Machining method of fine-grain cubic texture corrosion-fatigue-resistant aluminum alloy plate

An aluminum alloy sheet and cubic texture technology, which is applied in the field of skin materials and the preparation of corrosion-resistant fatigue-resistant aluminum alloy sheets, can solve problems such as the inability to meet aircraft service performance requirements, and achieve excellent corrosion-fatigue resistance and grain size. The effect of refining and suppressing the recovery phenomenon

Active Publication Date: 2018-06-12
HUNAN UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Under the conditions of 3.5% NaCl salt spray environment, stress ratio R=0.1, and loading frequency f=10Hz, when ΔK=10MPa*m 1/2 , the crack growth rate is 1.25×10 ‐4 mm/cycle; when ΔK=30MPa*m 1/2 , the crack growth rate is 9.11×10 ‐3 mm/week; in pH=4.0 acid mist environment (by adding H 2 SO

Method used

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  • Machining method of fine-grain cubic texture corrosion-fatigue-resistant aluminum alloy plate
  • Machining method of fine-grain cubic texture corrosion-fatigue-resistant aluminum alloy plate
  • Machining method of fine-grain cubic texture corrosion-fatigue-resistant aluminum alloy plate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0119] 1. Homogenize the 40mm aluminum alloy ingot at 495°C for 18 hours, then air cool;

[0120] 2. Keep the cast ingot at a temperature of 450°C for 1 hour, then perform hot rolling deformation to 6.0mm, and air-cool;

[0121] 3. The hot-rolled sheet is subjected to solution treatment at 500°C for 0.5h, and then water quenched;

[0122] 4. Cold rolling the plate at room temperature, the deformation of each pass is 0.8mm, after each pass of deformation, put the plate into liquid nitrogen for 10min cryogenic treatment, until the final thickness is 2.0mm;

[0123] 5. The plate is subjected to solid solution treatment at 500°C for 0.5h, and then water quenched;

[0124] 6. Carry out 0.2mm cold rolling deformation treatment;

[0125] 7. Short-term artificial aging of the plate at 195°C for 15 minutes, and then air-cooled to room temperature.

[0126] Its performance test values ​​are shown in Tables 1 and 2.

[0127] The reason for the reduction of the corrosion fatigue crack...

Embodiment 2

[0130] The specific implementation steps are:

[0131] 1. Homogenize the 40mm aluminum alloy ingot at 490°C for 24 hours, then air cool;

[0132] 2. Heat the ingot at 420°C for 1 hour, then hot-roll and deform it to 8mm, and air-cool;

[0133] 3. The hot-rolled plate is subjected to solution treatment at 505°C for 15 minutes, and then water quenched;

[0134] 4. Cold rolling the plate at room temperature, the deformation of each pass is 1.0mm, after each pass of deformation, put the plate into liquid nitrogen for 15min cryogenic treatment, until the final thickness is 2.0mm;

[0135] 5. The plate is subjected to solid solution treatment at 505°C for 40 minutes, and then water quenched;

[0136] 6. Carry out 0.2mm cold rolling deformation treatment;

[0137] 7. Short-term artificial aging of the plate at 190°C for 0.5h, and then air-cooled to room temperature.

[0138] The grains of the alloy in Example 2 of the present invention are equiaxed, and the grain size is very sma...

Embodiment 3

[0150] The specific implementation steps are:

[0151] 1. Homogenize the 40mm aluminum alloy ingot at 485°C for 48h, then air cool;

[0152] 2. Heat the ingot at 450°C for 1 hour, then hot-roll and deform it to 6mm, and air-cool;

[0153] 3. The hot-rolled plate is subjected to solution treatment at 495°C for 40 minutes, and then water quenched;

[0154] 4. Cold rolling the plate at room temperature, the deformation of each pass is 0.9mm, after each pass of deformation, put the plate into liquid nitrogen for 15min cryogenic treatment, until the final thickness is 1.5mm;

[0155] 5. The plate is subjected to solution treatment at a temperature of 505°C for 15 minutes, and then water quenched;

[0156] 6. Carry out 0.2mm cold rolling deformation treatment;

[0157] 7. Short-term artificial aging of the plate at 195°C for 15 minutes, and then air-cooled to room temperature.

[0158] The texture volume fraction of the alloy prepared by the method of embodiment 3

[0159]

...

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Abstract

The invention relates to a skin material for aviation, in particular to a machining method for preparing corrosion-fatigue-damage-resistant aluminum alloy plates, and belongs to the technical field ofnonferrous metals. The machining method comprises the steps that an aluminum alloy hot rolling material is subjected to solid solution treatment for the first time, then the second time of solid solution treatment is carried out after multi-pass cold rolling with the pass deformation amount being less than or equal to 1.0mm is carried out to achieve the design thickness of the aluminum alloy plate; and in the multi-pass cold rolling process, deep cooling treatment is carried out immediately after each pass of cold rolling, and the temperature of the deep cooling treatment is less than or equal to -100 DEG C. The machining method for preparing the corrosion-fatigue-damage-resistant aluminum alloy plates is reasonable in texture design, the preparation process is simple and controllable, obtained products have good performance, and the machining method for preparing the corrosion-fatigue-damage-resistant aluminum alloy plates is convenient for large-scale industrial application.

Description

technical field [0001] The invention relates to a skin material for aviation, in particular to a processing method for preparing a corrosion-resistant fatigue damage aluminum alloy plate, which belongs to the technical field of non-ferrous metals. Background technique [0002] Aluminum alloy materials are used in a wide range of industries and can be used in various fields such as aviation, aerospace, construction, transportation, etc., and the corrosion fatigue damage of aluminum alloy components is an important factor affecting aviation safety. [0003] Affected by factors such as take-off and landing, gusts of wind, etc., aircraft are often subjected to periodic loads during service. At the same time, affected by the environmental climate of various places, the aircraft will also be affected by corrosive environments such as ocean salt spray and acid rain caused by industrial pollution during its service. The combined effect of long-term cyclic loading and corrosive envi...

Claims

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Application Information

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IPC IPC(8): C22F1/04
CPCC22F1/002C22F1/04
Inventor 陈宇强潘素平刘文辉吴志强
Owner HUNAN UNIV OF SCI & TECH
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