Al-Zn-Mg-Cu aviation aluminum alloy and preparation method thereof

An aluminum alloy and aviation technology, applied in the field of aviation aluminum alloys, can solve problems such as poor fracture toughness, material stress corrosion cracking, etc., and achieve the effect of improving alloy stress corrosion resistance, fracture toughness, and intergranular corrosion resistance

Inactive Publication Date: 2018-07-20
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when the content of Zn and Mg increases, more Zn and Mg will be precipitated on the grain boundary, resulting in the material prone to stress corrosion cracking and poor fracture toughness

Method used

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  • Al-Zn-Mg-Cu aviation aluminum alloy and preparation method thereof
  • Al-Zn-Mg-Cu aviation aluminum alloy and preparation method thereof
  • Al-Zn-Mg-Cu aviation aluminum alloy and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0052] A kind of preparation method of Al-Zn-Mg-Cu series aviation aluminum alloy of the present invention is as follows:

[0053] The main composition ratio of the alloy is Al-14.5Zn-2.9Mg-1.3Cu (mass fraction, the same below), the microalloy composition is 0.1Zr-0.03Cr-0.05Ti, and inevitable impurities such as Fe and Si. The casting temperature is 700~740℃, using C 2 Cl 6 Casting after refining. After the ingot is cooled, it is homogenized at 460°C for 24 hours, and then hot-extruded at 410°C with an extrusion ratio of 12.2. The solid solution system is to raise the temperature for 1h to 480°C, keep it warm for 0.5h, quench in water, and then perform aging treatment. The aging system includes peak aging T6 (120℃×24h, air cooling). Grinding with 400 mesh sandpaper, followed by ultrasonic shot peening experiment ( figure 2 ) to get the finished product. The shot blasting chamber material is cast iron. The shot peening used in the ultrasonic shot peening test is stainle...

Embodiment 2

[0061] A kind of preparation method of Al-Zn-Mg-Cu series aviation aluminum alloy of the present invention is as follows:

[0062] The main composition of the alloy is Al-17.5Zn-2.9Mg-1.3Cu, the microalloy composition is 0.1Zr-0.03Cr-0.05Ti, and inevitable impurities such as Fe and Si. The casting temperature is 700~740℃, using C 2 Cl 6 Casting after refining. After the ingot is cooled, it is homogenized at 460°C for 24 hours, and then hot-extruded at 410°C with an extrusion ratio of 12.2. The solid solution system is to raise the temperature for 1h to 480°C, keep it warm for 0.5h, quench in water, and then perform aging treatment. The aging system includes peak aging T6 (120℃×24h, air cooling). Grinding with 400 mesh sandpaper, followed by ultrasonic shot peening experiment ( figure 2 ) to get the finished product. The shot blasting chamber material is cast iron. The shot peening used in the ultrasonic shot peening test is stainless steel shot with a particle size of ...

Embodiment 3

[0070] A kind of preparation method of Al-Zn-Mg-Cu series aviation aluminum alloy of the present invention is as follows:

[0071] The main composition of the alloy is Al-12.5Zn-2.0Mg-1.1Cu, the microalloy composition is 0.1Zr-0.03Cr-0.05Ti, and inevitable impurities such as Fe and Si. The casting temperature is 700~740℃, using C 2 Cl 6 Casting after refining. After the ingot is cooled, it is homogenized at 460°C for 24 hours, and then hot-extruded at 410°C with an extrusion ratio of 12.2. The solid solution system is to raise the temperature for 1h to 480°C, keep it warm for 0.5h, quench in water, and then perform aging treatment. The aging system includes peak aging T6 (120℃×24h, air cooling). Grinding with 400 mesh sandpaper, followed by ultrasonic shot peening experiment ( figure 2 ) to get the finished product. The shot blasting chamber material is cast iron. The shot peening used in the ultrasonic shot peening test is stainless steel shot with a particle size of ...

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Abstract

The invention relates to an Al-Zn-Mg-Cu aviation aluminum alloy and a preparation method thereof. The aviation aluminum alloy comprises, by weight, 12-20% of Zn, 1-3% of Mg and 1-2% of Cu. The Al-Zn-Mg-Cu aviation aluminum alloy comprises a core part and a surface plastic deformation layer, wherein the core part is provided with an aging-separated nanocrystalline strengthening phase, and the surface plastic deformation layer is a homogenized solid solution structure which is obtained through severe plastic deformation of the surface. The preparation method comprises the following steps that after the components are distributed according to a design group, casting is carried out, a cast ingot is obtained, and the cast ingot is subjected to homogenization treatment, thermal deformation treatment, solid solution treatment and aging treatment in sequence; materials after aging treatment are obtained, and the materials are taken as materials A; and impurities on the surfaces of the materials A are removed, and the surface severe plastic deformation is carried out; and the Al-Zn-Mg-Cu aviation aluminum alloy is obtained.

Description

technical field [0001] The invention relates to the technical field of aviation aluminum alloys, in particular to an Al-Zn-Mg-Cu series aviation aluminum alloy and a preparation method thereof. Background technique [0002] The world-class problem in the research and development of Al-Zn-Mg-Cu aerospace aluminum alloys is the contradiction between strength properties and stress corrosion, fracture toughness and fatigue resistance. If the content of Zn and Mg is increased, the density of intragranular precipitated phases will increase, and the strength of the alloy will increase. For example, when the Zn content increases from 5% to 12% (percentage is mass percent, the same below), the yield strength of the alloy increases from 500MPa to 800MPa. However, when the content of Zn and Mg increases, more Zn and Mg will be precipitated on the grain boundary, resulting in the material prone to stress corrosion cracking and poor fracture toughness. Therefore, as a compromise, the Z...

Claims

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Application Information

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IPC IPC(8): C22C21/10C22F1/053C22C1/06C22C1/02
CPCC22C1/026C22C1/06C22C21/10C22F1/053
Inventor 孙擎擎韩青有李洁
Owner CENT SOUTH UNIV
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