Products made of aluminum alloy with high resistance to damage, in particular for use in the aerospace industry

摘要

1. the product of the deformable aluminum alloy with high strength and high fatigue strength and u0432u00a0u0437u043au043eu0441u0442u044cu044e u0440u0430u0437u0440u0443u0448u0435u043du0438u00a0 and low speed growth u0443u0441u0442u0430u043bu043eu0441u0442u043du044b the cracks with mas.%.;cu from 4.4 to 5.5.;mg from 0.3 to 1.0, so 1.1 [mg] + 5.38 [cu] 5.5;fe 0.20;if 0.20;zn 0.40;and mn in the range from 0.15 to 0.8 as the element u0434u0438u0441u043fu0435u0440u0441u043eu0438u0434u043eu043eu0431u0440u0430u0437u043eu0432u0430u0442u0435u043bu00a0 in combination with one or more of the elements selected from the group u0434u0438u0441u043fu0435u0440u0441u043eu0438u0434u043eu043eu0431u0440u0430u0437u043eu0432u0430u0442u0435u043bu0435u0439, with u043eu0441u0442u043eu00a0u0449u0435u0439 of;Zr 0.5;for 0.7;cr 0.4;Hf 0.3;ag 1.0;ti 0.4;v 0.4;and the rest of the u0441u043eu0441u0442u0430u0432u043bu00a0u044eu0442 aluminum and other impurities and incidental elements.;2. the product of the deformable aluminum alloy 1, in which the;cu from 4.4 to 5.5.;mg from 0.35 to 0,78,;with 1.1 [mg] + 5.38 [cu] 5.5.;3. the product of the deformable aluminum alloy 1, in which the;cu from 4.4 to 5.35.;mg from 0.45 to 0.75.;and the - 1 [mg] + 5.15 [cu] 5.35.;4. the product of the deformable aluminum alloy 1, in which the;cu from 4.4 to 5.5.;mg from 0.45 to 0.75.;and the - 0.90 [mg] + 5,60 [cu] 5.5.;5. the product of the deformable aluminum alloy on paragraph 4, in which the content of Cu5,35%.;6. the product of the deformable aluminum alloy on any of the u043fu043f.1 - 5, in which the content of Zr u043du0430u0445u043eu0434u0438u0442u0441u00a0 ranging up to 0.3%, preferably in the range of up to 0.15%.;7. the product of the deformable aluminum alloy 1, in which the content of mn u043du0430u0445u043eu0434u0438u0442u0441u00a0 range less than 0.40%, preferably in the range from 0.20 to 0.35%.;8. the product of the deformable aluminum alloy 1, in which the content of ag u043du0430u0445u043eu0434u0438u0442u0441u00a0 ranging up to 0.6%, preferably in the range from 0.25 to 0.50% or more preferably, ranging from 0.32 to 0.48%.;9. the product of the deformable aluminum alloy 1, in which the content of cr u043du0430u0445u043eu0434u0438u0442u0441u00a0 ranging up to 0.30%, preferably in the range of up to 0.15%.;10. the product of the deformable aluminum alloy p.9, in which alloy essentially contains no Zr.;11. the product of the deformable aluminum alloy 1, in which the content of zn u043du0430u0445u043eu0434u0438u0442u0441u00a0 ranged from 0.10 to 0.25%.;12. the product of the deformable aluminum alloy 1, and the product u043du0430u0445u043eu0434u0438u0442u0441u00a0 in the form of sheet, plate, forgings or pressing u0434u043bu00a0 u043fu0440u0438u043cu0435u043du0435u043du0438u00a0 design air l u0435u0442u0430u0442u0435u043bu044cu043du043eu0433u043e apparatus.;13. the product of the deformable aluminum alloy 1, and the product u043fu0440u0435u0434u0441u0442u0430u0432u043bu00a0u0435u0442 a leaf u0444u044eu0437u0435u043bu00a0u0436u0430, stove top surface of the wing, the lower surface of the slab dug, thick slab u0434u043bu00a0 of machining parts, u043fu043eu043au043eu0432u043au0443 or thin sheet u0434u043bu00a0 u0441u0442u0440u0438u043du0433u0435u0440u043eu0432.;14. the product of the deformable aluminum alloy 1, and the product u043du0430u0445u043eu0434u0438u0442u0441u00a0 as u0438u0437u0434u0435u043bu0438u00a0 - plate with a thickness in the range from 12 to 76 mm.;15. method u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 having high durability and high u0432u00a0u0437u043au043eu0441u0442u044cu044e u0438u0437u0434u0435u043bu0438u00a0 u0430u04302000 series of aluminium alloy with good characteristics of resistance to p. u043eu0432u0440u0435u0436u0434u0435u043du0438u00a0u043c, comprising the following technological steps: u0441u0435u0431u00a0;(a) the casting ingot with the chemical composition of any of the u043fu043f.1 - 11.;(b) u0433u043eu043cu043eu0433u0435u043du0438u0437u0430u0446u0438u00a0 and / or pre heating ingots after u043bu0438u0442u044cu00a0;;(c) u0433u043eu0440u00a0u0447u0430u00a0 processing bars pressure pre deformed blank.;(d) u043du0435u043eu0431u00a0u0437u0430u0442u0435u043bu044cu043du044bu0439 re heating the pre deformed billets and the like;;(e) u0433u043eu0440u00a0u0447u0430u00a0 and / or u0445u043eu043bu043eu0434u043du0430u00a0 processing pressure to the u043fu043eu043bu0443u0447u0435u043du0438u00a0 u0444u043eu0440u043cu043eu0432u0430u043du043du043eu0439 desirable form.;(f) heat treatment at solid solution u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 u0444u043eu0440u043cu043eu0432u0430u043du043du043eu0439 billets at a temperature and for a sufficient time, u0434u043bu00a0 transfer in solid solution on the merits all the soluble components in the mixture.;(g) subjected to solid solution hardening heat billets through a hardening or tempering water immersion in water or other u0437u0430u043au0430u043bu043eu0447u043du0443u044e among du;;(h) u043du0435u043eu0431u00a0u0437u0430u0442u0435u043bu044cu043du043eu0435 u0440u0430u0441u0442u00a0u0436u0435u043du0438u0435 or compression forged billets.;(i) the ageing of hardened and u043du0435u043eu0431u00a0u0437u0430u0442u0435u043bu044cu043du043e u0440u0430u0441u0442u00a0u043du0443u0442u043eu0439 or compressed to the desired u0441u043eu0441u0442u043eu00a0u043du0438u00a0 u0434u043eu0441u0442u0438u0436u0435u043du0438u00a0 billets.;16. method for u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 p.15, in which the product of the alloy subjected to aging to u0441u043eu0441u0442u043eu00a0u043du0438u00a0, selected from the group consisting of u0441u0435u0431u00a0 t3, T351, T352, T36, T3x, t4, t6, T61, T62, T6x, T651, T652, t 87, T89, T8x.;17. method for u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 p.15 or 16, in which the product of the alloy was processed to sheet u0444u044eu0437u0435u043bu00a0u0436u0430 air aircraft.;18. method for u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 p.15 or 16, in which the product of the alloy was processed to the lower surface of the wing plate air aircraft.;19. method for u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 p.15 or 16, in which the product of the alloy was processed to plate the upper surface of the wing of an aircraft.;20. method for u0438u0437u0433u043eu0442u043eu0432u043bu0435u043du0438u00a0 p.15 or 16, in which the product of the alloy was processed to the thick plate with thickness up to 280 mm u0434u043bu00a0 of machining line u0441u0442u0440u0443u043au0446u0438u0439.