CN110592504A - Heat treatment method for improving comprehensive performance of alloy plate - Google Patents
Heat treatment method for improving comprehensive performance of alloy plate Download PDFInfo
- Publication number
- CN110592504A CN110592504A CN201810598455.6A CN201810598455A CN110592504A CN 110592504 A CN110592504 A CN 110592504A CN 201810598455 A CN201810598455 A CN 201810598455A CN 110592504 A CN110592504 A CN 110592504A
- Authority
- CN
- China
- Prior art keywords
- alloy
- treatment
- equal
- less
- aging
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Abstract
The invention provides a heat treatment method for improving the comprehensive performance of an alloy, which comprises the following components in percentage by weight: 3.5-4.5% of Cu, 1.4-1.80% of Li, 0.2-0.8% of Mg, 0.2-0.8% of Zn, 0.04-0.20% of Zr, 0.20-0.80% of Mn, 0.05-0.35% of Sc, 0.2-0.8% of Ag, any 1-3 of Er 0.10-0.25%, less than or equal to 0.08% of Si, less than or equal to 0.10% of Fe, less than or equal to 0.10% of Ti, less than or equal to 0.05% of other impurities, less than or equal to 0.15% of total amount, and the balance of Al. The method comprises the steps of carrying out solution quenching on the alloy, carrying out spheroidizing aging treatment for 10-20 hours at 220-280 ℃, forming a micron-sized granular precipitated phase in the crystal, converting large-size needle-shaped Weishi bodies remaining in the crystal boundary into an interrupted granular equilibrium phase, and then repeating the solution treatment, cold deformation and aging treatment to dissolve the micron-sized granular precipitated phase back and promote the precipitation of the nanometer-sized precipitated phase, so as to obtain a characteristic structure that the intra-crystal precipitated phase is uniform and fine and the crystal boundary precipitated phase is intermittently distributed, thereby improving the comprehensive performance of the alloy. The method is suitable for thick alloy plates, forgings and large-section extruded materials used in the fields of aviation and weapons.
Description
Technical Field
The invention relates to a heat treatment technology of an alloy, in particular to a heat treatment method for improving the comprehensive performance of an alloy plate.
Background
With the continuous development of high-reliability and high-weight reduction requirements in the aerospace field, alloys with lower density and higher strength are required, and the existing alloys are insufficient in strength grade (500MPa) and density. To achieve this goal, the content of some alloy elements is moderately increased, the solid solution saturation degree of the alloy is improved, and the alloy with higher strength and lower density is obtained, however, a great amount of flaky needle-shaped Weishi (Al) is easily and rapidly precipitated in the intragranular and grain boundary areas during the hot working deformation process of thick plates, forgings and large-section profiles in the process2CuLi，T1Phase) "and the strong" heredity "of the structure is difficult to eliminate in the subsequent solid solution and aging processes, thereby deteriorating the properties of plasticity, fracture toughness and corrosion and influencing the subsequent development and application of the alloy.
Therefore, a technical scheme aiming at the problem that the comprehensive performance is influenced because the 'widmannstatten' structure in the high-alloy-content alloy product is difficult to eliminate is needed to meet the needs of the prior art.
Disclosure of Invention
The technical scheme of solid solution, spheroidizing aging and secondary solid solution provided by the invention is characterized in that large-size sheet needle-shaped T distributed on a crystal boundary/subcrystal boundary1The phase is changed into a granular equilibrium phase which is distributed discontinuously, thereby greatly improving the fracture toughness and the corrosion resistance of the alloy without reducing the strength of the alloy and obtaining a product with excellent comprehensive performance.
The purpose of the invention is: the heat treatment method for improving the comprehensive performance of the alloy is provided, and the comprehensive performance of the alloy thick plate with high alloy content, the forge piece and the extruded material can be greatly improved by the method. The technical scheme for realizing the aim of the invention is as follows:
in a heat treatment process for improving the overall properties of an alloy sheet, the improvement comprising: after the alloy is subjected to solution quenching, performing spheroidization aging treatment at 220-280 ℃ for 10-20 h, and then repeating solution treatment, cold deformation and aging treatment;
the alloy comprises the following components in percentage by weight: 3.5-4.5% of Cu, 1.4-1.80% of Li, 0.2-0.8% of Mg, 0.2-0.8% of Zn0.04-0.20% of Zr, 0.20-0.80% of Mn, 0.05-0.35% of Sc, 0.2-0.8% of Ag, any 1-3 of Er 0.10-0.25%, less than or equal to 0.08% of Si, less than or equal to 0.10% of Fe, less than or equal to 0.10% of Ti, less than or equal to 0.05% of other impurities, less than or equal to 0.15% of total amount, and the balance of Al.
In a first preferred embodiment of the present invention:
1.1 the plate solution quenching comprises the following steps: solid dissolving in an air furnace or a salt bath furnace at 515-535 ℃, keeping the temperature (6.0-8.0) minutes according to the thickness of the plate unit (mm), and then quenching with water at room temperature;
1.2 the spheroidizing aging treatment comprises the following steps: aging the alloy plate subjected to the solution quenching treatment in an air furnace with a circulating device at 220-280 ℃ for 10-20 h, and taking out for air cooling or air cooling to room temperature;
1.3 the repeated solution treatment comprises: after spheroidizing aging treatment, putting the alloy plate into an air furnace or a salt bath furnace at 520-540 ℃ for solution treatment, keeping the temperature for 3.0-4.0 minutes according to the thickness of the plate unit (mm), and then carrying out water quenching at room temperature;
1.4 the cold deformation process comprises: performing cold drawing on the quenched plate within 4 hours according to the cold deformation amount of 3.0-5.0%;
1.5 the aging treatment comprises the following steps: after cold deformation treatment, natural aging or artificial aging treatment is carried out;
1.5.1 the natural aging comprises: placing under room temperature strip for at least 120 h;
1.5.2 the artificial aging is a two-stage artificial aging treatment, comprising: and keeping the temperature for 16-24 h at the first stage at 120-135 ℃ and keeping the temperature for 8-14 h at the second stage at 143-155 ℃, and continuously heating along with the furnace in a two-stage aging chamber.
In a second preferred embodiment of the present invention:
the heating temperature of the solution treatment is 520 ℃;
the heating temperature of the spheroidizing aging treatment is 220-280 ℃;
the heating temperature of the repeated solution treatment is 530 ℃.
In the third preferred technical scheme of the invention:
the method is applicable to the alloy components with the weight percentage of Cu as follows: 3.8% or 4%; the weight percentage of Li in the alloy components applicable to the method is as follows: 1.5% or 1.70%.
In a fourth preferred technical solution of the present invention: the alloy applicable to the method comprises the following components in percentage by weight: 0.60% of Mg, 0.50% of Zn, 0.12% of Zr, 0.50% of Mn, 0.20% of Sc, 0.60% of Ag and 0.15% of Er. 0.08 percent of Si, 0.08 percent of Fe, 0.08 percent of Ti, less than or equal to 0.05 percent of other impurities, less than or equal to 0.15 percent of total amount and the balance of Al.
Compared with the closest prior art, the technical scheme provided by the invention has the following excellent effects:
1. the heat treatment process provided by the invention can greatly improve the comprehensive performance of the alloy plate with high Li content in the alloy, so that the alloy strength reaches 600MPa, and meanwhile, the alloy plate has excellent fatigue and corrosion resistance;
2. the spheroidizing aging process in the heat treatment process in the technical scheme provided by the invention enables the advantages of other necessary procedures in the alloy preparation process to be utilized and exerted to the maximum extent, and the process is simple and feasible and has strong industrial applicability;
3. the technical scheme of the invention solves the problem of large-size T through solution treatment, spheroidizing aging and secondary solution treatment1The problem of phase inheritance enlarges the window between the design and the preparation of alloy components.
Description of the drawings:
drawing the high power tissue morphology of a hot rolled plate with the thickness of 180 mm;
drawing a high-power metallographic structure of a hot-rolled plate with the thickness of 280 mm after solid solution, pre-stretching and aging treatment;
FIG. 3 shows a high-power metallographic structure of a thick plate of 80mm after being processed by the technical scheme of the first embodiment of the invention;
the high-power metallographic structure of a forging with the thickness of 4100 mm after solid solution, cold compression and aging treatment is shown in the figure;
FIG. 5 shows the high power metallographic structure of a forging of 100mm thickness after treatment according to the second embodiment.
Detailed description of the preferred embodiments
The present invention will be further described with reference to specific examples, but the present invention is not limited to the following examples.
Example one
The method for improving the comprehensive performance of the alloy comprises the following components in percentage by weight: cu3.8 percent of Cu1.61 percent of Li, 0.38 percent of Mg, 0.42 percent of Zn, 0.38 percent of Mn, 0.10 percent of Zr, 0.06 percent of Ti, 0.06 percent of Si, 0.08 percent of Fe and the balance of Al, wherein a hot rolled plate sample with the thickness of 80mm (the high-power metallographic structure of which is shown in a figure 1) is subjected to solution quenching for 8 hours at 530 ℃, water quenching at room temperature and pre-stretching with the deformation of 4.6 percent, two-stage artificial aging treatment (125 ℃/20h +145 ℃/10h) and solution quenching (530 ℃/8h, water quenching at room temperature and spheroidizing aging (240 ℃/16h) and secondary (or repeated) solution quenching (530 ℃/4h, water quenching at room temperature) + pre-stretching (the pre-stretching deformation of 4.6 percent) and two-stage artificial aging treatment (125 ℃/20h +145 ℃/10h), and then the tensile property, the fracture property and intercrystalline, spalling and anti-stress corrosion property (C ring) of the plate are respectively measured, And observing the high-power microstructure morphology as shown in table 1, fig. 2 and fig. 3.
From fig. 2 and 3, it can be found that the large-size residual widmannstatten structures in the alloy thick plate treated by the method of the invention are converted into discrete granular precipitated phases, so that the plasticity, fracture toughness and corrosion resistance of the alloy thick plate are obviously improved on the premise of not reducing the strength, and the comprehensive performance is obviously improved.
TABLE 1 comparison of the Properties of the alloy sheet according to the invention and the conventional treatment method
Example two
The method for improving the comprehensive performance of the alloy comprises the following components in percentage by weight: 4.5 percent of Cu, 1.8 percent of Li, 0.46 percent of Mg, 0.35 percent of Ag, 0.20 percent of Zn, 0.38 percent of Mn, 0.08 percent of Zr, 0.03 percent of Ti, 0.06 percent of Si, 0.08 percent of Fe and the balance of Al, and respectively carrying out solution quenching (535 ℃/10h, room temperature water quenching) + cold pressing deformation (compression deformation 5.0 percent) + two-stage artificial aging treatment (120 ℃/20h +148 ℃/14h) and solution quenching (535 ℃/10h, room temperature water quenching) + spheroidizing aging (260 ℃/20h) + secondary solution quenching (535 ℃/5h, room temperature water quenching) + cold pressing deformation (compression deformation 5.0 percent) + two-stage artificial aging treatment (120 ℃/20h +148 ℃/14h) on a free forging with the thickness of 100 mm. After the completion, the tensile and fracture properties and intercrystalline, spalling and stress corrosion resistance (C-ring) of the forgings were measured, respectively, and the results are shown in table 2, and the high power structures of the forgings after different processes are shown in fig. 4 and 5.
Fig. 4 and 5 show that after the alloy plate is processed by the method provided by the invention, the strength, plasticity, fracture toughness and corrosion resistance of the forging are obviously improved.
Table 2 comparison of the properties of the alloy sheets treated according to the invention with those treated according to the conventional method
TABLE 3 composition of alloys of each example
Claims (5)
1. A heat treatment method for improving the overall performance of an alloy sheet material, the method comprising: after the alloy is subjected to solution quenching, performing spheroidization aging treatment at 220-280 ℃ for 10-20 h, and then repeating solution treatment, cold deformation and aging treatment;
the alloy comprises the following components in percentage by weight: 3.5-4.5% of Cu, 1.4-1.80% of Li, 0.2-0.8% of Mg, 0.2-0.8% of Zn, 0.04-0.20% of Zr, 0.20-0.80% of Mn, 0.05-0.35% of Sc, 0.2-0.8% of Ag, any 1-3 of Er0.10-0.25%, less than or equal to 0.08% of Si, less than or equal to 0.10% of Fe, less than or equal to 0.10% of Ti, less than or equal to 0.05% of other impurities, less than or equal to 0.15% of total amount, and the balance of Al.
2. The heat treatment method for improving the comprehensive performance of the alloy plate as claimed in claim 1, wherein the heat treatment method comprises the following steps:
1.1 the plate solution quenching comprises the following steps: solid dissolving in an air furnace or a salt bath furnace at 515-535 ℃, keeping the temperature (6.0-8.0) minutes according to the thickness of the plate unit (mm), and then quenching with water at room temperature;
1.2 the spheroidizing aging treatment comprises the following steps: aging the alloy plate subjected to the solution quenching treatment in an air furnace with a circulating device at 220-280 ℃ for 10-20 h, and taking out for air cooling or air cooling to room temperature;
1.3 the repeated solution treatment comprises: after spheroidizing aging treatment, putting the alloy plate into an air furnace or a salt bath furnace at 520-540 ℃ for solution treatment, keeping the temperature for 3.0-4.0 minutes according to the thickness of the plate unit (mm), and then carrying out water quenching at room temperature;
1.4 the cold deformation process comprises: performing cold drawing on the quenched plate within 4 hours according to the cold deformation amount of 3.0-5.0%;
1.5 the aging treatment comprises the following steps: after cold deformation treatment, natural aging or artificial aging treatment is carried out;
1.5.1 the natural aging comprises: placing under room temperature strip for at least 120 h;
1.5.2 the artificial aging is a two-stage artificial aging treatment, comprising: and keeping the temperature for 16-24 h at the first stage at 120-135 ℃ and keeping the temperature for 8-14 h at the second stage at 143-155 ℃, and continuously heating along with the furnace in a two-stage aging chamber.
3. The heat treatment method for improving the comprehensive performance of the alloy plate as claimed in claim 1, wherein the heat treatment method comprises the following steps:
the heating temperature of the solution treatment is 520 ℃;
the heating temperature of the spheroidizing aging treatment is 220-280 ℃;
the heating temperature of the repeated solution treatment is 530 ℃.
4. The heat treatment method for improving the comprehensive performance of the alloy plate as claimed in claim 1, wherein the weight percentage of Cu in the alloy components is as follows: 3.8% or 4%; the weight percentage of Li is: 1.5% or 1.70%.
5. The heat treatment method for improving the comprehensive performance of the alloy plate as claimed in claim 1, wherein the alloy comprises the following components: 0.60% of Mg, 0.50% of Zn, 0.12% of Zr, 0.50% of Mn, 0.20% of Sc, 0.60% of Ag, any 1-3 of Er0.15%, 0.08% of Si, 0.08% of Fe, 0.08% of Ti, less than or equal to 0.05% of other impurities, less than or equal to 0.15% of the total amount, and the balance of Al.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810598455.6A CN110592504B (en) | 2018-06-12 | 2018-06-12 | Heat treatment method for improving comprehensive performance of alloy plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810598455.6A CN110592504B (en) | 2018-06-12 | 2018-06-12 | Heat treatment method for improving comprehensive performance of alloy plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110592504A true CN110592504A (en) | 2019-12-20 |
| CN110592504B CN110592504B (en) | 2021-07-23 |
Family
ID=68848667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810598455.6A Active CN110592504B (en) | 2018-06-12 | 2018-06-12 | Heat treatment method for improving comprehensive performance of alloy plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110592504B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111363961A (en) * | 2020-04-29 | 2020-07-03 | 贵州航天新力铸锻有限责任公司 | Er-containing high-Li-content light low-cost high-toughness aluminum lithium alloy |
| CN112410691A (en) * | 2020-11-10 | 2021-02-26 | 中国航发北京航空材料研究院 | Annealing process of aluminum-lithium alloy material |
| CN113981280A (en) * | 2021-11-01 | 2022-01-28 | 北京理工大学 | Low-density high-strength high-elasticity-modulus aluminum-lithium alloy and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998018976A1 (en) * | 1996-10-28 | 1998-05-07 | Mcdonnell Douglas Corporation | HEAT TREATED Al-Cu-Li-Sc ALLOYS |
| CN105951007A (en) * | 2016-06-22 | 2016-09-21 | 上海交通大学 | Heat treatment method for high-lithium-content cast aluminum-lithium alloy |
| CN106521270A (en) * | 2016-12-07 | 2017-03-22 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving corrosion resistance of aluminum-lithium alloy |
| CN106591650A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Method for improving stress corrosion resisting performance of aluminum lithium alloy |
| CN106591632A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving comprehensive performance of aluminum-lithium alloy |
| CN106702232A (en) * | 2016-12-07 | 2017-05-24 | 北京科技大学 | Discrete processing method for facilitating progenetic phase distribution of Al-Mg-Si-Cu alloy |
| CN107858614A (en) * | 2017-11-22 | 2018-03-30 | 重庆理工大学 | A kind of micro-meter scale T based on Al Cu Li alloys1The in-situ preparation method of phase |
-
2018
- 2018-06-12 CN CN201810598455.6A patent/CN110592504B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998018976A1 (en) * | 1996-10-28 | 1998-05-07 | Mcdonnell Douglas Corporation | HEAT TREATED Al-Cu-Li-Sc ALLOYS |
| CN105951007A (en) * | 2016-06-22 | 2016-09-21 | 上海交通大学 | Heat treatment method for high-lithium-content cast aluminum-lithium alloy |
| CN106521270A (en) * | 2016-12-07 | 2017-03-22 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving corrosion resistance of aluminum-lithium alloy |
| CN106591650A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Method for improving stress corrosion resisting performance of aluminum lithium alloy |
| CN106591632A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving comprehensive performance of aluminum-lithium alloy |
| CN106702232A (en) * | 2016-12-07 | 2017-05-24 | 北京科技大学 | Discrete processing method for facilitating progenetic phase distribution of Al-Mg-Si-Cu alloy |
| CN107858614A (en) * | 2017-11-22 | 2018-03-30 | 重庆理工大学 | A kind of micro-meter scale T based on Al Cu Li alloys1The in-situ preparation method of phase |
Non-Patent Citations (1)
| Title |
|---|
| 马云龙等: "2195铝锂合金重固溶-T8再时效的组织与力学性能", 《材料热处理学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111363961A (en) * | 2020-04-29 | 2020-07-03 | 贵州航天新力铸锻有限责任公司 | Er-containing high-Li-content light low-cost high-toughness aluminum lithium alloy |
| CN112410691A (en) * | 2020-11-10 | 2021-02-26 | 中国航发北京航空材料研究院 | Annealing process of aluminum-lithium alloy material |
| CN113981280A (en) * | 2021-11-01 | 2022-01-28 | 北京理工大学 | Low-density high-strength high-elasticity-modulus aluminum-lithium alloy and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110592504B (en) | 2021-07-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106591650B (en) | A method of improving aluminium lithium alloy anti-stress corrosion performance | |
| CN108531817B (en) | Nano/ultra-fine grain structure ultra-high strength plasticity austenitic stainless steel and preparation method thereof | |
| JP6458003B2 (en) | Aluminum alloy material suitable for manufacturing automobile body panel and method for producing the same | |
| CN108359920B (en) | A kind of short route prepares the deformation heat treatment method of the anti-corrosion Al-Mg-Zn aluminium alloy of high-strength height | |
| CN105543595B (en) | High intensity, high formability, inexpensive aluminum-copper-lithium alloys | |
| CN110592504B (en) | Heat treatment method for improving comprehensive performance of alloy plate | |
| CN108300918A (en) | One kind having high room temperature forming property calcic rare earth-magnesium alloy board and preparation method | |
| CN110306136B (en) | Processing method for high yield of high-alloying aluminum alloy sheet | |
| US20150184272A1 (en) | Low cost and high strength titanium alloy and heat treatment process | |
| CN109207811A (en) | A kind of preparation method and applications of aluminium alloy extrusions | |
| CN107488823B (en) | Method that is a kind of while improving intensity of aluminum alloy and elongation percentage | |
| CN110846599A (en) | Heat treatment method for improving corrosion performance of 800 MPa-grade aluminum alloy | |
| CN107964641B (en) | Heat treatment method for improving creep forming performance of aluminum-lithium alloy | |
| WO2020048539A1 (en) | Method for improving strength of aq80m magnesium alloy and prolonging strain fatigue life thereof | |
| CN110423966A (en) | A kind of preparation process improving aluminium lithium alloy product comprehensive performance | |
| Zhang et al. | Optimizing the mechanical properties of a Mg–Y–Nd–Zn–Zr alloy via interrupted compression with an intermediate annealing | |
| CN103589977A (en) | Method for improving the fatigue resistance performance of Al-Cu-Mg alloy | |
| CN110592508A (en) | Low-cost and high-performance titanium alloy short-process forging process | |
| CN109897999B (en) | Production process of high-strength high-toughness 2XXX aluminum alloy forge piece | |
| Jiang et al. | Formability and strengthening mechanism of AA6061 tubular components under solid granule medium internal high pressure forming | |
| CN104313521A (en) | Machining method capable of improving performance of 7075 aluminum alloy plates | |
| CN106939388B (en) | A kind of high strength and low cost high-ductility isotropism Mg-Zn-Y alloys and preparation method thereof | |
| CN109988947A (en) | Anti-corrosion, solderable alloy and preparation method thereof | |
| CN114438428B (en) | Preparation method of corrosion-resistant aluminum alloy | |
| CN114540646B (en) | Preparation and heat treatment method of high-strength and high-toughness 7-series aluminum alloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |