Treatment method for brass texture antifatigue aluminum alloy panel

A technology of aluminum alloy sheet and brass texture, which is applied in the processing field of skin materials and the preparation of fatigue-resistant aluminum alloy sheet, can solve the problems that cannot meet the performance requirements of aircraft service, achieve excellent fatigue resistance, and promote the recovery process , the effect of grain refinement

Active Publication Date: 2016-04-20
湖南润泰新能源科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Under the conditions of stress ratio R=0.1 and loading frequency f=10Hz, when the stress intensity factor range ΔK=10Mpa*m 1/2 , the crack growth rate is 4.25×10 -5 mm/cycle; when the stress intensity factor range ΔK=30Mpa*m 1/2 , the cr

Method used

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  • Treatment method for brass texture antifatigue aluminum alloy panel
  • Treatment method for brass texture antifatigue aluminum alloy panel
  • Treatment method for brass texture antifatigue aluminum alloy panel

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0076] Example 1

[0077] 1. The 40mm aluminum alloy ingot is homogenized at a temperature of 493°C for 24 hours, and then air-cooled;

[0078] 2. Keep the ingot at a temperature of 440℃ for 1h, and then deform it to 8.0mm by hot rolling and air cooling;

[0079] 3. Carry out warm rolling at 160℃, the deformation of pass is 1.0mm, until the final thickness is 2.0mm;

[0080] 4. The plate is annealed at a temperature of 380℃ for 1h, and then air-cooled;

[0081] 5. Put the plate into solution treatment at 500℃ for 1h, and then water quench;

[0082] 6. Perform 0.2mm cold rolling deformation treatment;

[0083] 7. The plate is artificially aged at 190℃ for 0.5h for a short time, and then air-cooled to room temperature.

[0084] Table 1 shows the mechanical properties of the alloy of the present invention, the existing industrial 2E12-T3 alloy and the alloy obtained by the previous method; it can be seen from Table 1:

[0085] Table 1

[0086]

[0087] In the alloy prepared in Example 1, the vo...

Example Embodiment

[0093] Example 2

[0094] 1. The 40mm aluminum alloy ingot is homogenized at a temperature of 495℃ for 18 hours, and then air-cooled;

[0095] 2. Keep the ingot at a temperature of 420℃ for 1h, and then deform it to 7mm by hot rolling and air cooling;

[0096] 3. Carry out warm rolling at 180℃, the deformation of pass is 1.4mm, until the final thickness is 2.0mm;

[0097] 4. The plate is annealed at 400℃ for 0.5h, and then air-cooled;

[0098] 5. Put the plate into solution treatment at 505℃ for 0.5h, and then water quench;

[0099] 6. Carry out 0.1mm cold rolling deformation treatment;

[0100] 7. The plate is subjected to short-time artificial aging at 175℃ for 2.0h, and then air-cooled to room temperature.

[0101] The alloy prepared in Example 2 has relatively large grain length and diameter, and some of the grains are obviously fibrous. The average grain size in the three directions of LD, TD and SD is 254μm, 93μm and 27μm, respectively.

[0102] In the 2E12-T3 alloy prepared in Examp...

Example Embodiment

[0110] Example 3

[0111] 1. The 20mm aluminum alloy ingot is homogenized at a temperature of 485℃ for 48 hours, and then air-cooled;

[0112] 2. Keep the ingot at a temperature of 460℃ for 1h, and then deform it to 8mm by hot rolling and air cooling;

[0113] 3. Carry out warm rolling at 180℃, the deformation of pass is 0.8mm, until the final thickness is 1.6mm;

[0114] 4. The plate is annealed for 1.5h at a temperature of 360℃, and then air-cooled;

[0115] 5. Put the plate into solution treatment at 498℃ for 1.0h, and then water quench;

[0116] 6. Perform 0.2mm cold rolling deformation treatment;

[0117] 7. The plate is artificially aged at 180℃ for 1.0h for a short time, and then air-cooled to room temperature.

[0118] The alloy prepared in Example 3 has relatively large grain length and diameter, and some of the grains are obviously fibrous. The average grain size in the three directions of LD, TD and SD is 193μm, 72μm and 16μm, respectively.

[0119] In the 2E12-T3 alloy prepared...

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Abstract

The invention relates to a treatment method for a brass texture antifatigue aluminum alloy panel, which is characterized in that multiple times of warm rolling is performed on an aluminum alloy hot rolling material until reaching the designed thickness of the aluminum alloy panel, and after annealing treatment and solution treatment, short-term artificial aging is performed. According to the invention, a treatment process of multiple times of warm rolling and annealing is adopted; by virtue of warm rolling, grains of the alloy can be effectively refined, the return process of alloy can be promoted, deformation energy storage can be reduced, and recrystallization can be inhibited; and by virtue of primary annealing treatment, annealing temperature and heat insulation time can be controlled, grains cannot grow up, and a deformation texture can be retained, thus obtaining a relatively strong deformation texture. The treatment method is simple in process method and convenient to operate, can effectively improve the composition and the volume fraction of the texture in an aluminum alloy matrix, can effectively prolong the fatigue life of the aluminum alloy on the premise of ensuring that aluminum alloy strength and ductility meet alloy performance requirements, is suitable for industrial application, and provides a feasible technical solution for preparation of aluminum alloy material for aviation and spaceflight.

Description

technical field [0001] The invention relates to a skin material for aviation, in particular to a processing method for preparing an aluminum alloy sheet material resistant to fatigue damage, and belongs to the technical field of nonferrous metals. Background technique [0002] Aluminum alloy materials have a wide range of applications, and can be used in various fields such as aviation, aerospace, construction, and transportation in industry. Fatigue damage of aluminum alloy components is an important factor affecting aviation safety. [0003] Metal fatigue is a complex process. In the process of repeated loading, due to the effect of stress, plastic deformation occurs in the local area of ​​the metal, and when the deformation accumulates to the limit, it will be damaged and eventually lead to the fracture of the specimen. Therefore, in order to make the alloy have excellent fatigue properties, it is not only required to have high strength (the ability to resist external fo...

Claims

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Application Information

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IPC IPC(8): C22F1/04
CPCC22F1/04
Inventor 陈宇强潘素平宋文炜刘文辉唐昌平
Owner 湖南润泰新能源科技有限公司
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