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Processing technique for improving fatigue damage resistance of 2XXX series 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: 2016-05-25
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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  • Processing technique for improving fatigue damage resistance of 2XXX series aluminum alloy plate
  • Processing technique for improving fatigue damage resistance of 2XXX series aluminum alloy plate
  • Processing technique for improving fatigue damage resistance of 2XXX series 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 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-rolled plate is kept at 290°C for 4h, and then undergoes solution quenching at 496°C / 50min, straightening treatment and natural aging for more than 96h. The process flow is as follows 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 the cold final rolling plate is kept at 270°C for 8h, then solution quenched at 496°C / 25min, and naturally aged for more than 96h after straightening , the process such as 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 the cold final rolling plate is kept at 290°C for 4h, then solution quenched at 496°C / 25min, and naturally aged for more than 96h after straightening treatment , the process such as 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 a processing technique for improving fatigue damage resistance of a 2XXX series aluminum alloy plate, comprising the following steps: (1), burdening and smelting an alloy, and casting to obtain an ingot; (2), subjecting the ingot sequentially to homogenizing, surface milling and aluminum cladding, and preheating to obtain a hot roughed plate; (3), subjecting the hot roughed plate to hot finishing and cold rolling deformation to finished plate thickness; (4), carrying out recovery pre-annealing at 250-320 DEG C, and holding the temperature for 2-20 h; (5), carrying out solid solution quenching at 480-505 DEG C, and holding the temperature for 3-60 min; (6), straightening a plate, and naturally ageing to a stable state. By adding the recovery pre-annealing treatment, it is possible to effectively control grain average equivalent diameter and grain length-width ratio of L-ST section of the plate, so that both tensile mechanical property of the plate and fatigue crack growth rate thereof meet the requirements of AMS 4296 aviation standards.

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): C22F1/057
CPCC22F1/057
Inventor 刘成金滨辉熊明华李伟罗海云王正安
Owner CHINALCO MATERIALS APPL RES INST CO LTD
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