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Aluminum-copper-magnesium alloy thin plate microalloyed by zirconium or by scandium and zirconium and preparation method thereof

A micro-alloying, aluminum-copper-magnesium technology, which is applied in the field of aluminum alloy preparation, can solve the problems that the anti-fatigue characteristics need to be further improved, and achieve the effects of product performance control and simple process

Inactive Publication Date: 2009-12-30
CENT SOUTH UNIV
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0002] The traditional 2524 aluminum-copper-magnesium alloy is a typical lightweight and high-strength structural material for aerospace due to its high strength, good heat resistance, excellent formability and damage resistance, but its fatigue resistance still needs to be further improved

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1、2

[0024] (1) Chemical composition (mass fraction, %) of alloy of table 1

[0025] Example

Alloy

Cu

Mg

mn

Fe

Si

Ti

Zr

sc

Al

1

2524Z

3.80

1.40

0.29

0.03

0.03

0.05

0.06

-

Bal.

2

2524SZ

3.80

1.40

0.29

0.03

0.03

0.05

0.06

0.05

Bal.

[0026] (2) Melt the aluminum, copper, Al-Mn and Al-Ti master alloys in the melting furnace according to the content required in Table 1. After the melt is completely melted, the Sc elements are added in the form of Al-Sc master alloys, and the Zr elements are added in the form of Mg - Added in the form of Zr master alloy or zirconium salt. Mg is added according to the conventional method of 2524 aluminum alloy, and the melt is refined and degassed and semi-continuously cast into flat ingots (ie ingots).

[0027] (3) When Sc is 0, the flat ingot microalloyed with zi...

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Abstract

The invention relates to an aluminum-copper-magnesium alloy thin plate microalloyed by zirconium or by scandium and zirconium and a preparation method thereof. The invention aims to further improve the antifatigue performance of the prior aero high-strength 2524 aluminum alloy thin plate. The alloy comprises the following components in portion by weight: Cu 3.80-4.0, Mg 1.20-1.6, Mn 0.25-0.4, Fe 0.02-0.06, Si 0.02-0.06, Ti 0.03-0.06, Sc 0-0.10, Zr 0.05-0.10 and the balance of Al, wherein the impurity content is no more than 0.1 percent and the total portions of the components are 100 positions. The preparation method of the invention is implemented by the steps of material mixing, smelting, semicontinuous ingot casting, even heat treatment of a cast ingot, hot and cold rolling, solid solution heat treatment, pressure polish, leveling and natural aging. The finished plate of the invention has high yield stress and antifatigue performance advantageous over that of the prior 2524 aluminum alloy.

Description

technical field [0001] The invention relates to the technical field of aluminum alloy preparation, in particular to a high-strength aluminum alloy sheet for aviation with high fatigue resistance and its preparation technology. Background technique [0002] The traditional 2524 aluminum-copper-magnesium alloy is a typical lightweight and high-strength structural material for aerospace due to its high strength, good heat resistance, excellent formability and damage resistance, but its fatigue resistance still needs to be further improved . Contents of the invention [0003] The inventors have found through experiments that adding trace amounts of scandium and zirconium to aluminum-magnesium alloys and aluminum-zinc-magnesium alloys has a significant grain refinement effect, and the secondary Al formed by scandium, zirconium and aluminum 3 Zr and Al 3 (Sc 1-x Zr x ) particles are coherent with the matrix, dispersedly distributed in the α(Al) matrix, strongly pinning dislo...

Claims

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Application Information

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IPC IPC(8): C22C21/16C22C1/02B22D11/00C22F1/057C21D1/18C21D1/26
Inventor 尹志民姜锋潘清林王华
Owner CENT SOUTH UNIV
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