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2xxx aluminium alloy for aviation and processing method thereof

A processing method and aluminum alloy technology, which is applied in the field of aluminum alloy, aviation 2xxx series aluminum alloy and its processing, can solve the problems affecting material plasticity, fracture toughness, large size, etc., and achieve good comprehensive mechanical properties, good strength and plasticity , optimize the effect of trace elements

Inactive Publication Date: 2009-12-09
苏州有色金属研究院有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But Al 20 Cu 2 mn 3 The effect of controlling grain size will decrease at higher temperature; and Al 20 Cu 2 mn 3 The size of the phase is large, which may affect the plasticity and fracture toughness of the material

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] The composition of the aluminum alloy is calculated by mass percentage: Cu 3.5wt%, Mg 1.3wt%, Mn 0.50wt%, Zr 0.10wt%, Fe 0.10wt%, Si 0.10wt%, Ti 0.15wt%, Cr 0.10wt%, the rest The amount is Al.

[0032] The alloy ingot is subjected to homogenization heat treatment in a circulating air furnace, and the temperature is raised from room temperature to 490°C at a rate of 40°C / h, kept for 10 hours, and then air-cooled; the heating temperature before extrusion is 400°C; After solid solution for 1h, place it at room temperature for more than 100h to T4 state.

Embodiment 2

[0034]The composition of the aluminum alloy in terms of mass percentage is: Cu 3.78wt%, Mg 1.40wt%, Mn 0.70wt%, Zr 0.15wt%, Fe 0.10wt%, Si 0.10wt%, Ti 0.15%wt%, Cr 0.10wt%, The balance is Al.

[0035] The alloy ingot is subjected to homogenization heat treatment in a circulating air furnace: from room temperature to 500°C at a rate of 50°C / h, then kept for 30 hours, and then air-cooled; the heating temperature before extrusion is 490°C; the extruded sheet is subjected to 495 After solid solution at ℃ / 1h, place it at room temperature for more than 100h to T4 state.

Embodiment 3

[0037] The composition of the aluminum alloy is calculated by mass percentage: Cu 3.75wt%, Mg 1.5wt%, Mn 0.7wt%, Zr 0.12wt%, Fe 0.10wt%, Si 0.10wt%, Ti 0.15wt%, Cr 0.10wt%, the rest The amount is Al.

[0038] The alloy ingot is subjected to homogenization heat treatment in a circulating air furnace: from room temperature to 500°C at a rate of 45°C / h, then kept for 18 hours, and then air-cooled; the heating temperature before extrusion is 460°C; the extruded sheet is subjected to 495 After solid solution at ℃ / 1h, place it at room temperature for more than 100h to T4 state.

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Abstract

The invention relates to a 2xxx aluminium alloy for aviation and a processing method thereof; in the alloy, Mg is 1.3-1.5wt%, Cu is 3.5-4.05wt%, Si is less than or equal to 0.10wt%, Fe is less than or equal to 0.10wt%, Mn is 0.5-0.7wt%, Cr is less than or equal to 0.10wt%, Ti is less than or equal to 0.15wt%, Zr is 0.10-0.15wt%, and Al is the balance; the ratio between Cu and Mg is 2.50-2.70:1.The processing technology is as follows: carrying out homogenized annealing on alloy ingot, namely heating the alloy ingot from room temperature to 490-500 DEG C with the heating rate of 40-50 DEG C / h, preserving heat for 10-30h, then air cooling; carrying out extruding at the temperature of 400-490 DEG C after the homogenized annealing of the alloy ingot to obtain alloy sheet; naturally placing the extruded alloy sheet for above 100h after solutionizing for 495 DEG C / h. The technical proposal of the invention controls the contents of surplus phases in the structure by reasonably adjusting the contents of Cu and Mg in the 2xxx aluminium alloy, and ensures the content of main reinforced phase Al2CuMg, thus providing the materials with better strength and plasticity; scientific technical measures ensure the materials to be provided with better comprehensive mechanical property, thus being the ideal materials for manufacturing aviation parts.

Description

technical field [0001] The invention relates to an aluminum alloy, in particular to a 2xxx series aluminum alloy for aviation and a processing method thereof, belonging to the technical field of nonferrous metals. Background technique [0002] 2xxx series aluminum alloys are used in parts of aircraft that have high requirements for fracture toughness and fatigue resistance due to their medium strength and high damage tolerance, such as aircraft fuselage skins and lower wing skins in a state of tensile stress . Representative aviation 2xxx aluminum alloys include: 2024, 2124, 2324 and other aluminum alloys. [0003] In order to improve the plasticity, fracture toughness and fatigue performance of 2xxx series aluminum alloys, the most direct method is to increase the purity of the material, that is, to reduce the content of Fe and Si impurities in the alloy. However, in order to improve the plasticity and fracture toughness of the material, the content of Fe and Si cannot be...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C21/16C22F1/057C21D1/26
Inventor 纪艳丽胡平钟皓郭富安
Owner 苏州有色金属研究院有限公司
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