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Processing technology for improving fatigue damage resistance of 2xxx series aluminium alloy plate

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

Active Publication Date: 2016-03-30
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 technology for improving fatigue damage resistance of 2xxx series aluminium alloy plate
  • Processing technology for improving fatigue damage resistance of 2xxx series aluminium alloy plate
  • Processing technology for improving fatigue damage resistance of 2xxx series aluminium alloy plate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] 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, then hot rough rolling at 480°C to 20mm, followed by hot finish rolling to 6.0mm, and then 496°C / 50min solution quenching, straightening treatment and natural aging for more than 96h, the process flow is as follows figure 1 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 2

[0034] 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 4.0mm by cold final rolling at a reduction rate of 33%, and then solution quenched at 496°C / 25min, and naturally aged for more than 96h after straightening treatment. 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

[0036]According to the element ratio of 4.28wt.% Cu, 1.30wt.% Mg, 0.60wt.% 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 / 30h homogenization treatment, face milling, aluminum cladding, 485°C / 8h preheating, and then hot rough rolling at 485°C, followed by hot finish rolling to 4.5mm. The hot finish rolling plate is cold-rolled at a reduction rate of 56% to 2.0mm, then subjected to intermediate annealing at 340°C / 4h and cold-rolled at a reduction rate of 40% to deform to 1.2mm, and then subjected to intermediate annealing at 340°C / 4h and pressed 33% cold final rolling deformation to 0.8mm, and solution quenching at 498°C / 16min, and then natural aging for more than 96h after straightening treatment, the process flow is as follows image 3 shown. Test the mechanical properties of the final finished plate, and test the fatigue crack growth rate of the plate according to GB / T6398-20...

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Abstract

The invention relates to a processing technology for improving fatigue damage resistance of a 2xxx series aluminium alloy plate. The processing technology comprises the following steps that (1) an alloy is subjected to batching and smelting and is cast to form an ingot; (2) the ingot is sequentially subjected to homogenizing treatment, face milling, aluminium cladding and preheating, and is made into a hot rough-rolled plate; (3) the hot rough-rolled plate is subjected to hot finish rolling, different technologies are implemented according to the plates requiring different exit thicknesses, and a cold final rolling reduction rate of the plate is controlled; (5) solid solution quenching treatment is carried out with the solid solution temperature being 480-505 degrees and the heat preservation time being 3-60min; and (6) the plate is straightened, and is subjected to natural aging till a stable state is reached. By controlling the cold final rolling reduction rate of the plate, the grain average equivalent diameter and the grain length-width ratio of the L-ST cross section of the plate can be controlled effectively, and the tensile mechanical property and the fatigue-crack propagation speed of the plate can meet the requirements of AMS (Aerospace Material Specification) 4296.

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): C22F1/057C22C21/14C22C21/16
CPCC22C21/14C22C21/16C22F1/002C22F1/057
Inventor 刘成金滨辉熊明华肖翔罗海云王正安
Owner CHINALCO MATERIALS APPL RES INST CO LTD
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