High-strength and high-corrosion-resistance rapid aging method fusing plastic deformation and multistage continuous temperature control

Abstract

The invention provides a high-strength and high-corrosion-resistance rapid aging method integrating plastic deformation and multistage continuous temperature control, and belongs to the technical field of aluminum alloy machining. The method comprises the following steps: carrying out plastic deformation on an aluminum alloy component to obtain a deformed component; carrying out regression aging treatment on the deformed component to obtain a first-state component; and sequentially carrying out low-temperature aging treatment and high-temperature aging treatment on the first-state component to obtain a finished product component. According to the method, moderate plastic deformation is introduced in the aging process to promote the synergistic effect of dislocation and a precipitated phase, nucleation acceleration and dispersion distribution optimization of the precipitated phase are achieved, and therefore the mechanical strengthening effect and the stress corrosion resistance of the aluminum alloy component can be considered; and on the premise that the strengthening effect and the stress corrosion resistance of the high-strength aluminum alloy component are maintained or improved, the aging strengthening treatment time is greatly shortened, the production takt is improved, the energy consumption and the production cost are reduced, the equipment occupancy rate is reduced, and the purposes of energy conservation, consumption reduction and green manufacturing are achieved.

Description

Technical Field

[0001] This invention relates to the field of aluminum alloy processing technology, specifically to a rapid aging method for high strength and high corrosion resistance that integrates plastic deformation and multi-stage continuous temperature control. Background Technology

[0002] With the rapid development of high-end equipment manufacturing sectors (such as aviation, aerospace, marine, rail transportation, and automotive industries), more stringent technical specifications and application requirements have been placed on structural materials for multiple performance indicators, including lightweight, high strength and toughness, corrosion resistance, and service stability. High-strength Al-Li alloys, Al-Mg-Si alloys, and Al-Zn-Mg-Cu alloys have advantages such as low density, high strength, good impact resistance, and easy recycling.

[0003] In current aluminum alloy component manufacturing processes, artificial aging often requires long holding times, with some high-strength aluminum alloys requiring aging cycles of 12-24 hours. This long-cycle process not only significantly reduces production pace and overall manufacturing efficiency but also leads to a substantial increase in energy consumption. Furthermore, prolonged aging increases equipment occupancy and production costs, hindering large-scale continuous production. Summary of the Invention

[0004] In view of the technical problems existing in the background art, this application provides a high-strength, high-corrosion-resistant rapid aging method that integrates plastic deformation and multi-stage continuous temperature control, aiming to provide a method with short aging time and good mechanical properties of finished products.

[0005] In a first aspect, embodiments of this application provide a rapid aging method for high strength and high corrosion resistance that integrates plastic deformation and multi-stage continuous temperature control, comprising the following steps: Aluminum alloy components are plastically deformed to obtain deformed components; The deformed component is subjected to regression aging processing to obtain the first state component; The first-state component is subjected to low-temperature aging treatment and high-temperature aging treatment in sequence to obtain the finished component.

[0006] Optionally, in some embodiments of this application, in the step of plastically deforming the aluminum alloy component to obtain the deformed component, the aluminum alloy component is in the T4 state.

[0007] Optionally, in some embodiments of this application, the material of the aluminum alloy component includes Al-Li alloy, Al-Mg-Si alloy, or Al-Zn-Mg-Cu alloy.

[0008] Optionally, in some embodiments of this application, the step of plastically deforming the aluminum alloy component to obtain the deformed component includes: Obtain the target deformation of the aluminum alloy component; When the target deformation is less than 20%, the aluminum alloy component is cold-formed to obtain the deformed component; When the target deformation is greater than or equal to 20%, the aluminum alloy component is hot-formed to obtain the deformed component.

[0009] Optionally, in some embodiments of this application, in the step of performing regression aging treatment on the deformed component to obtain the first state component, the temperature of the regression aging treatment is 100℃~240℃ and the time is 1~60min.

[0010] Optionally, in some embodiments of this application, when the material of the aluminum alloy component is an Al-Zn-Mg-Cu alloy, the temperature range of the low-temperature aging treatment is controlled at 100℃~160℃, the time of the low-temperature aging treatment is controlled at 180~300min, the temperature range of the high-temperature aging treatment is controlled at 120℃~220℃, and the time of the high-temperature aging treatment is controlled at 10~80min.

[0011] Optionally, in some embodiments of this application, when the material of the aluminum alloy component is 7075 aluminum alloy, the temperature range of the low-temperature aging treatment is controlled at 100℃~140℃, the time of the low-temperature aging treatment is controlled at 180~250min, the temperature range of the high-temperature aging treatment is controlled at 140℃~200℃, and the time of the high-temperature aging treatment is controlled at 10~60min.

[0012] Optionally, in some embodiments of this application, when the material of the aluminum alloy component is 6061 aluminum alloy, the temperature range of the low-temperature aging treatment is controlled at 160℃~180℃, the time of the low-temperature aging treatment is controlled at 30~220min, the temperature range of the high-temperature aging treatment is controlled at 150℃~200℃, and the time of the high-temperature aging treatment is controlled at 40~120min.

[0013] Optionally, in some embodiments of this application, after the steps of performing low-temperature aging treatment and high-temperature aging treatment on the first state component in sequence and before the step of obtaining the finished component, the component that has undergone the high-temperature aging treatment is further cooled, and the finished component is obtained after cooling to room temperature.

[0014] The technical solution proposed in this application has the following beneficial effects: In this technical solution, by introducing appropriate plastic deformation during the aging process to promote the synergistic effect of dislocations and precipitated phases, the nucleation of precipitated phases is accelerated and the dispersion distribution is optimized. This allows for a balance between the mechanical strengthening effect and stress corrosion resistance of aluminum alloy components. While maintaining or improving the strengthening effect and stress corrosion resistance of high-strength aluminum alloy components, the aging strengthening treatment time is significantly shortened, which can significantly improve production efficiency, increase production cycle time, reduce energy consumption and production costs, reduce equipment occupancy, and achieve the goals of energy conservation, emission reduction and green manufacturing.

[0015] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0016] To more clearly illustrate the technical solution of this application, the accompanying drawings used in this application will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without any creative effort.

[0017] Figure 1 This is a process flow diagram of a high-strength, high-corrosion-resistant rapid aging method that integrates plastic deformation and multi-stage continuous temperature control, as proposed in an embodiment of this application. Figure 2 This is a process flow diagram of a high-strength, high-corrosion-resistant rapid aging method that integrates plastic deformation and multi-stage continuous temperature control, as proposed in another embodiment of this application. Figure 3 The image shows the metallographic structure of the finished component prepared in Example 3 of the stress corrosion test after 2.5 hours of corrosion. Figure 4 The image shows the metallographic structure of the finished component prepared in Comparative Example 10 after 2 hours of corrosion in the stress corrosion test. Detailed Implementation

[0018] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0019] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0020] Various embodiments of this application may exist in the form of a range; it should be understood that the description in the form of a range is merely for convenience and brevity and should not be construed as a hard limitation on the scope of this application; therefore, it should be considered that the range description has specifically disclosed all possible sub-ranges and single numerical values ​​within that range. For example, it should be considered that the range description from 1 to 6 has specifically disclosed sub-ranges such as from 1 to 3, from 1 to 4, from 1 to 5, from 2 to 4, from 2 to 6, from 3 to 6, etc., and single numbers within the range, such as 1, 2, 3, 4, 5, and 6, regardless of the range. Furthermore, whenever a numerical range is referred to herein, it means including any referenced number (fraction or integer) within the referred range.

[0021] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly specifying the number, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly defined.

[0022] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0023] In the description of the embodiments in this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this document generally indicates that the preceding and following related objects have an "or" relationship.

[0024] In the description of the embodiments of this application, the term "at least one" refers to one or more, "more than one" refers to two or more (including two), similarly, "multiple sets" refers to two or more (including two sets), and "multiple pieces" refers to two or more (including two pieces). "At least one," "at least one of the following," or similar expressions refer to any combination of these items, including any combination of single or multiple items. For example, "at least one of a, b, or c," or "at least one of a, b, and c," can all represent: a, b, c, ab (i.e., a and b), ac, bc, or abc, where a, b, and c can be single or multiple.

[0025] In traditional aluminum alloy processing, after solution treatment and natural aging, artificial aging is typically performed. This involves heating the aluminum alloy to a specific temperature (usually 160°C to 200°C) and holding it for a certain time (12 to 24 hours), followed by rapid cooling to accelerate the precipitation of alloying elements and improve material strength. However, this method is not only time-consuming, impacting production efficiency and pace, but traditional artificial aging processes also struggle to achieve the optimal balance between mechanical properties and corrosion resistance. When the goal is to increase strength, the precipitated phases within the material tend to coarsen or form high-density strengthening phases, which, while improving mechanical properties, weaken the alloy's corrosion resistance. Conversely, if maintaining corrosion resistance is prioritized, the precipitation strengthening effect is insufficient, and the material strength cannot be fully realized. Therefore, current high-strength aluminum alloy component manufacturing faces bottlenecks such as excessively long aging cycles, high production costs, significant energy consumption, and the difficulty in achieving a balance between mechanical properties and corrosion resistance.

[0026] In view of this, this application proposes a rapid aging method for high strength and high corrosion resistance that integrates plastic deformation and multi-stage continuous temperature control. Please refer to [link to relevant documentation]. Figure 1 or Figure 2 The processing method includes the following steps: S10, the aluminum alloy component is plastically deformed to obtain the deformed component; S20, Perform regression aging processing on the deformed component to obtain the first state component; S30, the first state component is subjected to low-temperature aging treatment and high-temperature aging treatment in sequence to obtain the finished component.

[0027] In this technical solution, plastic forming processes at different temperatures (such as cold forming or hot forming) are organically combined with multi-stage continuous temperature-controlled aging processes (including regression aging, low-temperature aging, and high-temperature aging). By introducing appropriate plastic deformation during the aging process, the synergistic effect of dislocations and precipitated phases is promoted, thereby accelerating the nucleation and optimizing the dispersion distribution of precipitated phases. This approach can balance the mechanical strengthening effect and stress corrosion resistance of aluminum alloy components. While maintaining or improving the strengthening effect and stress corrosion resistance of high-strength aluminum alloy components, the aging strengthening treatment time is significantly shortened, which can significantly improve production efficiency, increase production cycle time, reduce energy consumption and production costs, reduce equipment occupancy, and achieve the goals of energy conservation, emission reduction, and green manufacturing.

[0028] Specifically, the process proposed in this application first utilizes a plastic forming process to obtain the final size and shape of the workpiece and form a certain amount of dislocations. Then, through a short-term regression aging treatment, the GPI zone precipitates generated by natural aging are dissolved, thereby eliminating the negative effects of natural aging. Next, a low-temperature aging treatment is used to promote the nucleation and growth of precipitates, resulting in the formation and uniform growth of fine GPII zone precipitates in the matrix. Finally, a high-temperature aging treatment is used to suppress the nucleation of new precipitates while ensuring that the precipitates from the low-temperature aging treatment grow further uniformly, allowing the GPII zone precipitates to transform into the η' phase. Simultaneously, the size of the precipitates in the matrix and on the dislocations remains below the critical coarse phase size. During this process, the relatively high aging temperature can also fully induce the nucleation and growth of precipitates on the dislocations. This maximizes the tensile strength and elongation of the material. Furthermore, low-temperature aging treatment can promote the formation of high-density GPI regions in the matrix. In the subsequent high-temperature short-time secondary final aging treatment, the precipitates at the grain boundaries gradually coarsen from the GP region and η' phase to the η phase, and the η phase will gradually converge. When the size of the grain boundary precipitates exceeds a certain critical value, the precipitates separate, eventually forming discrete island-like η phases, which effectively improves the stress corrosion resistance of the alloy.

[0029] Meanwhile, by using multi-level continuous temperature control to achieve sequential connection of the aging process at each stage, the frequent removal and reinsertion of components during different stages of aging treatment is avoided, simplifying the production process and significantly meeting the needs of modern industrial continuous and large-scale production.

[0030] In some embodiments, the material of the aluminum alloy component in step S10 includes Al-Li alloy, Al-Mg-Si alloy, or Al-Zn-Mg-Cu alloy.

[0031] In some embodiments, in step S10, the aluminum alloy component is in the T4 state. The "T4 state" as described in this application refers to a process stage where the aluminum alloy component, after solution treatment, reaches a fully stable state through natural aging.

[0032] In some embodiments, during step S10, when performing plastic deformation, this application does not limit the target shape to be processed from the aluminum alloy component, which can specifically be a plate, bar, tube, profile, or strip. In terms of implementation, plastic deformation can be achieved through processes such as stamping, forging, rolling, extrusion, bending, or stretch bending. Specifically, hot deformation or cold deformation can be selected based on the target deformation amount in this step. For example, in some embodiments, step S10 may specifically include: S11, obtain the target deformation of the aluminum alloy component; S12, when the target deformation is less than 20%, the aluminum alloy component is cold-formed to obtain the deformed component; S13, when the target deformation is greater than or equal to 20%, the aluminum alloy component is hot-formed to obtain the deformed component.

[0033] It is understood that, in this article, the target deformation amount refers to the degree of shape change of the target workpiece relative to the initial workpiece that is expected to be processed during the plastic deformation step. In some embodiments, the target deformation amount may refer to the reduction of area (ψ) of the aluminum alloy component.

[0034] It should be noted that during hot forming, the forming temperature should be controlled below the recrystallization temperature of the aluminum alloy.

[0035] In step S20, the regression aging treatment refers to a process of heating at a relatively high temperature for a short time followed by rapid cooling. In some embodiments, the temperature of the regression aging treatment can be 100℃~240℃, and the time can be 1~60min.

[0036] In step S30, the heating method in the low-temperature aging treatment and the high-temperature aging treatment may include, but is not limited to, radiation heating, induction heating or electric heating.

[0037] In actual processing, to better accelerate the nucleation and optimize the dispersion of precipitates, different aging temperatures and times can be used for different types of aluminum alloys. In some embodiments, before step S30, a step may be included to obtain the appropriate low-temperature aging treatment and high-temperature aging treatment temperatures according to the type of aluminum alloy, specifically: In some specific embodiments, when the aluminum alloy component is made of Al-Zn-Mg-Cu alloy, the temperature range of the low-temperature aging treatment is controlled between 100℃ and 160℃, and the time of the low-temperature aging treatment is controlled between 180℃ and 300 minutes; the temperature range of the high-temperature aging treatment is controlled between 120℃ and 220℃, and the time of the high-temperature aging treatment is controlled between 10℃ and 80 minutes. Further, when the aluminum alloy component is made of 7075 aluminum alloy, the temperature range of the low-temperature aging treatment can be controlled between 100℃ and 140℃, and the time of the low-temperature aging treatment can be controlled between 180℃ and 250 minutes; the temperature range of the high-temperature aging treatment is controlled between 140℃ and 200℃, and the time of the high-temperature aging treatment is controlled between 10℃ and 60 minutes.

[0038] In some other specific embodiments, when the material of the aluminum alloy component is 6061 aluminum alloy, the temperature range of the low-temperature aging treatment is controlled at 160℃~180℃, the time of the low-temperature aging treatment is controlled at 30~220min, the temperature range of the high-temperature aging treatment is controlled at 150℃~200℃, and the time of the high-temperature aging treatment is controlled at 40~120min.

[0039] In addition, in step S30, after the steps of performing low-temperature aging treatment and high-temperature aging treatment on the first state component in sequence, and before the step of obtaining the finished component, the following steps may also be included: cooling the component that has undergone the high-temperature aging treatment, and obtaining the finished component after cooling to room temperature (20℃~40℃).

[0040] The following are some specific embodiments. It should be noted that the embodiments described below are exemplary and are only used to explain this application, and should not be construed as limiting this application. Where specific techniques or conditions are not specified in the embodiments, they shall be performed in accordance with the techniques or conditions described in the literature in this field or according to the product instructions. Reagents or instruments whose manufacturers are not specified are all conventional products that can be obtained commercially.

[0041] Example 1 7075 aluminum alloy samples (1.6 mm thick, T4 state) that had been stored for a long time underwent hot deformation, with the deformation controlled at 25%. They were then subjected to regression aging treatment at 180℃ for 10 minutes (abbreviated as 180℃ / 10min; the temperature and time of the regression aging treatment will be described in this manner throughout). The semi-finished samples after regression aging treatment underwent low-temperature aging treatment at 120℃ for 220 minutes; then, they underwent high-temperature aging treatment at 160℃ for 30 minutes; finally, they were furnace cooled to room temperature. After aging, the finished components were removed from the furnace, ready for subsequent performance testing.

[0042] Example 2 Cold deformation was performed on 7075 aluminum alloy samples (2.0 mm thick, T4 state) that had been stored for a long time, with the deformation controlled at 15%, followed by regression aging treatment at 180℃ for 20 min. The semi-finished samples after regression aging were then subjected to low-temperature aging treatment at 120℃ for 220 min; subsequently, they underwent high-temperature aging treatment at 160℃ for 30 min; finally, they were furnace cooled to room temperature. After aging, the aluminum alloy parts were removed from the furnace, ready for subsequent performance testing.

[0043] Example 3 For 7075 aluminum alloy samples (2.0 mm thick, T4 state) that have been left to stand for a long time, cold deformation was performed on the samples, controlling the deformation to be 8%, followed by regression aging treatment at 180℃ for 20 min. The semi-finished samples after regression aging were then subjected to low-temperature aging treatment at 120℃ for 220 min; then, high-temperature aging treatment was performed at 160℃ for 30 min; finally, the samples were cooled to room temperature in the furnace. After aging, the aluminum alloy parts were removed from the furnace, ready for subsequent stress corrosion testing and mechanical property testing.

[0044] Example 4 7075 aluminum alloy samples (2.0 mm thick, T4 state) that had been stored for a long time underwent hot deformation, with the deformation controlled at 25%, followed by regression aging treatment at 100℃ for 1 min. The semi-finished samples after regression aging were then subjected to low-temperature aging treatment at 100℃ for 180 min; subsequently, they underwent high-temperature aging treatment at 140℃ for 10 min; finally, they were cooled to room temperature in the furnace. After aging, the aluminum alloy parts were removed from the furnace, ready for subsequent mechanical property testing.

[0045] Example 5 7075 aluminum alloy samples (2.0 mm thick, T4 state) that had been stored for a long time underwent hot deformation, with the deformation controlled at 25%, followed by regression aging treatment at 240℃ for 60 min. The semi-finished samples after regression aging were then subjected to low-temperature aging treatment at 140℃ for 250 min; subsequently, they underwent high-temperature aging treatment at 200℃ for 60 min; finally, they were furnace cooled to room temperature. After aging, the aluminum alloy parts were removed from the furnace, ready for subsequent mechanical property testing.

[0046] Example 6 Cold deformation was performed on 6061 aluminum alloy samples (2.0 mm thick, T4 state) that had been stored for a long time, with the deformation controlled at 15%. Following this, a regression aging treatment was performed at 160℃ for 30 min. The regressed semi-finished samples were then subjected to low-temperature aging treatment at 180℃ for 220 min; subsequently, high-temperature aging treatment was performed at 200℃ for 45 min; finally, the samples were furnace-cooled to room temperature. After aging, the aluminum alloy parts were removed from the furnace, ready for subsequent performance testing.

[0047] Comparative Example 1 This comparative example is basically the same as Example 1, except that a traditional processing method is used in this comparative example, as follows: For 7075 aluminum alloy samples (1.6 mm thick, T4 temper) that had been stored for an extended period, hot deformation was performed with a deformation controlled at 25%. Following this, solution heat treatment was conducted at 470 ℃ for 60 min, after which the samples were immediately removed and water-quenched to room temperature. The quenched samples were then subjected to artificial aging treatment at 120 ℃ for 24 h, followed by furnace cooling to room temperature. The final samples were used for subsequent performance testing.

[0048] Comparative Example 2 This comparative example is basically the same as Example 2, except that a traditional processing method is used in this comparative example, as follows: For 7075 aluminum alloy samples (2.0 mm thick, T4 temper) that had been stored for an extended period, cold deformation was performed with a deformation controlled at 15%. Following this, solution heat treatment was conducted at 470 ℃ for 60 min, after which the samples were immediately removed and water-quenched to room temperature. The quenched samples were then subjected to artificial aging treatment at 120 ℃ for 24 h, followed by furnace cooling to room temperature. The final samples were used for subsequent performance testing.

[0049] Comparative Example 3 This comparative example is basically the same as Example 3, except that a traditional processing method is used in this comparative example, as follows: For 7075 aluminum alloy samples (2.0 mm thick, T4 temper) that had been stored for an extended period, cold deformation was performed with a deformation controlled at 8%. Following this, solution heat treatment was conducted at 470 ℃ for 60 min, after which the samples were immediately removed and water-quenched to room temperature. The quenched samples were then subjected to artificial aging treatment at 120 ℃ for 24 h, followed by furnace cooling to room temperature. The final samples were used for subsequent performance testing.

[0050] Comparative Example 4 This comparative example is basically the same as Example 6, except that a traditional processing method is used in this comparative example, as follows: For 6061 aluminum alloy samples (2.0 mm thick, T4 temper) that had been stored for an extended period, cold deformation was performed with a deformation controlled at 15%. The samples were then placed in a furnace and solution-treated at 530 °C for 60 min. Immediately afterward, they were removed and water-quenched to room temperature. Following this, the quenched samples underwent artificial aging treatment at 175 °C for 8 h, and were then furnace-cooled to room temperature. After heat treatment, the samples were removed from the furnace and prepared for subsequent performance testing.

[0051] Comparative Example 5 This comparative example scheme is basically the same as that of Example 1, except that the aging process is performed in the following order: regression aging, high-temperature aging, and low-temperature aging. All other parameters and conditions remain unchanged.

[0052] Comparative Example 6 This comparative example scheme is basically the same as that of Example 1, except that the aging treatment order in this comparative example is high-temperature aging treatment, regression aging treatment, and low-temperature aging treatment in sequence. All other parameters and conditions remain unchanged.

[0053] Comparative Example 7 This comparative example is basically the same as Example 2, except that it does not include the regression aging treatment step. Instead, low-temperature aging treatment and high-temperature aging treatment are performed directly after plastic deformation. All other parameters and conditions remain unchanged.

[0054] Comparative Example 8 This comparative example scheme is basically the same as that of Example 1, except that the aging treatment order in this comparative example is low-temperature aging treatment, regression aging treatment, and high-temperature aging treatment in sequence. All other parameters and conditions remain unchanged.

[0055] Comparative Example 9 This comparative example is basically the same as Example 1, except that the aging process is performed in the following order: high-temperature aging, low-temperature aging, and regression aging. All other parameters and conditions remain unchanged.

[0056] Comparative Example 10 This comparative example is basically the same as Example 3, except that the aging process is performed in the following order: low-temperature aging, high-temperature aging, and regression aging. All other parameters and conditions remain unchanged.

[0057] Experimental Example (I): Finished components obtained from Example 1 and Comparative Example 1 were tested for yield strength, tensile strength, and elongation according to the methods given in GB / T 228.1-2021, Metallic materials, tensile testing—Part 1: Tests at room temperature. In Example 1, three groups of samples from the same batch were tested separately, and the average values ​​were compared. The results are shown in Table 1.

[0058] Table 1

[0059] Results analysis: Compared with Comparative Example 1, Example 1 showed significant improvements in yield strength, tensile strength and elongation. In terms of aging time, Comparative Example 1 took 25 hours, while Example 1 took 4.3 hours. This indicates that the method of this application can not only improve the mechanical strengthening effect of aluminum alloy components, but also significantly shorten the aging strengthening treatment time and improve production efficiency. Furthermore, the test results of the three groups of samples in Example 1 are similar, indicating that the method of this application has good stability and reproducibility.

[0060] Experimental Example (II) The finished components obtained from each embodiment and comparative example were tested for tensile strength and elongation using the method of Experimental Example (I). The results are shown in Table 2.

[0061] Table 2

[0062] The test results above show that the finished components obtained in each embodiment have high tensile strength and elongation, indicating that the method proposed in this application is sufficient to replace traditional artificial aging treatment. Moreover, in the comparison between each embodiment and its corresponding conventional aging treatment method, it can be found that the tensile strength and elongation of the products in each embodiment are improved, and the total aging time is much shorter than that of conventional aging treatment. This shows that the method of this application can not only improve the strengthening effect of high-strength aluminum alloy components, but also significantly shorten the aging strengthening treatment time. Furthermore, comparing Example 1 with Comparative Examples 5, 6, 8, and 9, and comparing Example 2 with Comparative Example 7, and Example 3 with Comparative Example 10, it can be found that each example has significantly better tensile strength and elongation. This indicates that sequentially performing regression aging treatment, low-temperature aging treatment, and high-temperature aging treatment is more conducive to promoting the optimized dispersion distribution of precipitates and improving the strengthening effect. Conversely, when high-temperature aging treatment is performed first, followed by low-temperature aging treatment, the dispersion of precipitates is not high, and the precipitates coarsen prematurely. When low-temperature aging treatment or high-temperature aging treatment is performed... When regression aging is performed after aging treatment, the fine strengthening precipitates that have already formed are redissolved or significantly coarsened, the volume fraction and dispersion of the precipitates decrease, and the matrix recovery is intensified, which weakens the dislocation pinning and precipitation strengthening effects. When regression aging treatment is canceled, it becomes difficult to achieve phased and graded gradient control of precipitation behavior inside the grains and at grain boundaries. Grain boundaries are more likely to form continuous or near-continuous coarse precipitates and significantly depleted near-grain boundary areas, which increases the susceptibility to stress corrosion cracking and intergranular corrosion, thereby affecting the strengthening effect and corrosion resistance.

[0063] Experimental Example (3) The finished components obtained in Example 3 and Comparative Example 10 were subjected to stress corrosion tests, and the results are as follows: Figure 3 and Figure 4 As shown. The test methods are: GB / T 15970.2-2000 "Corrosion of metals and alloys - Stress corrosion testing - Part 2: Preparation and application of bending specimens", GB / T 15970.1-2018 "Corrosion of metals and alloys - Stress corrosion testing - Part 1: General test methods".

[0064] Results analysis: The sample of Example 3 developed cracks after 2.5 hours, while the sample of Comparative Example 10 developed cracks after 2 hours, indicating that the sample of Example 3 has better corrosion resistance. Table 2 further illustrates that the method of this application helps to balance the mechanical strengthening effect and stress corrosion resistance of aluminum alloy components.

[0065] It should be noted that this application is not limited to the above-described embodiments. The above embodiments are merely examples, and any embodiments with the same structure and effect as the technical concept within the scope of this application are included in the technical scope of this application. Furthermore, various modifications that can be conceived by those skilled in the art to the embodiments, and other ways of constructing by combining some of the constituent elements of the embodiments, without departing from the spirit of this application, are also included in the scope of this application.

Claims

1. A rapid aging method for high strength and high corrosion resistance that integrates plastic deformation and multi-stage continuous temperature control, characterized in that, Includes the following steps: Aluminum alloy components are plastically deformed to obtain deformed components; The deformed component is subjected to regression aging processing to obtain the first state component; The first-state component is subjected to low-temperature aging treatment and high-temperature aging treatment in sequence to obtain the finished component.

2. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control as described in claim 1, characterized in that, In the step of plastically deforming an aluminum alloy component to obtain a deformed component, the aluminum alloy component is in the T4 state.

3. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control as described in claim 1, characterized in that... The materials of the aluminum alloy components include Al-Li alloy, Al-Mg-Si alloy, or Al-Zn-Mg-Cu alloy.

4. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control as described in claim 1, characterized in that... The steps for plastically deforming aluminum alloy components to obtain the deformed components include: Obtain the target deformation of the aluminum alloy component; When the target deformation is less than 20%, the aluminum alloy component is cold-formed to obtain the deformed component; When the target deformation is greater than or equal to 20%, the aluminum alloy component is hot-formed to obtain the deformed component.

5. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control as described in claim 1, characterized in that... In the step of performing regression aging treatment on the deformed component to obtain the first state component, the temperature of the regression aging treatment is 100℃~240℃ and the time is 1~60min.

6. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control according to claim 3, characterized in that, When the material of the aluminum alloy component is an Al-Zn-Mg-Cu alloy, the temperature range of the low-temperature aging treatment is controlled at 100℃~160℃, the time of the low-temperature aging treatment is controlled at 180~300min, the temperature range of the high-temperature aging treatment is controlled at 120℃~220℃, and the time of the high-temperature aging treatment is controlled at 10~80min.

7. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control as described in claim 6, is characterized in that... When the material of the aluminum alloy component is 7075 aluminum alloy, the temperature range of the low-temperature aging treatment is controlled at 100℃~140℃, the time of the low-temperature aging treatment is controlled at 180~250min, the temperature range of the high-temperature aging treatment is controlled at 140℃~200℃, and the time of the high-temperature aging treatment is controlled at 10~60min.

8. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control according to claim 3, characterized in that, When the material of the aluminum alloy component is 6061 aluminum alloy, the temperature range of the low-temperature aging treatment is controlled at 160℃~180℃, the time of the low-temperature aging treatment is controlled at 30~220min, the temperature range of the high-temperature aging treatment is controlled at 150℃~200℃, and the time of the high-temperature aging treatment is controlled at 40~120min.

9. The high-strength, high-corrosion-resistant rapid aging method based on fusion plastic deformation and multi-stage continuous temperature control according to claim 1, characterized in that, After performing low-temperature aging treatment and high-temperature aging treatment on the first state component in sequence, and before obtaining the finished component, the component that has undergone the high-temperature aging treatment is cooled to room temperature to obtain the finished component.

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