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Machining technology for improving fatigue damage resisting performance of 2xxx aluminum alloy plate

A technology of anti-fatigue damage, aluminum alloy plate, applied in the field of non-ferrous metal material engineering, to achieve a wide range of applications

Active Publication Date: 2016-04-13
CHINALCO MATERIALS APPL RES INST CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there are few reports on the influence of grain morphology and size on the fatigue crack growth rate of plates and the methods of controlling the grain morphology and size of plates.

Method used

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  • Machining technology for improving fatigue damage resisting performance of 2xxx aluminum alloy plate
  • Machining technology for improving fatigue damage resisting performance of 2xxx aluminum alloy plate
  • Machining technology for improving fatigue damage resisting performance of 2xxx aluminum alloy plate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] According to the element ratio of 4.32wt.% Cu, 1.35wt.% Mg, 0.61wt.% Mn, 0.08wt.% Fe, 0.06wt.% Si, 0.03wt.% Ti, the 2524 aluminum alloy with a size of 400×1620×2500mm was cast Ingot. The alloy ingot is subjected to 498°C / 32h homogenization treatment, face milling, aluminum cladding, 480°C / 8h preheating, and then hot rough rolling at 480°C, followed by hot finish rolling to 6.0mm, and then recrystallization pre-annealing For treatment, the hot finish-rolled sheet is heated to 350°C at an average rate of 36°C / h or 9h to 350°C, and then kept at a temperature of 4h, followed by solution quenching at 496°C / 50min, straightening treatment and natural aging for more than 96h, process such as figure 1 shown. Test the tensile mechanical properties of the final finished plate, and test the fatigue crack growth rate of the plate according to GB / T6398-2000 and AMS4296 standards.

Embodiment 2

[0038] According to the element ratio of 4.32wt.% Cu, 1.35wt.% Mg, 0.61wt.% Mn, 0.08wt.% Fe, 0.06wt.% Si, 0.03wt.% Ti, the 2524 aluminum alloy with a size of 400×1620×2500mm was cast Ingot. The ingot was subjected to 498°C / 32h homogenization treatment, face milling, aluminum cladding, 480°C / 8h preheating, and then hot rough rolling at 480°C, followed by hot finish rolling to 6.0mm. The hot finish rolling plate is deformed to 2.5mm by cold final rolling at a reduction rate of 58%, and then recrystallized and pre-annealed, and the temperature is raised to 340°C at an average rate of 63°C / h or 5h to 340°C, and kept for 4h , and then through 496 ℃ / 25min solution quenching, and after straightening treatment, natural aging for more than 96h, the process flow is as follows figure 2 shown. Test the mechanical properties of the final finished plate, and test the fatigue crack growth rate of the plate according to GB / T6398-2000 and AMS4296 standards.

Embodiment 3

[0040] According to the element ratio of 4.32wt.% Cu, 1.35wt.% Mg, 0.61wt.% Mn, 0.08wt.% Fe, 0.06wt.% Si, 0.03wt.% Ti, the 2524 aluminum alloy with a size of 400×1620×2500mm was cast Ingot. The ingot was subjected to 498°C / 32h homogenization treatment, face milling, aluminum cladding, 480°C / 8h preheating, and then hot rough rolling at 480°C, followed by hot finish rolling to 6.0mm. The hot finish rolling plate is deformed to 2.5mm by cold final rolling at a reduction rate of 58%, and then recrystallized and pre-annealed, and the temperature is raised to 340°C at an average rate of 150°C / h or to 340°C after 2.1h, and kept 4h, and then 496℃ / 25min solution quenching, and after straightening treatment, natural aging for more than 96h, the process flow is as follows figure 2 shown. Test the mechanical properties of the final finished plate, and test the fatigue crack growth rate of the plate according to GB / T6398-2000 and AMS4296 standards.

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Abstract

The invention relates to a machining technology for improving the fatigue damage resisting performance of a 2xxx aluminum alloy plate. The machining technology comprises the following steps that 1, alloy is subjected to burdening smelting and is cast into an ingot casting; 2, the ingot casting is sequentially subjected to homogenization treatment, surface milling and aluminum cladding, preheating is carried out, and a hot rough-rolled plate is manufactured; 3, the hot rough-rolled plate is subjected to hot finishing and cold rolling deformation to the thickness of the finished plate; 4, recrystallization pre-annealing treatment is carried out, temperature is raised to 300-450 DEG C at the average speed of 10-300 DEG C / h or within 1.0-45 h, and heat preservation is carried out for 1-20 h; 5, solid solution hardening treatment is carried out, the solid solution temperature is 480-505 DEG C, and heat preservation time is 3-60 min; and 6, the plate is straightened, and natural ageing is carried out to the stable state. According to the machining technology, recrystallization pre-annealing treatment is added so that the L-ST section grain average equivalent diameter and grain length-width ratio of the plate can be effectively controlled, and the tensile mechanical property and fatigue crack spreading rate of the plate can both meet the AMS 4296 aviation standard requirement.

Description

technical field [0001] The invention relates to a processing technology for improving the anti-fatigue damage performance of 2××× series aluminum alloy plates, which belongs to the field of nonferrous metal material engineering. Background technique [0002] With the development of the aviation industry, higher requirements are put forward for materials. As an aircraft skin, the aluminum alloy sheet must not only meet the strength requirements, but also be required to have the characteristics of safety, reliability and long life. This requires that the aluminum alloy skin material for aircraft not only meets the strength requirements, but also takes into account the performance requirements of high fracture toughness and fatigue damage resistance. [0003] In 1995, Alcoa developed the 2524 aluminum alloy for aircraft skin, and stipulated in the AMS4296 aviation standard: For 2524-T3 plates with a thickness ≥ 1.57mm, the yield strength, tensile strength and elongation are not...

Claims

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Application Information

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IPC IPC(8): C22F1/057C22C21/16C22C21/14
CPCC22C21/14C22C21/16C22F1/057
Inventor 刘成金滨辉熊明华罗海云李登谚王正安
Owner CHINALCO MATERIALS APPL RES INST CO LTD
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