A heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag alloy system, a high-strength and corrosion-resistant aluminum alloy, and their applications

Abstract

The present invention discloses a heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy, a high-strength corrosion-resistant aluminum alloy and their applications. This method is obtained by subjecting the T6 state or thermally fatigued state Al-Cu-Mg-Ag series alloy to solution re-treatment and re-aging treatment in sequence. Based on the synergistic effect among various steps, this method can not only restore the mechanical properties of the alloy whose strength has decayed due to service in a high-temperature environment, but also improve the corrosion resistance of the alloy, extend the service life of the alloy, and realize the reuse of large alloy devices. The corrosion-resistant aluminum alloy prepared by this method has more Ω-phase precipitates with a higher number density, and the width of the PFZ is reduced, strengthening the corrosion resistance of the alloy on the premise of improving the mechanical strength of the aluminum alloy. The alloy material prepared based on the regeneration strengthening method provided by the present invention not only has excellent mechanical properties, but also has good corrosion resistance, and can meet the performance requirements of the materials for the internal and external wheels of airplanes.

Description

Technical Field

[0001] The present invention relates to a method for regenerating and strengthening a heat-fatigue aluminum alloy, specifically to a heat treatment regeneration and strengthening method for an Al-Cu-Mg-Ag series alloy, a high-strength and corrosion-resistant aluminum alloy and its application, belonging to the technical field of heat-resistant alloys. Background Art

[0002] With the development of the aerospace field, the demand for lightweight, high-strength and corrosion-resistant alloys is becoming more and more urgent, and the requirements for material properties are also becoming more and more stringent. The hub material of an aircraft usually uses 2014 alloy as the inner hub in contact with the brake pair, and 7050 alloy as the outer hub.

[0003] The lightweight and high-strength Al-Cu-Mg-Ag series alloy has excellent fatigue resistance and thermal stability. Applying it to the hub material can well solve problems such as strength and heat resistance. In this service state, the alloy material will not only be affected by the coupled action of high temperature and cyclic stress, but also be affected by factors such as dust particles, oil stains, weather, etc. For such a complex service environment, it is required that the aluminum alloy has excellent comprehensive properties. However, improving the corrosion resistance of the aluminum alloy through heat treatment often sacrifices a certain amount of strength. Therefore, it is necessary to develop a heat treatment process that can simultaneously improve the strength and corrosion resistance of the alloy, and improve the corrosion resistance of the alloy without sacrificing the strength of the alloy. On the other hand, when this material is applied to the aircraft hub, when high temperature is generated during the aircraft braking process, the long-term cyclic high-heat environment will cause the Ω phase in the Al-Cu-Mg-Ag alloy to coarsen or transform into the S phase, resulting in strength attenuation. After such large alloy components are replaced, they can often only be recycled and remelted, which will consume more energy and cost.

[0004] Therefore, it is necessary to find a new way from the heat treatment process, which can not only improve the corrosion resistance of the alloy without losing strength, but also enable the performance of the Al-Cu-Mg-Ag alloy hub in the heat fatigue state to be restored, meeting the reuse standard. Summary of the Invention

[0005] Aiming at the problems existing in the prior art, the first object of the present invention is to provide a heat treatment regeneration and strengthening method for an Al-Cu-Mg-Ag series alloy. Based on the synergistic effect between each step, this method can not only restore the mechanical properties of the alloy whose strength has decayed due to service in a high-temperature environment, but also improve the corrosion resistance of the alloy, extend the service life of the alloy, and realize the reuse of large alloy devices.

[0006] The second object of the present invention is to provide an Al-Cu-Mg-Ag series high-strength and corrosion-resistant alloy. Through re-solution treatment and re-aging treatment, this aluminum alloy can not only promote the precipitation of intragranular precipitates in the aluminum alloy, improve the morphology and distribution of grain boundary precipitates, weaken the precipitate-free zone, and reduce the PFZ width, but also enhance the mechanical strength of the alloy and strengthen the corrosion resistance of the alloy.

[0007] The third object of the present invention is to provide an application of a corrosion-resistant Al-Cu-Mg-Ag series alloy for preparing aircraft wheels. The alloy material prepared based on the regeneration strengthening method provided by the present invention not only has excellent mechanical properties but also has good corrosion resistance. After testing, for the thermally fatigue aluminum alloy treated by the regeneration strengthening method provided by the present invention, its mechanical tensile strength is 490 - 520 MPa, the yield strength is 450 - 470 MPa, the elongation is 13% - 14%, the maximum depth of intergranular corrosion is below 79.8 μm, and the electrochemical corrosion current is 4.4E-4 A / cm 2 The following meets the performance requirements of the internal and external wheel materials for aircraft.

[0008] To achieve the above technical objects, the present invention provides a heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy, which is obtained by sequentially subjecting the T6 state or thermally fatigue state Al-Cu-Mg-Ag series alloy to re-solution treatment and re-aging treatment; the conditions for the re-solution treatment are: heat preservation at 508 - 512 °C for 1 - 2 h, and after water quenching, a re-solution state alloy is obtained; the conditions for the re-aging treatment are: heat preservation of the re-solution state alloy at 160 - 185 °C for 13 - 18 h, and after water cooling, it is obtained.

[0009] The heat treatment regeneration strengthening method provided by the present invention, through re-solution treatment, promotes the occurrence of Ostwald ripening phenomenon in the grains, causes grain growth, reduces the total length of grain boundaries, thereby reducing the intergranular corrosion sensitivity of the alloy; and the re-aging treatment can promote secondary precipitation inside the alloy, strengthen the precipitation of Ω phase, reduce the consumption of solute by intergranular precipitates, thereby further reducing the PFZ width, and improving the intergranular corrosion resistance of the alloy on the premise of ensuring the mechanical properties of the alloy.

[0010] The solution re-treatment and re-aging treatment adopted by the present invention should be strictly carried out in accordance with the above requirements. The solution re-treatment stage is a high-temperature stage, and its purpose is to dissolve back the overly coarsened Ω phase and the transformed θ or S phase in the thermal fatigue alloy, ensuring that the alloy can be restored to the initial solution state again. Since the long-range diffusion of solutes requires more time, the coarse second phase cannot completely eliminate segregation during the solution re-treatment. Among them, local aggregation of Cu, Mg, and Ag solutes still exists. At this time, re-aging treatment is beneficial to the nucleation and growth of Mg-Ag clusters and provides sufficient solutes for the growth of the Ω phase, increasing the number density and average diameter of the Ω phase in the alloy. The copper-rich intermetallic particles inside the alloy material after high-temperature solution re-treatment will partially dissolve back, reducing the microcrack initiation sources, and the plasticity will continue to increase. And re-aging treatment under low-temperature conditions will not only affect the coarsening (thickening) of the Ω phase, but also according to the interface strengthening formula, when the volume fraction is certain, at a larger aspect ratio, the strengthening contribution of the Ω phase is stronger. Therefore, to a certain extent, the strength of the alloy is improved. The precipitation of more Ω phases with higher number density can effectively weaken the solute consumption for the growth of GBPs, reduce the width of PFZ, and improve the intergranular corrosion resistance of the alloy.

[0011] As a preferred solution, the Al-Cu-Mg-Ag alloy system includes the following components by mass percentage: 4.8 - 5.4% Cu, 0.7 - 1.1% Mg, 0.4 - 0.7% Ag, 0.45 - 0.8% Mn, 0.08 - 0.15% Zr, 0.03 - 0.06% Ti, each unavoidable impurity element is less than 0.05%, and the total amount of impurity elements is less than 0.15%, and the balance is Al.

[0012] As a preferred solution, the thermally fatigued Al-Cu-Mg-Ag alloy system is the T6 state Al-Cu-Mg-Ag alloy system under thermal exposure.

[0013] As a preferred solution, the conditions of thermal exposure are: the temperature is 200 - 220 °C, and the time ≥ 100 h.

[0014] As a preferred solution, the preparation process of the T6 state Al-Cu-Mg-Ag alloy system is: mixing the raw materials including each component evenly and then melting them together to obtain an ingot; subjecting the ingot to three-stage homogenization heat treatment, hot rolling treatment, solution treatment and aging treatment in sequence to obtain the alloy.

[0015] As a preferred solution, the process of the three-stage homogenization heat treatment is: the temperature of the first-stage homogenization heat treatment is 445 - 455 °C, and the time is 5 - 8 h; the temperature of the second-stage homogenization heat treatment is 475 - 485 °C, and the time is 5 - 8 h; the temperature of the third-stage homogenization heat treatment is 500 - 510 °C, and the time is 24 - 30 h.

[0016] As a preferred solution, the process of the hot rolling treatment is as follows: The alloy after homogenization heat treatment is kept at 455 - 465 °C for 1 - 3 h, hot rolled 8 - 10 times until the final thickness of the alloy is 2 - 3 mm, and air cooled to room temperature after rolling.

[0017] As a preferred solution, the process of the solution treatment is as follows: The alloy after hot rolling treatment is kept at 505 - 515 °C for 1 - 2 h, and quenched to obtain a solution-state alloy.

[0018] As a preferred solution, the quenching method is water quenching, and the quenching transfer time < 10 s.

[0019] As a preferred solution, the process of the aging treatment is as follows: The solution-state alloy is kept at 160 - 185 °C for 14 - 16 h, and water cooled to obtain the product.

[0020] The present invention also provides a corrosion-resistant Al-Cu-Mg-Ag series alloy obtained by the regeneration strengthening method described in any one of the above.

[0021] The present invention also provides an application of the heat treatment regeneration strengthening method for Al-Cu-Mg-Ag series alloy, which is used for the regeneration strengthening of aluminum alloy materials for aircraft inner and outer hubs.

[0022] The regeneration strengthening method provided by the present invention can not only realize the regeneration of the mechanical properties and the strengthening of the corrosion resistance of the thermal fatigue aluminum alloy, but also greatly improve the comprehensive performance of the T6 state alloy. After testing, for the aluminum alloy prepared by the regeneration strengthening method provided by the present invention, its mechanical tensile strength is 490 - 520 MPa, the yield strength is 450 - 470 MPa, the elongation is 13% - 14%, the maximum depth of intergranular corrosion is below 79.8 μm, and the electrochemical corrosion current is 4.4E-4 A / cm 2 The following meets the performance requirements of the materials for aircraft inner and outer hubs.

[0023] Compared with the prior art, the beneficial technical effects of the present invention are as follows:

[0024] 1) The heat treatment regeneration strengthening method provided by the present invention is based on the synergistic effect among various steps. It can not only restore the mechanical properties of the alloy whose strength has decayed due to service in a high-temperature environment, but also improve the corrosion resistance of the alloy, extend the service life of the alloy, and realize the reuse of large alloy devices;

[0025] 2) The high-strength and corrosion-resistant aluminum alloy provided by the present invention can not only promote the precipitation of intragranular precipitates in the aluminum alloy through re-solution treatment and re-aging treatment, but also improve the morphology and distribution of grain boundary precipitates, weaken the precipitate-free zone, and reduce the width of the PFZ. Therefore, it can simultaneously improve the mechanical strength and corrosion resistance of the alloy;

[0026] 3) In the technical solution provided by the present invention, through solution re-treatment, the precipitation strengthening phases and intermetallic particles in the alloy are basically redissolved. After the second phase of this part is redissolved, on the one hand, it can strengthen the precipitation process of the re-aging Ω phase, and on the other hand, it can reduce the area of the corrosion cell formed between the second phase and the matrix. Thereby, it can ensure that the strength is not reduced while improving the corrosion resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to make the technical solution and beneficial effects of the present invention clearer, the following drawings are provided for further illustration:

[0028] Figure 1 TEM intragranular microstructure diagrams of the samples obtained in Example 1, Example 2, Comparative Example 1, and Comparative Example 2; wherein, Figure 1 (a) is the TEM diagram of the intragranular HRSA alloy of the sample obtained in Example 1; Figure 1 (b) is the TEM diagram of the intragranular RSA alloy of the sample obtained in Example 2; Figure 1 (c) is the TEM diagram of the intragranular alloy after SA of the sample obtained in Comparative Example 1; Figure 1 (d) is the TEM diagram of the intragranular H alloy of the sample obtained in Comparative Example 2;

[0029] Figure 2 TEM grain boundary microstructure diagrams of the samples obtained in Example 1, Example 2, Comparative Example 1, and Comparative Example 2; wherein, Figure 2 (a) is the TEM diagram of the grain boundary microstructure of HRSA of the sample obtained in Example 1; Figure 2 (b) is the TEM diagram of the grain boundary microstructure of RSA of the sample obtained in Example 2; Figure 2 (c) is the TEM diagram of the grain boundary microstructure of SA of the sample obtained in Comparative Example 1; Figure 2 (d) is the TEM diagram of the grain boundary microstructure of H of the sample obtained in Comparative Example 2;

[0030] Figure 3 Metallographic microstructure diagrams of the samples of Example 1, Example 2, Comparative Example 1, and Comparative Example 2;

[0031] Wherein, Figure 3 (a) is the metallographic microstructure diagram of HRSA of the sample obtained in Example 1; Figure 3 (b) is the metallographic microstructure diagram of RSA of the sample obtained in Example 2; Figure 3 (c) is the metallographic microstructure diagram of SA of the sample obtained in Comparative Example 1; Figure 3 (d) is the metallographic microstructure diagram of H of the sample obtained in Comparative Example 2. DETAILED DESCRIPTION OF THE INVENTION

[0032] The raw materials used in the embodiments and comparative examples of the present invention are Al-Cu-Mg-Ag series alloys, and their components are in mass percentage and include the following components: 4.8-5.4% Cu, 0.7-1.1% Mg, 0.4-0.7% Ag, 0.45-0.8% Mn, 0.08-0.15% Zr, 0.03-0.06% Ti. Each inevitable impurity element is less than 0.05%, and the total amount of impurity elements is less than 0.15%, with the balance being Al.

[0033] The raw materials used in the embodiments and comparative examples of the present invention are Al-Cu-Mg-Ag series alloys. The hot rolling temperature is 460±5°C, and it is held for 2 h, and then multi-pass hot rolling is carried out until the final thickness of the alloy is 2.5 mm. The change in the thickness of the alloy in each pass during the rolling process is: 23 mm→20 mm→18 mm→14 mm→9 mm→7 mm→5 mm→4 mm→2.5 mm; cold cutting lubrication is used for rolling, and a metal rolling emulsion is used; after rolling, it is air-cooled to room temperature.

[0034] In the specific embodiments of the present invention, the tensile properties are based on the GB / T288.1-2010 standard, and the intergranular corrosion properties are based on the GB / T7998-2005 standard.

[0035] Example 1

[0036] Taking the hot-rolled Al-Cu-Mg-Ag series alloy as the raw material, its components are in mass percentage and include the following components: 4.96% Cu, 0.96% Mg, 0.63% Ag, 0.57% Mn, 0.13% Zr, 0.02% Ti. Each inevitable impurity element is <0.05%, and the total amount of impurity elements is <0.15%, with the balance being Al. The following heat treatment is carried out on the raw material:

[0037] Step 1: Solution treatment. First, raise the temperature of the resistance furnace to 510±2°C, and then place the homogenized hot-rolled alloy in the resistance furnace and hold it for 1.5 h; water quench, and the quenching transfer time is <10 s to obtain a solution-state product.

[0038] Step 2: Aging treatment. Raise the temperature of the resistance furnace to 165±2°C, transfer the solution-state alloy to the resistance furnace, and hold it for 15 h; water cool to obtain a T6-state alloy product.

[0039] Step 3: Thermal exposure treatment. Raise the temperature of the resistance furnace to 200±2°C, and then place the T6-state alloy in the resistance furnace and hold it for 100 h; water cool to obtain a thermal exposure-state product.

[0040] Step 4: Re-solution treatment. Raise the temperature of the resistance furnace to 510±2°C, and then transfer the thermal exposure-state alloy to the resistance furnace and hold it for 1.5 h; water quench, and the quenching transfer time is <10 s to obtain a re-solution-state product.

[0041] Step 5: Re-aging treatment. Raise the temperature of the resistance furnace to 165 ± 2 °C, then transfer the heavy solution-treated alloy into the resistance furnace and hold for 15 h; water-cool to obtain the heavy solution re-aged alloy product after thermal exposure, which is abbreviated as HRSA. The specific mechanical property data are shown in Table 1, and the specific corrosion resistance data are shown in Table 2. Figure 1 (a) is the TEM image of the intragranular of the alloy after HRSA; Figure 2 (a) is the TEM image of the grain boundary of the alloy after HRSA; Figure 3 (a) is the metallographic structure diagram of the alloy after HRSA.

[0042] Example 2

[0043] Steps 1 and 2 are exactly the same as those in Example 1, except that in Example 2, the alloy does not undergo thermal exposure treatment and directly undergoes heavy solution re-aging treatment.

[0044] Step 3: Heavy solution treatment. Raise the temperature of the resistance furnace to 510 ± 2 °C, then transfer the thermally exposed alloy into the resistance furnace and hold for 1.5 h; water-quench, and the quenching transfer time < 10 s to obtain the heavy solution-treated product.

[0045] Step 4: Re-aging treatment. Raise the temperature of the resistance furnace to 165 ± 2 °C, then transfer the heavy solution-treated alloy into the resistance furnace and hold for 15 h; water-cool to obtain the heavy solution re-aged alloy product after thermal exposure, which is abbreviated as RSA. The specific mechanical property data are shown in Table 1, and the specific corrosion resistance data are shown in Table 2. Figure 1 (b) is the TEM image of the intragranular of the alloy after RSA; Figure 2 (b) is the TEM image of the grain boundary of the alloy after RSA; Figure 3 (b) is the metallographic structure diagram of the alloy after RSA.

[0046] Comparative Example 1

[0047] The alloy and preparation method used in this comparative example are exactly the same as those in Example 1, except that Steps 3 to 5 are not performed, so as to obtain the Al-Cu-Mg-Ag alloy in the T6 state, which is abbreviated as SA. The specific mechanical property data are shown in Table 1, and the specific corrosion resistance data are shown in Table 2. Figure 1 (c) is the TEM image of the intragranular of the alloy after SA; Figure 2 (c) is the TEM image of the grain boundary of the alloy after SA; Figure 3 (c) is the metallographic diagram of the SA alloy.

[0048] Comparative Example 2

[0049] The alloy and preparation method used in this comparative example are exactly the same as those in Example 1, except that Steps 4 and 5 are not performed, and this product is abbreviated as H. The specific mechanical property data are shown in Table 1, and the specific corrosion resistance data are shown in Table 2. Figure 1 (d) is the TEM image inside the grains of alloy H; Figure 2 (d) is the TEM image at the grain boundaries of alloy H; Figure 3 (d) is the metallographic image of alloy H.

[0050] The present invention also conducted relevant tests on the samples obtained in the above examples and comparative examples. The test process was as follows: Each group of room-temperature tensile specimens was tested on an MTS 810 tensile testing machine at a loading rate of 2 mm / min. Electrochemical tests were carried out using a CHI604E electrochemical workstation, and the solution used was 3.5 wt.% NaCl solution. In accordance with the requirements of GB / T 7998-2005, intergranular corrosion tests were conducted on the aged specimens. One rolling surface was selected as the corrosion test surface, and the other non-test surfaces were sealed with resin. The surface to be corroded was polished, and then the treated samples were placed in a corrosion solution (aqueous solution of 57 g / L NaCl + 10 g / ml H2O2) for intergranular corrosion. The ratio of the experimental area of the sample to the volume of the solution was 4 mm 2 / ml, the temperature was controlled at (25 ± 1) °C, and the total immersion time was 6 h. The corrosion cross-section of the tested samples was polished, and the maximum corrosion depth was photographed and measured for rating using a metallographic microscope.

[0051] Table 1 shows the mechanical property tests of Examples 1 and 2 and Comparative Examples 1 and 2

[0052] alloy Tensile strength (MPa) Yield strength (MPa) Elongation rate (%) Example 1 497 451 13 Example 2 498 451 14 Comparative Example 1 496 448 14 Comparative Example 2 313 409 11

[0053] Table 2 shows the corrosion resistance tests of Examples 1 and 2 and Comparative Examples 1 and 2

[0054] alloy Maximum depth of intergranular corrosion (μm) <![CDATA[Corrosion current density (A / cm 2 )]]> Example 1 82.7 8.5E-4 Example 2 79.8 4.4E-4 Comparative Example 1 91.4 1.2E-3 Comparative Example 2 84.6 1.3E-3

[0055] The results in Table 1 and Table 2 show that compared with the traditional T6 process, the yield strength and tensile strength of the alloy obtained in Example 1 can reach those of the T6-state product. Although the elongation rate has a slight decrease, the corrosion resistance is improved; the strength and elongation rate of the alloy obtained in Example 2 are the same as those in the T6 state, and this heat treatment process will not cause loss of the alloy's mechanical properties. In addition, the corrosion resistance of the alloy is also improved compared with the T6 state. Combining Figure 1 、 Figure 2 and Figure 3 it can be seen that after the alloy is treated by the heat treatment process of the present invention, the grain size in the alloy becomes significantly larger, but the number density of Ω phases increases, the average diameter increases, the intermetallic particles in the alloy decrease, and the width of the grain boundary PFZ decreases. This is the reason for the basic recovery of its strength and the improvement of its corrosion resistance.

[0056] From the comparison between the above comparative examples and examples, it is found that when the heat-treatment process of the present invention is used to regenerate the heat-fatigue aluminum alloy, its tensile strength is 497-498 MPa, the yield strength is 451 MPa, the elongation is 13%-14%, the maximum depth of intergranular corrosion is below 82.7 μm, and the electrochemical corrosion current density is 8.5E-4 A / cm 2 Below.

[0057] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy, characterized in that: It is obtained by subjecting the T6 state or thermally fatigued state Al-Cu-Mg-Ag series alloy to solution re-treatment and re-aging treatment in sequence; the conditions of the solution re-treatment are: heat preservation at 508-512 °C for 1-2 h, and after water quenching, a solution re-treated alloy is obtained; the conditions of the re-aging treatment are: heat preservation of the solution re-treated alloy at 160-185 °C for 13-18 h, and after water cooling, it is obtained.

2. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 1, characterized in that: The Al-Cu-Mg-Ag series alloy comprises the following components by mass percentage: 4.8-5.4% Cu, 0.7-1.1% Mg, 0.4-0.7% Ag, 0.45-0.8% Mn, 0.08-0.15% Zr, 0.03-0.06% Ti, each inevitable impurity element is less than 0.05%, and the total amount of impurity elements is less than 0.15%, and the balance is Al.

3. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 2, characterized in that: The thermally fatigued state Al-Cu-Mg-Ag series alloy is the T6 state Al-Cu-Mg-Ag series alloy under thermal exposure; the conditions of the thermal exposure are: the temperature is 200-220 °C, and the time ≥ 100 h.

4. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 1 or 3, characterized in that: The preparation process of the T6 state Al-Cu-Mg-Ag series alloy is: mixing the raw materials including each component evenly and then melting them together to obtain an ingot; subjecting the ingot to three-stage homogenization heat treatment, hot rolling treatment, solution treatment and aging treatment in sequence, and it is obtained.

5. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 4, characterized in that: The process of the three-stage homogenization heat treatment is: the temperature of the first-stage homogenization heat treatment is 445-455 °C, and the time is 5-8 h; the temperature of the second-stage homogenization heat treatment is 475-485 °C, and the time is 5-8 h; the temperature of the third-stage homogenization heat treatment is 500-510 °C, and the time is 24-30 h.

6. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 4, characterized in that: The process of the hot rolling treatment is: heat preservation of the alloy after homogenization heat treatment at 455-465 °C for 1-3 h, hot rolling 8-10 times until the final thickness of the alloy is 2-3 mm, and air cooling to room temperature after the rolling ends.

7. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 4, characterized in that: The process of the solution treatment is: heat preservation of the alloy after hot rolling treatment at 505-515 °C for 1-2 h, and after quenching, a solution-treated alloy is obtained; the quenching method is water quenching, and the quenching transfer time < 10 s.

8. The heat treatment regeneration strengthening method for an Al-Cu-Mg-Ag series alloy according to claim 7, characterized in that: The process of the aging treatment is: heat preservation of the solution-treated alloy at 160-185 °C for 14-16 h, and after water cooling, it is obtained.

9. An Al-Cu-Mg-Ag series high-strength corrosion-resistant alloy, characterized in that: It is obtained by the regeneration strengthening method described in any one of claims 1-8.

10. The application of the Al-Cu-Mg-Ag series high-strength corrosion-resistant alloy according to claim 9, characterized in that: It is used for preparing the inner and outer hubs of an aircraft.

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