Si: 0.7-1.3; Mg: 0.6-1.1; Cu: 0.5-1.1; Mn: 0.3-0.8; Zn<1 Fe<0.30; Zr<0.20; Cr<0.25; other elements <0.05 each and <0.15 in total; remainder aluminum. The product is treated by steps of:
solution heat treatment of the product between 540 and 570° C.;
quenching the solution heat treated product;
producing the structural component by forming of the product, and welding if required;
ageing of the structural component, in one or more stages, for which the total equivalent time at 175° C. expressed in hours is between (−160+57γ) and (−184+69γ), γ being the sum of Si+2Mg+2Cu contents in % by weight. The invention results in an improvement in tolerance to damage with no loss of other operating parameters.
[0001] The invention relates to the field of rolled, extruded or forged products made of series 6000 Al—Si—Mg aluminum alloy according to Aluminum Association references, intended to produce aircraft structural components, particularly fuselage components.
[0002] 2. Description of Related Art
[0003] Commercial aircraft fuselages are mostly produced using 2024 T3 or T351 alloy sheets, clad on both sides with a low content aluminum alloy, for example a 1050 or 1070 alloy, in order to improve corrosion resistance. The thickness of the cladding may represent, depending on the thickness of the core sheet, between 2 and 12% of the total thickness.
[0004] Several years ago, it was proposed to use series 6000 Al—Si—Mg alloys for fuselage panels instead of 2024 alloys or similar alloys. These alloys, also heat-treated, offer good mechanical characteristics when treated, a high modulus of elasticity and a lower density than 2024. The alloys are easier to weld, enabling a reduction in the number of riveted assemblies, which are a source of additional cost, and also sites in which stress is concentrated and corrosion initiated.
[0005] The patent U.S. Pat. No. 4,589,932 (Alcoa) discloses the use, for aircraft structural components, of an alloy subsequently registered under the reference 6013, with the following composition (% by weight):
[0006] Si: 0.4-1.2 Mg: 0.5-1.3 Cu: 0.6-1.1 Mn: 0.1-1 Fe<0.6
[0007] The patent EP 0 173 632, filed by the applicant, discloses an alloy, subsequently registered under the reference 6056, with the following composition:
[0008] Si: 0.9-1.2 Mg: 0.7-1.1 Cu: 0.3-1.1 Mn: 0.25-0.75 Zn: 0.1-0.7 Zr: 0.07-0.2 Fe<0.3
[0009] The patent EP 0 787 217, also filed by the applicant, relates to a specific ageing treatment, resulting in a T78 temper, for a 6056 type alloy, so as to desensitize it to intercrystalline corrosion, and thus enable its use without cladding for aircraft fuselages. This ageing is defined by a total duration, measured in equivalent time at 175° C., between 30 and 300 hours, and preferentially between 70 and 120 hours. This development was the subject of a presentation by R. Dif, D. Béchet, T. Warner and H. Ribes: “6056 T78: A corrosion resistant copper-rich 6xxx alloy for aerospace applications” at the ICAA-6 congress (July 1998) in Toyohashi (Japan) and published in the Congress Proceedings, pages 1991-1996.
[0010] The parts are preferentially shaped in the T4 temper, wherein the 6056 alloy shows excellent forming properties. The ageing is performed on shaped and possibly welded parts. The use of 6056-T78 results in complete desensitisation to intercrystalline corrosion of the welded join or the base product and in static mechanical characteristics equivalent to those of clad T3 or T351 2024. However, it seemed desirable to improve the results obtained in terms of tolerance to damage, while retaining the static mechanical properties and desensitization to intercrystalline corrosion.
[0011] The invention relates to an aircraft structural component production method using rolled, extruded or forged products made of aluminum alloy comprising:
[0012] the casting of a blank with the following composition (% by weight):
[0013] Si: 0.7-1.3 Mg: 0.6-1.1 Cu: 0.5-1.1 Mn: 0.3-0.8 Zn<1 Fe<0.30 Zr<0.20 Cr<0.25 other elements <0.05 each and <0.15 in total, the remainder being aluminum,
[0014] hot, and possibly cold, transformation of said blank to produce a product,
[0015] solution heat treatment of the product between 540 and 570° C.,
[0016] quenching of said product,
[0017] production of the structural component by forming of the product, and welding if required,
[0018] ageing of the structural component, in one or more stages, for which the total equivalent time at 175° C. expressed in hours is between (−160+57γ) and (−184+69γ), γ being the sum of the Si+2Mg+2Cu contents in % by weight.
[0019] The invention also relates to an aircraft structural component production method, wherein the composition of the products belongs to a preferential composition range (% by weight):
[0020] Si: 0.7-1.1 Mg: 0.6-0.9 Cu: 0.5-0.7 Mn: 0.3-0.8 Zr<0.2 Fe<0.2 Zn<0.5 Cr<0.25 Mg/Si<1, Si+2 Mg: 2-2.6 other elements <0.05 each and <0.15 in total, the remainder being aluminum,
[0021] and the ageing time is between 40 and 65 hours of total equivalent time at 175° C.
[0022] It also relates to an aircraft fuselage component produced using products with the preferential composition given above.
[0023]
[0024]
[0025] The invention is based on the observation that within the composition and ageing range disclosed in the patent EP 0 787 217, there is a restricted range linking the major elements of the composition (Si, Mg and Cu) and the total equivalent ageing time at 175° C., as this parameter is defined in EP 0 787 217; with this range, in relation to the results given in the examples of this European patent, an improvement in the static mechanical characteristics and tolerance to damage is obtained, with no adverse effect on sensitivity to intercrystalline corrosion. It is thus possible to associate with each alloy composition a factor γ equal to the sum of the Si+2Mg+2Cu contents (in % by weight) and with said factor γ a period of equivalent ageing time at 175° C. between (in hours) (−160+57γ) and (−184+69γ) and preferentially between (−150+57γ) and (−184+69γ).
[0026] More specifically, the inventors revealed that by unloading the alloy in relation to compositions of the examples in the European patent, i.e. by positioning at the lower end of the content ranges for these 3 elements, while ensuring that these elements are put in solution as completely as possible, the alloy became less sensitive to intercrystalline corrosion at given over-ageing and that, as a result, it was possible to desensitize it with a lower level over-ageing.
[0027] In this way, in the preferential composition range mentioned above, with particularly Cu<0.7% and Si+2Mg<2.6%, the equivalent ageing time at 175° C. to reach the T78 temper with total desensitization is between 40 and 65 hours, i.e. below the preferential range (70 to 120 hours) indicated in the patent EP 0 787 217. However, to obtain a sufficient mechanical resistance, it is necessary to maintain Cu>0.5% and Si+2Mg>2.0 and preferentially >2.3%.
[0028] In this preferential composition range, associated with T78 ageing for an equivalent time at 175° C. between 40 and 65 hours, it is possible to obtain, in addition to complete desensitization to intercrystalline corrosion, the following level of properties in terms of static mechanical characteristics, toughness and crack growth:
[0029] a yield strength R
[0030] a plane strain fracture toughness, measured in the T-L direction, according to the ASTM E561 standard, such that at least one of the following properties is verified:
[0031] K
[0032] K
[0033] K
[0034] K
[0035] The measurements are made on a CCT test specimen of width W=760 mm and initial cracking length 2a
[0036] a fracture toughness in the L-T direction, measured under the same conditions as that in the T-L direction, such that at least one of the following properties is verified:
[0037] K
[0038] K
[0039] a crack growth rate da/dn, measured in the T-L direction according the ASTM E647 standard for R=0.1 on a CCT type test specimen of width W=160 mm, less than:
[0040] 2 10
[0041] 4 10
[0042] 8 10
[0043] Finally, in this particular T78 temper, a lower drop in the fatigue resistance after prolonged exposure in a corrosive environment is observed in relation to the T6 temper.
[0044] This set of properties, associated with the fact that the alloy can be welded, makes it particularly suitable for the production of aircraft structural components, particularly fuselage components.
[0045] It is also possible to use the alloy, in the preferential composition according to the invention, in the T6 temper. The level of properties obtained in said T6 temper with the preferential composition according to the invention, in terms of static mechanical characteristics, fracture toughness and crack growth rate is as follows:
[0046] a yield strength R
[0047] a fracture toughness, measured under the same conditions as for the T78 temper mentioned above, such that at least one of the following properties is verified:
[0048] K
[0049] K
[0050] K
[0051] K
[0052] a fracture toughness measured in the L-T direction under the same conditions, such that at least one of the following properties is verified:
[0053] K
[0054] K
[0055] a crack growth rate da/dn, measured under the same conditions as for the T78 temper, less than:
[0056] 2 10
[0057] 4 10
[0058] 8 10
[0059] This set of properties, associated with the fact that the alloy can be welded, makes the product particularly suitable for the production of aircraft fuselage components.
[0060] The production method according to the invention comprises the casting of a blank made of the composition mentioned, said blank being a plate for rolled products, a slug for extruded products or a forging block for forged products. The blank is scalped and then heated before hot transformation by rolling, extrusion or forging, and possibly undergoes cold transformation. After cutting in the required format, the semi-finished product obtained undergoes a heat treatment at a temperature between 540 and 570° C., quenched, generally in cold water, and finished, the purpose of said final step essentially being to absorb the deformations of the semi-finished product after quenching. The product is most frequently supplied in this T4 temper to shape the structural component and for welding if required. The formed, and if applicable welded, component then undergoes the ageing treatment according to the invention.
[0061] The applicant observed that it is advantageous to add, before scalping, a homogenization step at a temperature between 540 and 570°. Said homogenization may comprise a single stage, or two stages, the second stage being at a higher temperature than the first. It helps improve the forming properties of the product in the T4 temper and reduce the grain size, leading to a decrease in the roughness of the metal when it undergoes chemical machining. Excessive roughness may induce initial micro-cracking due to fatigue.
[0062] In addition, the tests demonstrated that the desensitization to intercrystalline corrosion increases in effectiveness with the level of cold-working in the T4 temper. This cold-working may be a result of finishing operations such as straightening or planing with rollers or traction for sheets and traction or drawing for profiles. It may also be the result of part forming operations by rolling, drawing-forming, embossing, flow turning or folding. Said cold-working, of at least 1%, and preferably of at least 2% permanent elongation, may be relatively significant, for example up to 10%, or even up to 15% permanent elongation; indeed, it is observed, surprisingly, that significant cold-working, although it accelerates the ageing kinetics, does not reduce the yield strength in the T78 temper with reference to the same non-cold-worked product.
[0063] This possibility to use significant cold-working improving the resistance to intercrystalline corrosion is particularly useful if, as is frequently the case for aircraft fuselage production, thin sheets and profiles must be assembled. Indeed, the applicant observed that desensitization to intercrystalline corrosion is more difficult to carry out on profiles than on sheets, probably due to the difference in their metallurgic structure. If the sheets and profiles are formed separately, and then welded before ageing, this is liable to induce a difference in corrosion resistance between the sections produced from profiles and those produced from sheets. To remedy this disadvantage, rather than choose a very high level of ageing to desensitize the profiles, which would induce a significant loss of mechanical resistance, it is preferable to retain the T78 ageing adapted to the desensitization of the sheets and to subject the profiles to an additional cold-working step to bring their resistance to intercrystalline corrosion to the same level as those of thin sheets.
[0064] A plate of the composition (% by weight) corresponding to Example 3 of the patent EP 0 787 217 was cast, i.e.: Si: 0.92 Mg: 0.86 Cu: 0.87 Mn: 0.55 Fe: 0.19 Zn: 0.15 Zr: 0.10 i.e. Mg/Si=0.93 and Si+2Mg=2.64.
[0065] The plate was heated at 530° C., scalped, hot and then cold rolled to a thickness of 3.2 mm. Samples of the sheet obtained were subjected to a solution heat treatment at 550° C., quenched in water, finished and subjected to ageing. In some cases, the ageing lasted 8 hours at 175° C. to obtain the T6 temper, i.e. the temper corresponding to maximum mechanical resistance; in other cases, it lasted 6 hours at 175° C. and then 2 hours at 220° C., or an equivalent time at 175° C. of 95 hours, to obtain the T78 temper, as described in Example 3 of the patent EP 0 787 217.
[0066] The mechanical characteristics were measured in the TL direction, i.e. the tensile strength Rm (in MPa), the conventional yield strength at 0.2% elongation RTABLE 1 IC Temper R R A (TL) sensitivity T6 364 408 7 Yes T78 304 343 8 No
[0067] For the T78 temper, the fracture toughness was also measured using the R curve method, according to the ASTM E 561 standard. The test, performed on a CCT type test specimen of width W=760 mm and central cracking length 2a
[0068] The R curve is also used, for example using L. Schwarmann's method mentioned above, to determine by calculation the plane strain toughnesses KTABLE 2 K K K K K K Temper Δa = 20 mm Δa = 40 mm (T-L) (T-L) (L-T) (L-T) T78 89.5 107.5 75.2 105.9 88.8 137.8
[0069] The fatigue crack growth was also measured in the T78 temper in the T-L direction (in mm/cycle) for R=0.1 (ratio between minimal and maximal stress) and for different values of ΔK (in MPa{square root}m) according to the ASTM E 647 standard. The results, obtained on CCT type test specimens of width W=160 mm, are given in Table 3:
TABLE 3 Temper ΔK = 20 MPa{square root}m ΔK = 25 MPa{square root}m ΔK = 30 MPa{square root}m T78 10 3 10 6.3 10
[0070] A plate of a composition included in the preferential composition of the present invention was cast: Si=0.93 Mg=0.75 Cu=0.60 Mn=0.63 Fe=0.10 Zn=0.16 which corresponds to Mg/Si=0.81 and Si+2Mg=2.43.
[0071] The plate was transformed under the same conditions as in Example 1, except in terms of the ageing in the T78 temper. Part of the samples underwent ageing for 6 hours at 175° C. followed by 5 hours at 210° C., or a total equivalent time at 175° C. of 105 hours, according to the preferential disclosure in the patent EP 0787217. Another part underwent ageing for 6 hours at 175° C. followed by 13 hours at 190° C., or a total equivalent time at 175° C. of 55 hours, according to the present invention. The same measurements as in Example 1 were made for the T6 and T78 tempers at 105 hours and 55 hours. The results are given in Tables 4, 5 and 6.
TABLE 4 IC Temper R R A (TL) sensitivity T6 360 397 7.5 Yes T78 305 337 10.5 No (105 hrs) T78 339 367 9.2 No (55 hrs)
[0072] It is observed that ageing for 55 hours equivalent time improves mechanical resistance significantly in relation to that for 105 hours equivalent time, while showing the same desensitization to intercrystalline corrosion.
TABLE 5 K K K K K K Temper Δa = 20 mm Δa = 40 mm (T-L) (T-L) (L-T) (L-T) T6 101.1 126.2 87.9 121.7 104.4 155.1 T78 94.4 119.6 83.1 117.5 91.6 137.9 105 hrs T78 96.5 125 86.9 125.7 55 hrs
[0073] It is observed firstly that, with the same ageing, the variation in composition between Example 1 and Example 2 results in an improvement in fracture toughness, irrespective of the measurement parameter used and secondly that, with the same composition, the ageing for 55 hours equivalent time also improves the toughness.
TABLE 6 Temper ΔK = 20 MPa{square root}m ΔK = 25 MPa{square root}m ΔK = 30 MPa{square root}m T6 1.2 10 3 10 5 10 T78 (105 hrs) 10 2 10 4 10 T78 (55 hrs) 1.2 10 3 10 5 10
[0074] It is observed that with the ageing and preferential composition according to the invention, there is no degradation of da/dn between T6 and T78.
[0075] On the same sheets in the T6 and T78 temper, fatigue specimen blanks were removed and exposed for one year to a marine environment on the Mediterranean coast. After machining, the test specimens, showing a strain concentration factor of almost 1, underwent fatigue-endurance tests, to determine the number of fracture cycles, at different levels of strain and a frequency of 30 Hz, for a load ratio R=0.1. The results are represented in
[0076] These results demonstrate the advantage of the T78 treatment with reference to the T6 treatment in terms of the drop in fatigue resistance after exposure to corrosion.
[0077] Three plates made of alloys A, B and C were cast, for which the compositions (by weight %) within the preferential composition range according to the invention and the final rolling thicknesses e, are given in Table 7:
TABLE 7 Alloy E (mm) Si Mg Cu Mn Fe Zn Si + 2 Mg A 1.4-3.2 0.93 0.75 0.60 0.63 0.10 0.16 2.43 B 4-8 0.91 0.76 0.64 0.59 0.13 0.17 2.43 C 4.5-6 0.94 0.80 0.64 0.56 0.10 0.13 2.54
[0078] The plates were transformed in the same way as those in the above examples up to the ageing step, apart from the fact that, for thicknesses greater than or equal to 4.5 mm, given in Table 7, no cold rolling was carried out. The same ageing for 6 hours at 175° C.+13 hours at 190° C., or a total equivalent time at 175° C. of 55 hours, was performed for all the samples. The same measurements as in the above examples were made: static mechanical characteristics (TL direction) RTABLE 8 IC Alloy - th R R A (TL) sensitivity A 1.4 mm 337 363 8.3 No A 3.2 mm 339 367 9.2 No B 4 mm 340 369 9.1 No B 8 mm 345 371 8.9 No C 4.5 mm 337 367 9.4 No C 6 mm 351 379 9.4 No
[0079]
TABLE 9 K K Alloy - th Δa = 20 mm Δa = 40 mm K K A 1.4 mm 90 122.5 85.5 129.7 A 3.2 mm 95.5 125 86.9 125.7 B 8 mm 110 134 93.8 126.1 C 4.5 mm 98.5 121.5 84.9 114.7
[0080]
TABLE 10 Alloy - th ΔK = 20 MPa{square root}m ΔK = 25 MPa{square root}m ΔK = 30 MPa{square root}m A 1.4 mm 1.3 10 2.5 10 5.2 10 A 3.2 mm 1.1 10 3 10 4.8 10 B 8 mm 8 10 2.3 10 4.1 10 C 4.5 mm 1.1 10 2.8 10 4.3 10
[0081] It is observed that, for all the thicknesses, irrespective of whether cold rolling was performed or not, the values measured for the static mechanical characteristics and toughnesses are greater than the minimum values given above for the T78 temper, and the crack growths da/dn are less than the maximum values given above for the same temper.
[0082] An alloy with the following composition (% by weight) was cast: Si=1.01 Mg=0.71 Cu=0.67 Mn=0.55 Fe=0.14 Zn=0.15 remainder aluminum.
[0083] A first plate of this alloy was subjected to the production procedure A comprising the following steps: homogenization for 4 hours at 540° C.+24 hours at 565° C., scalping, heating at 530° C., hot rolling of a strip up to 4.5 mm, conversion of strip into sheets, solution heat treatment in a furnace for 40 min at 550° C. in air, water quenching, finishing, T6 ageing for 8 hours at 175° C.
[0084] A second plate underwent production procedure B comprising the same steps except for the preliminary homogenization. The grain size (thickness e and length l) on the surface and mid-thickness of the sheet was measured in the T4 temper (before ageing) by optical microscopy on a ground section, along with the distribution of the Al—Mn—Si dispersoids in electron microscopy in transmission. This distribution is evaluated with the parameter ECD (Equivalent Circle Diameter)={square root}4A/π wherein A in the area of the phases observed on the microscopic section. To characterize the formability, the parameter LDH (Limit Dome Height) is used. This parameter is defined in the patent application EP 1045043 filed by the applicant. The results are given in Table 11:
TABLE 11 e grain 1 grain e grain 1 grain surface surface mid-th. mid-th. ECD LDH Procedure (μm) (μm) (μm) (μm) (nm) (mm) A 27 143 23 140 271 92 B 40 316 30 320 108 73
[0085] It is observed that, in the T4 temper, i.e. in the temper in which sheets are most frequently delivered to the aeronautic manufacturer for forming, ageing, procedure A with homogenization results in a smaller grain size and therefore lower roughness after chemical machining and improved formability.
[0086] The static mechanical characteristics RTABLE 12 R Procedure (TL) R A (TL) R R A (L) A 361 390 11.3 374 386 12.0 B 359 389 10.5 367 386 12.7
[0087] It is possible to conclude that homogenization does not have a significant effect on the mechanical characteristics in the T6 temper.
[0088] An alloy with the following composition (% by weight) was cast: Si=0.82 Mg=0.68 Cu=0.55 Mn=0.57 Fe=0.13 Zn=0.14 remainder aluminum.
[0089] This plate alloy was subjected to the following production procedure: homogenization for 4 hours at 540° C.+24 hours at 565° C., scalping, heating at 530° C., hot rolling of a strip up to 5 mm, conversion of strip into sheets, solution heat treatment in a furnace for 40 min at 550° C. in air, water quenching, finishing, T78 ageing for 6 hours at 175° C.+13 hours at 190° C. (or 55 hours of equivalent time at 175° C.).
[0090] The static mechanical characteristics RTABLE 13 IC Procedure R R A (TL) sensitivity Homog. + 337 359 11 No T78
[0091]
TABLE 14 K K Temper Δa = 20 mm Δa = 40 mm K K Homog. + 115 142 98.8 136 T78
[0092]
TABLE 15 Temper ΔK = 20 MPa{square root}m ΔK = 25 MPa{square root}m ΔK = 30 MPa{square root}m Homog. + T78 1.1 10 2.1 10 4.0 10
[0093] If these results are compared to those in Table 4 of Example 2, it is noted that, also in the T78 temper, homogenization does not have a significant effect on mechanical characteristics, the crack growth rate or the sensitivity to intercrystalline corrosion, but seems to increase the fracture toughness measured by the R curve.
[0094] Samples were taken from the sheets of Example 3 and Example 5 at different thicknesses and with different types of finishing, comprising at least one of the straightening D, roller planning P or traction planing T operations. In each case, the yield strength RTABLE 16 Alloy R ex. e (mm) Finish T4 R IC sens. 3 A 1.4 D + P + T 218 337 No 3 A 3.2 D + P + T 215 339 No 3 B 4 D + P + T 218 340 No 3 B 8 T 181 345 Slight 3 C 4.5 D + P + T 203 337 No 3 C 6 T 198 351 Slight 5 2.2 D + P + T 179 340 Yes 5 2.2 D + P + T 211 336 Slight 5 2.5 D + P + T 224 332 No 5 2.5 D + P + T 200 330 Slight 5 3.2 D + P + T 245 326 No 5 5 P + T 218 337 No
[0095] The results given in
[0096] Using the sheet corresponding to the seventh row of Table 14 (composition according to Example 5, thickness 2.2 mm), different finishing operations were carried out in the laboratory in the T4 temper consisting of controlled traction to 3.2% permanent elongation and cold rolling to different levels of permanent elongation between 2.6 and 8.7%. The samples obtained in this way were subjected firstly to ageing A for 6 hours at 175° C.+13 hours at 190° C., corresponding to a T78 temper with 55 hours of equivalent time at 175° C. and secondly ageing B for 6 hours at 175° C.+6 hours at 190°, in a slightly over-aged temper with an equivalent time at 175° C. of 31 hours, making it possible exacerbate the sensitivity to intercrystalline corrosion. The yield strength (in MPa) and the elongation (in %) in the TL direction in the T4 temper and the yield strength in the TL direction in the T78 temper after ageing A (Table 17) were measured, along with the sensitivity to intercrystalline corrosion for the ageing steps A and B, indicating the depth of the corrosion (in μm) and extent of the corrosion as a % of the surface affected (Table 18).
TABLE 17 Finishing R R A (T4-TL) None 191 337 24.6 3.2% traction 234 330 21.7 2.6% rolling 235 333 21.4 3.5% rolling 236 332 21.1 5.3% rolling 261 336 18.7 8.7% rolling 285 340 16.4
[0097]
TABLE 18 Ageing A Ageing B IC Depth IC Depth Finishing sensitivity Extent sensitivity Extent None Yes 190 μm-10% Yes 150 μm-20% 3.2% Slight 10 μm Yes 140 μm-1% traction 2.6% Slight 10 μm Yes 190 μm-5% rolling 3.5% No — Yes 125 μm-10% rolling 5.3% No — Yes 25 μm-1% rolling 8.7% No — No — rolling
[0098] The correlation between the yield strength in the T4 temper and the desensitization to intercrystalline corrosion in the T78 temper is again observed. It is also observed that a high cold-working rate does not induce a degradation of the yield strength after ageing, as could be expected, since the ageing kinetics is accelerated.