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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 crack growth rate is 3.89×10 -3 mm / cycle; in addition, the alloy is cyclically loaded under this stress for 10 7 The cycle fatigue limit is 158Mpa; as an aircraft skin material, it cannot meet the performance requirements of aircraft service

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

Embodiment 1

[0077] 1. Homogenize the 40mm aluminum alloy ingot at 493°C for 24 hours, then air cool;

[0078] 2. Keep the cast ingot at a temperature of 440°C for 1 hour, then perform hot rolling deformation to 8.0mm, and air-cool;

[0079] 3. Warm rolling at 160°C, with a deformation of 1.0mm in each pass, until the final thickness is 2.0mm;

[0080] 4. Anneal the plate at 380°C for 1 hour, then air cool;

[0081] 5. The plate is subjected to solid solution treatment at a temperature of 500°C for 1 hour, and then water quenched;

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

[0083] 7. Short-term artificial aging of the plate at 190°C for 0.5h, and then air-cooled to room temperature.

[0084] Table 1 has shown alloy of the present invention, existing industry 2E12-T3 alloy and the mechanical property that previous method obtains alloy; As can be seen from Table 1:

[0085] Table 1

[0086]

[0087] In the alloy prepared in Example 1, the volume fractions of cub...

Embodiment 2

[0094] 1. Homogenize the 40mm aluminum alloy ingot at 495°C for 18 hours, then air cool;

[0095] 2. Heat the ingot at 420°C for 1 hour, then hot-roll and deform it to 7mm, and air-cool;

[0096] 3. Warm rolling is carried out at 180°C, the deformation amount of each pass is 1.4mm, until the final thickness is 2.0mm;

[0097] 4. Anneal the plate at 400°C for 0.5h, then air cool;

[0098] 5. The plate is subjected to solid solution treatment at 505°C for 0.5h, and then water quenched;

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

[0100] 7. Short-term artificial aging of the plate at 175°C for 2.0h, and then air-cooled to room temperature.

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

[0102] In the 2E12-T3 alloy prepared in Example 2, the volume fractions of...

Embodiment 3

[0111] 1. Homogenize the 20mm aluminum alloy ingot at 485°C for 48h, then air cool;

[0112] 2. Keep the cast ingot at a temperature of 460°C for 1 hour, then perform hot rolling deformation to 8mm, and air-cool;

[0113] 3. Warm rolling at 180°C, with a deformation of 0.8mm in each pass, until the final thickness is 1.6mm;

[0114] 4. Anneal the plate at 360°C for 1.5h, then air cool;

[0115] 5. The plate is subjected to solid solution treatment at 498°C for 1.0h, and then water quenched;

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

[0117] 7. Short-term artificial aging of the plate at 180°C for 1.0h, and then air-cooled to room temperature.

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

[0119] In the 2E12-T3 alloy prepared in Example 3, the volume fractions of cubic t...

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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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