High damage-resistant aluminium alloy and preparation method thereof

An aluminum alloy and damage-resistant technology, which is applied in the field of non-ferrous metal materials, can solve the problems of narrow PFZ and achieve the effects of improving damage resistance, high resistance to fatigue crack growth, and reducing stress concentration at the tip of cracks

Active Publication Date: 2014-08-13
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this paper, the increase of Ag content changes the size distribution of the main precipitated phase Ω phase in the alloy matrix, mak

Method used

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  • High damage-resistant aluminium alloy and preparation method thereof
  • High damage-resistant aluminium alloy and preparation method thereof
  • High damage-resistant aluminium alloy and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment example 1

[0050] The composition of alloy 1 is 3.15% Cu, 0.84% ​​Mg, 0.3% Mn, 0.48% Ag, 0.12% Zr, and the balance is unavoidable trace impurity elements and Al.

[0051] After the ingot billet is obtained, it is first kept at 480°C for 8 hours, and then at 520°C for 36 hours to obtain a homogenized ingot billet, which is hot-rolled, intermediate annealed, and cold-rolled to obtain a cold-rolled billet. State plate; the temperature of the hot rolling is 400-450 ℃, the deformation of the hot rolling pass is 15%; the total deformation of the hot rolling is 60%; the system of the intermediate annealing is: after annealing at 450 ℃ for 5 hours Cool to room temperature with the furnace; the pass deformation of the cold rolling is 10%, and the total deformation of the cold rolling is 60%.

[0052] The cold-rolled sheet is solution treated at 530°C for one hour, water quenched, and then pre-deformed by 4% cold rolling, aged at room temperature for 100 days, and the mechanical properties at room...

Embodiment example 2

[0055] The composition of alloy 1 is 3.15% Cu, 0.84% ​​Mg, 0.3% Mn, 0.48% Ag, 0.12% Zr, and the balance is unavoidable trace impurity elements and Al.

[0056] After the ingot billet is obtained, it is first kept at 480°C for 8 hours, and then at 520°C for 36 hours to obtain a homogenized ingot billet, which is hot-rolled, intermediate annealed, and cold-rolled to obtain a cold-rolled billet. State plate; the temperature of the hot rolling is 400-450 ℃, the deformation of the hot rolling pass is 15%; the total deformation of the hot rolling is 60%; the system of the intermediate annealing is: after annealing at 450 ℃ for 5 hours Cool to room temperature with the furnace; the pass deformation of the cold rolling is 10%, and the total deformation of the cold rolling is 60%.

[0057] The cold-rolled sheet is solution treated at 520°C for 1.5 hours, water quenched, and then subjected to 4% cold rolling pre-deformation, and artificially aged at 145°C for 60 hours to obtain mechanic...

Embodiment example 3

[0065]The composition of alloy 2 is 3.32% Cu, 0.91% Mg, 0.3% Mn, 0.48% Ag, 0.1% Zr, and the balance is unavoidable trace impurity elements and Al. After the ingot billet is obtained, it is first kept at 485°C for 12 hours, and then at 530°C for 30 hours to obtain a homogenized ingot billet, which is hot-rolled, intermediate annealed, and cold-rolled to obtain a cold-rolled billet. State plate; the temperature of the hot rolling is 400-450 ℃, the deformation of the hot rolling pass is 8%; the total deformation of the hot rolling is 64%; the system of the intermediate annealing is: after annealing at 420 ℃ for 4h Cool to room temperature with the furnace; the deformation of each pass of cold rolling is 8%, and the total deformation of cold rolling is 64%.

[0066] The cold-rolled sheet is solution treated at 530°C for one hour, water quenched, and then pre-deformed by 4% cold rolling, aged at room temperature for 100 days, and the mechanical properties at room temperature are ob...

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Abstract

The invention relates to an aluminium alloy and a preparation method thereof, and in particular relates to a damage-resistant aluminium alloy and a preparation method thereof. The aluminium alloy disclosed by the invention comprises the following components in mass percentage: 3.0-4.0% of Cu, 0.7-1.5% of Mg, 0.15-0.6% of Mn, 0.3-0.8% of Ag, 0.08-0.2% of Zr, and the balance of Al and trace impurity elements, wherein the total content of the impurity elements is less than 0.1%. On the basis of a traditional damage-resistant Al-Cu-Mg alloy (2X24 alloy), the contents of Cu and Mg main alloy elements are reduced; simultaneously, Ag and Zr are added, therefore, the novel high damage-resistant Al-Cu-Mg-Ag-Mn-Zr alloy is designed. Compared with 2524 alloy, the aluminum alloy disclosed by the invention has the advantages that in the event that the intensity of the aluminum alloy is higher than that of the 2X24 alloy, the crack growth rate of the aluminum alloy is reduced by above 1/3; the tensile strength sigma b of the prepared aluminium alloy is 425-480 Mpa; the yield strength sigma 0.2 of the prepared aluminium alloy is 320-390 MPa; the elongation rate delta of the prepared aluminium alloy is 18-25%; in addition, when delta K=30 MPa*m<1/2>, the crack growth rate is 1.1*10<-3>-2.0*10<-3>-mm/cycle.

Description

Technical field: [0001] The present invention relates to an aluminum alloy and its preparation method, in particular to a damage-resistant aluminum alloy and its preparation method; by adjusting the content of main alloy elements, adding new alloy elements and matching heat treatment process, fatigue resistance is achieved The invention relates to an aluminum alloy with high crack propagation ability and excellent mechanical properties; it belongs to the technical field of non-ferrous metal materials. Background technique: [0002] Since domestic aluminum alloys cannot meet the requirements of aircraft design in terms of comprehensive performance and uniformity, most of the high-performance aluminum alloy materials required by large aircraft in my country currently rely on imports. In particular, aircraft skin structures are subject to alternating loads and different medium corrosion environments, requiring aluminum alloys to continuously improve damage resistance on the bas...

Claims

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Application Information

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IPC IPC(8): C22C21/16C22C1/03C22F1/057
Inventor 郑子樵钟继发胡芳
Owner CENT SOUTH UNIV
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