6)
Country | Link |
---|---|
US (2) | US7294213B2 (de) |
EP (1) | EP1382698B2 (de) |
AT (1) | ATE267885T1 (de) |
DE (1) | DE60300004T3 (de) |
ES (1) | ES2220902T5 (de) |
FR (1) | FR2842212B1 (de) |
Families Citing this family (22)
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US20050034794A1 (en) * | 2003-04-10 | 2005-02-17 | Rinze Benedictus | High strength Al-Zn alloy and method for producing such an alloy product |
WO2004090185A1 (en) | 2003-04-10 | 2004-10-21 | Corus Aluminium Walzprodukte Gmbh | An al-zn-mg-cu alloy |
US7883591B2 (en) * | 2004-10-05 | 2011-02-08 | Aleris Aluminum Koblenz Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
RU2455529C2 (ru) * | 2006-04-29 | 2012-07-10 | Ёрликон Лайбольд Вакуум Гмбх | Ротор или статор турбомолекулярного насоса |
US8608876B2 (en) | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
US8002913B2 (en) * | 2006-07-07 | 2011-08-23 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
DE602008002822D1 (de) * | 2007-03-14 | 2010-11-11 | Aleris Aluminum Koblenz Gmbh | Al-cu-legierungsprodukt, das für die luft- und raumfahrtanwendung geeignet ist |
WO2010042498A1 (en) * | 2008-10-10 | 2010-04-15 | Gkn Sinter Metals, Llc | Aluminum alloy powder metal bulk chemistry formulation |
CA2750394C (en) | 2009-01-22 | 2015-12-08 | Alcoa Inc. | Improved aluminum-copper alloys containing vanadium |
SI3141624T1 (sl) | 2011-09-16 | 2021-11-30 | Ball Corporation | Udarno iztiskani vsebniki iz recikliranega odpadnega aluminija |
CN102732849A (zh) * | 2012-06-29 | 2012-10-17 | 武汉理工大学 | 镁合金与铝合金表面改性处理及高强连接的方法 |
CN107985713A (zh) | 2013-04-09 | 2018-05-04 | 鲍尔公司 | 由再循环的铝和增强的合金制造的具有带螺纹的颈部的冲挤的铝瓶 |
CN104711498B (zh) * | 2013-12-13 | 2016-09-07 | 天津大学 | 高强度铝合金二次拉伸成型中表面橘皮效应的控制方法 |
CN104451298A (zh) * | 2014-11-19 | 2015-03-25 | 无锡鸿声铝业有限公司 | 一种改进的2024铝合金 |
DE102016205221A1 (de) * | 2016-03-30 | 2017-10-05 | Sms Group Gmbh | Vorrichtung und Verfahren zum Plattieren einer warmen Bramme |
US20180044155A1 (en) | 2016-08-12 | 2018-02-15 | Ball Corporation | Apparatus and Methods of Capping Metallic Bottles |
CA3032261A1 (en) | 2016-08-26 | 2018-03-01 | Shape Corp. | Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component |
EP3529394A4 (de) | 2016-10-24 | 2020-06-24 | Shape Corp. | Mehrstufiges formen von aluminiumlegierungen und thermisches behandlungsverfahren zur herstellung von fahrzeugkomponenten |
BR122020012460B1 (pt) | 2016-12-30 | 2022-09-06 | Ball Corporation | Liga de alumínio, método para produzir um recipiente e recipiente |
MX2019009745A (es) | 2017-02-16 | 2020-02-07 | Ball Corp | Aparato y metodo para formar y aplicar tapas a prueba de robo giratorias en cuellos roscados de contenedores de metal. |
US11185909B2 (en) | 2017-09-15 | 2021-11-30 | Ball Corporation | System and method of forming a metallic closure for a threaded container |
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 |
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GB1133113A (en) * | 1965-02-05 | 1968-11-06 | Aluminum Co Of America | Improvements in forged aluminium base alloy members |
US3333990A (en) * | 1965-02-05 | 1967-08-01 | Aluminum Co Of America | Aluminum base alloy forgings |
US3826688A (en) * | 1971-01-08 | 1974-07-30 | Reynolds Metals Co | Aluminum alloy system |
US4336075A (en) * | 1979-12-28 | 1982-06-22 | The Boeing Company | Aluminum alloy products and method of making same |
US5137686A (en) * | 1988-01-28 | 1992-08-11 | Aluminum Company Of America | Aluminum-lithium alloys |
JPH03236441A (ja) | 1990-02-14 | 1991-10-22 | Nkk Corp | 高強度アルミニウム合金および高強度アルミニウム合金材の製造方法 |
US5213639A (en) | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
BR9103666A (pt) * | 1990-08-27 | 1992-05-19 | Aluminum Co Of America | Metodo de producao de um produto de folha de liga a base de aluminio e produto feito pelo dito metodo |
GB9021565D0 (en) * | 1990-10-04 | 1990-11-21 | Allied Colloids Ltd | Dewatering compositions and processes |
US5376192A (en) * | 1992-08-28 | 1994-12-27 | Reynolds Metals Company | High strength, high toughness aluminum-copper-magnesium-type aluminum alloy |
FR2704557B1 (fr) | 1993-04-28 | 1995-06-02 | Pechiney Rhenalu | Alliage de revêtement à base d'Al et produit composite plaqué sur alliages 2000 ou 6000. |
FR2731440B1 (fr) * | 1995-03-10 | 1997-04-18 | Pechiney Rhenalu | Toles en alliage al-cu-mg a faible niveau de contraintes residuelles |
US5879475A (en) * | 1995-03-22 | 1999-03-09 | Aluminum Company Of America | Vanadium-free, lithium-free aluminum alloy suitable for forged aerospace products |
US5652063A (en) * | 1995-03-22 | 1997-07-29 | Aluminum Company Of America | Sheet or plate product made from a substantially vanadium-free aluminum alloy |
US5630889A (en) * | 1995-03-22 | 1997-05-20 | Aluminum Company Of America | Vanadium-free aluminum alloy suitable for extruded aerospace products |
US6077363A (en) * | 1996-06-17 | 2000-06-20 | Pechiney Rhenalu | Al-Cu-Mg sheet metals with low levels of residual stress |
FR2792001B1 (fr) * | 1999-04-12 | 2001-05-18 | Pechiney Rhenalu | Procede de fabrication de pieces de forme en alliage d'aluminium type 2024 |
JP2001330757A (ja) * | 2000-05-23 | 2001-11-30 | Yazaki Corp | 光コネクタ |
US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
-
2002
- 2002-07-11 FR FR0208737A patent/FR2842212B1/fr not_active Expired - Fee Related
-
2003
- 2003-07-07 US US10/612,878 patent/US7294213B2/en active Active
- 2003-07-09 DE DE60300004T patent/DE60300004T3/de not_active Expired - Lifetime
- 2003-07-09 ES ES03356108T patent/ES2220902T5/es not_active Expired - Lifetime
- 2003-07-09 AT AT03356108T patent/ATE267885T1/de not_active IP Right Cessation
- 2003-07-09 EP EP03356108A patent/EP1382698B2/de not_active Expired - Lifetime
-
2007
- 2007-10-01 US US11/865,300 patent/US7993474B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
FR2842212A1 (fr) | 2004-01-16 |
DE60300004T2 (de) | 2005-01-20 |
ES2220902T3 (es) | 2004-12-16 |
DE60300004D1 (de) | 2004-07-01 |
US7294213B2 (en) | 2007-11-13 |
US7993474B2 (en) | 2011-08-09 |
EP1382698A1 (de) | 2004-01-21 |
EP1382698B2 (de) | 2013-01-09 |
US20080210350A1 (en) | 2008-09-04 |
ES2220902T5 (es) | 2013-05-09 |
US20040086418A1 (en) | 2004-05-06 |
DE60300004T3 (de) | 2013-06-20 |
ATE267885T1 (de) | 2004-06-15 |
FR2842212B1 (fr) | 2004-08-13 |
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