CN113751524A - Production and preparation process of aviation O-state coated 7-series aluminum alloy skin sheet - Google Patents
Production and preparation process of aviation O-state coated 7-series aluminum alloy skin sheet Download PDFInfo
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 46
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 22
- 238000002360 preparation method Methods 0.000 title claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 51
- 238000000034 method Methods 0.000 claims abstract description 42
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 41
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- 230000008569 process Effects 0.000 claims abstract description 38
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- 238000005253 cladding Methods 0.000 claims abstract description 29
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- 238000003466 welding Methods 0.000 claims abstract description 19
- 238000001816 cooling Methods 0.000 claims abstract description 16
- 238000005266 casting Methods 0.000 claims abstract description 15
- 239000002131 composite material Substances 0.000 claims abstract description 14
- 238000010438 heat treatment Methods 0.000 claims abstract description 11
- 238000005097 cold rolling Methods 0.000 claims abstract description 8
- 238000005096 rolling process Methods 0.000 claims description 56
- 239000011248 coating agent Substances 0.000 claims description 33
- 238000000576 coating method Methods 0.000 claims description 33
- ZWEHNKRNPOVVGH-UHFFFAOYSA-N 2-Butanone Chemical compound CCC(C)=O ZWEHNKRNPOVVGH-UHFFFAOYSA-N 0.000 claims description 20
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 20
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 6
- 238000000137 annealing Methods 0.000 description 6
- 239000001257 hydrogen Substances 0.000 description 6
- 229910052739 hydrogen Inorganic materials 0.000 description 6
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- 239000011247 coating layer Substances 0.000 description 4
- 229910052802 copper Inorganic materials 0.000 description 4
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- 238000005275 alloying Methods 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C37/00—Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape
- B21C37/02—Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape of sheets
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
- C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
- C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
- C21D8/0226—Hot rolling
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
- C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
- C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
- C21D8/0236—Cold rolling
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
- C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
- C21D8/0247—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the heat treatment
- C21D8/0273—Final recrystallisation annealing
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
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- 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
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
-
- 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
- C22F1/053—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 zinc as the next major constituent
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- Crystallography & Structural Chemistry (AREA)
- Metal Rolling (AREA)
Abstract
A production and preparation process of an aviation O-state coated 7-series aluminum alloy skin sheet comprises the following steps: the method comprises the following steps: the cladding material is attached to the ingot, the periphery of the cladding material is 20-30mm away from the edge of the ingot, the cladding material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy; step two: heating and hot rolling the clad material and the cast ingot composite aluminum material; step three: carrying out 3 times of cold rolling on a hot-rolled plate with the thickness of 7.0-8.0 to 3.25-4.75 mm; step four: and (3) preserving the heat of the cold-rolled plate at the temperature of 370-plus 380 ℃ for 2h, reducing the temperature to be below 150 ℃, reducing the temperature at a cooling rate of less than or equal to 15 ℃/h, and cooling to obtain the O-state coated aluminum sheet. According to the invention, through technical means of alloy component optimization, composite casting welding process, cold-hot rolling process matching and the like, the 7075 alloy O-state coated thin plate for civil aircraft skin is developed, wherein each performance index of the 7075 alloy O-state coated thin plate can fully meet the performance requirement of AMS4048 standard.
Description
Technical Field
The invention belongs to the field of aerospace aluminum alloy, and particularly relates to a production and preparation process of an aviation O-state coated 7-series aluminum alloy skin sheet.
Background
The skin sheet for the airplane is exposed in the environment for a long time, the requirements on the corrosion resistance and the strength of the material are high, the 7075 aluminum alloy belongs to an Al-Zn-Mg-Cu system and is a high-strength aluminum alloy, and the clad sheet gives higher corrosion resistance to the alloy and can sufficiently meet the design and use requirements of high safety and long service life of the airplane. Due to the lack of experience in the development of aviation clad sheets in China, domestic and civil aviation aircraft skin materials mainly come from foreign imports. The 7075 alloy O-state clad sheet has the difficulties of easy generation of cracks, low control precision of the thickness of the sheet, poor surface quality, performance not meeting standard requirements and the like in the process of cladding and rolling in the development process, so that the comprehensive performance of the subsequent application state cannot meet the technical design requirements. Leading to the dependence of skin materials on imports for large aircraft projects made in China. The Nanshan aluminum industry develops the aluminum alloy sheet material for civil aircrafts by means of the construction project of the related production line of the national new material application demonstration platform (aviation material), overcomes the blockade of foreign technologies, and lays a foundation for the localization of the aviation aluminum alloy skin sheet for the domestic large aircrafts.
The 7075 alloy belongs to high-strength heat-treatable alloy, elements playing a main strengthening role are Zn and Mg, and Cu also has a certain strengthening effect, but the main role is to improve the corrosion resistance of the material. The 7075 alloy has good mechanical properties, easy processing, and good corrosion resistance and oxidation resistance. The representative application is the fields of aerospace, die processing, mechanical equipment, tool fixtures and the like. In the aviation field, the composite material not only can be used as an aviation aircraft structural member in a section form, but also can be used on aircraft wings as a skin plate.
The 7075 alloy O-state clad sheet is used as a processable state for a large civil aircraft skin sheet, but in the prior art, the material has uneven performance, is easy to have cladding cracks, has uneven thickness of a cladding layer, is difficult to control the plate shape and the like, and cannot well meet the AMS4048 standard requirements, so that the system needs to be innovated from the technologies of alloy components, cladding process, rolling process optimization and the like. In the prior art, the production meets the AMS4048 standard and the requirement of a domestic large airplane project as the premise of technical research and development, and the process optimization and the performance improvement are carried out according to the use environment and the performance requirement of customers on the aviation skin thin plate. In the actual use process of the wing skin 7 series aluminum alloy, the impact of airflow at high speed is borne, and meanwhile, high corrosion resistance is required. However, at present, a mature production method does not exist in China, in the actual production process, due to the problems of uneven plate thickness, poor coating aluminum thickness uniformity and the like, the performance difference of the whole plate at different positions is large, cracking, deformation and the like can also occur in the use process, and the influence on the service life of the wing skin is large.
Disclosure of Invention
The invention provides a production and preparation process of an aviation O-state coated 7-series aluminum alloy skin sheet, which is used for overcoming the defects in the prior art.
The invention is realized by the following technical scheme:
a production and preparation process of an aviation O-state coated 7-series aluminum alloy skin sheet comprises the following steps:
the method comprises the following steps: the cladding material is attached to the ingot, the periphery of the cladding material is 20-30mm away from the edge of the ingot, the cladding material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy;
step two: and (3) heating the composite aluminum material of the coating material and the ingot casting to 450-470 ℃, and carrying out hot rolling after heat preservation for 2-5 h. Setting hot rolling for 20-25 times, and performing the first two times of welding rolling, wherein the rolling reduction is controlled to be 1-3mm, and the rolling speed is 0.35-0.5 m/s. The subsequent passes adopt a conventional rolling mode, emulsion is added at the beginning of the sixth rolling, the opening degree of an upper emulsifier spray nozzle is 20 percent, the opening degree of a lower emulsifier spray nozzle is 50 percent, the opening degree of an upper emulsifier spray nozzle is 40 percent, the opening degree of a lower emulsifier spray nozzle is 80 percent, the reduction amount of each pass is controlled to be less than or equal to 30mm, the rolling speed is controlled to be less than or equal to 2.0m/s, a roller brush is used for cleaning the roller surface in the rolling gap, the finish rolling temperature is controlled to be 330 ℃, and the thickness of a hot rolled finished product is 7.0-8.0mm from the sixth rolling to the eighth rolling;
step three: carrying out 3 times of cold rolling on a hot-rolled plate with the thickness of 7.0-8.0 to 3.25-4.75 mm;
step four: and (3) preserving the heat of the cold-rolled plate at the temperature of 370-plus 380 ℃ for 2h, reducing the temperature to be below 150 ℃, reducing the temperature at a cooling rate of less than or equal to 15 ℃/h, and cooling to obtain the O-state coated aluminum sheet.
The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet comprises the following steps: the content of i is less than 0.08 percent, the content of Fe is less than 0.15 percent, the content of Zn is 5.6 to 5.9 percent, the content of Cu is 1.3 to 1.6 percent, the content of Mg is 2.4 to 2.7 percent, the content of Mn is less than 0.1 percent, the content of Cr is 0.18 to 0.21 percent, the content of Ti is less than 0.1 percent, the content of other impurity elements is less than 0.05 percent, the sum of the impurity elements is less than 0.15 percent, and the balance is aluminum.
The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet comprises the following steps: placing raw materials in a smelting furnace, adding a remelting aluminum ingot and waste materials of the same alloy, smelting at 740 ℃, adding a covering agent after melting, starting electromagnetic stirring after 60-70% of the aluminum alloy raw materials are melted, adjusting components after all the aluminum alloy raw materials are melted, adding an intermediate alloy or an additive to adjust the components, then skimming, sampling and detecting chemical components, transferring the melt to a holding furnace after the components are proper, then placing the ingot into a homogenizing furnace for homogenization heat treatment, adopting a two-stage homogenization process of 465 +/-3 ℃/8-10h +475 +/-3 ℃/25-30h, taking out of the furnace and pushing into a cooling chamber for rapid cooling.
According to the production and preparation process of the aviation O-state clad 7-series aluminum alloy skin sheet, in the first step, the clad material is a low-alloy 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad sheet with the finished thickness of 3.25mm-4.75mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad sheet used for the aluminum clad sheet is 13-15mm, the width of the clad sheet is the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad sheet is the core ingot length- (200 +/-10 mm) × 2.
According to the production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet, in the step I, the coating material is brushed on one side before use, the brushing quality needs to be ensured, the brushing layer is uniform and has no omission, and the brushing surface is strictly forbidden to have foreign matters such as dust, oil stains, aluminum scraps and the like.
According to the production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet, the ingot surface in the step one is wiped by a towel dipped with a butanone or acetone cleaning agent, the ingot surface is wiped by a clean dry towel, residual butanone or acetone on the surface is removed by air blowing, the surface is wiped by white paper after wiping is ensured not to be blackened, and interlayer slag inclusion is avoided.
The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet is described.
The invention has the advantages that:
1. according to the invention, through technical means of alloy component optimization, composite casting welding process, cold-hot rolling process matching and the like, the 7075 alloy O-state coated thin plate for civil aircraft skin is developed, wherein each performance index of the 7075 alloy O-state coated thin plate can fully meet the performance requirement of AMS4048 standard.
2. Ingot casting soaking process: a large number of soaking processes are carried out on the large-size high-quality ingot casting, a set of soaking process parameters suitable for the ingot casting are formulated, and the high-quality aviation-grade large-size ingot casting with low content of residual second phase and no obvious loose defect is obtained.
3. Thickness of the composite sheet: the invention develops the composite O-state thin plate with the thickness ranging from 3.25mm to 4.75mm, and the coated O-state thin plate with the thickness can be used as a skin outer plate of a large airplane for processing.
4. The rolling process comprises the following steps: the purpose of starting emulsion lubrication in the hot rolling pass is to give consideration to both rolling stability and anodic oxidation surface quality. If lubrication is started in the first 3 or 4 passes, the temperature difference between the upper surface and the lower surface of the intermediate plate is too large due to higher hot rolling temperature, so that warping and rolling waste is caused; in the verification, the problem of warping can be avoided by slowly starting auxiliary emulsion lubrication in the 6 th pass, the 9 th pass is sprayed up and down to be large, the produced plate not only ensures the warping phenomenon between the cladding plate and the base plate, but also the quality of the surface of the anodic oxidation reaches more than the B grade due to the subsequent sufficient lubrication.
According to the invention, through the research of a large-size ingot casting homogenization process, the optimal homogenization process is determined, so that the content of the homogenized crystalline phase is lower than 0.9%; the pass setting, the lubricant pass use and the cold rolling deformation control in the hot rolling process realize the design target that the coating reaches more than 2 percent aiming at the 3.25mm-4.75mm sheet, and successfully ensure the problems of uneven thickness and poor surface quality of the coating layer; the mass of the surface after anodic oxidation is more than grade B; the problem of unstable process in the production process is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a technical protocol of the present invention;
FIG. 2 is a diagram of the cladding design of the present invention;
FIG. 3 is a surface quality chart of a product of the present invention;
FIG. 4 is a graph showing the results of measuring the coating thickness in example 1 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
1. The invention adopts a semi-continuous casting mode to produce the flat ingot with the ingot size (400 + 620mm (thickness) × 1200 + 2200mm (width) × 2000 + 8000mm (length)) and controls the alloy components to be within the ranges of Si content being lower than 0.08%, Fe content being lower than 0.15%, Zn content being 5.6% -5.9%, Cu content being 1.3% -1.6%, Mg content being 2.4% -2.7%, Mn content being lower than 0.1%, Cr content being 0.18% -0.21%, Ti content being lower than 0.1%, other impurity elements, the single element is not more than 0.05%, and the total is not more than 0.15%.
2. The preparation method of the slab ingot alloy comprises the following steps: preparing raw materials according to the components and mass percent of the aluminum alloy sheet. Putting the raw materials into a smelting furnace, adding a remelting aluminum ingot and waste materials of the same alloy, smelting at 740 ℃, adding a covering agent after the melting is started, starting electromagnetic stirring after 60-70% of the aluminum alloy raw materials are melted, adjusting components after the aluminum alloy raw materials are completely melted, adding an intermediate alloy or an additive to adjust the components, then slagging off, sampling and detecting chemical components, and transferring the melt to a holding furnace after the components are proper. Refining by adopting mixed gas at the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, and casting into an aluminum alloy ingot through on-line (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0kg/t) and CCF two-stage filtration). The process control hydrogen content is less than 0.12mL/100g.Al, the Na content is within 2ppm, and the Ca content is within 3 ppm. The removal rate of the slag with the size of more than 20 mu m is more than 95 percent. Ensuring that the content of hydrogen and slag in the melt meets the requirement of aviation aluminum alloy.
3. And (3) homogenization process: placing the cast ingot into a homogenizing furnace for homogenizing heat treatment, adopting a two-stage homogenizing process of 465 +/-3 ℃/8-10h +475 +/-3 ℃/25-30h, discharging, and pushing into a cooling type for rapid cooling. After the casting of the ingot is finished, obtaining a high-quality soaking ingot with the volume fraction of the residual second phase less than 0.9% by optimizing a homogenization process.
4. Coating design: the clad aluminum plate is a low-alloying 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad sheet with the finished thickness of 3.25mm-4.75mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad sheet used for the aluminum clad sheet is 13-15mm, the width of the clad sheet is the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad sheet is the core ingot length- (200 +/-10 mm) × 2.
5. Preparing before composite welding: the coating material is brushed on one side before use, the brushing quality needs to be ensured, the brushing layer is uniform and has no omission, and the brushing surface is strictly forbidden to have foreign matters such as dust, oil stain, aluminum scraps and the like, so that the surface oxide layer is removed. The surface of the cast ingot is wiped by a towel dipped with a butanone or acetone cleaning agent, the surface of the cast ingot is wiped by a clean dry towel, and the residual butanone or acetone on the surface is removed by air blowing, so that the surface is wiped by white paper after wiping and is prevented from blackening, and interlayer slag inclusion is avoided, thereby avoiding the risk of bag penetration of the cladding plate in the subsequent use process.
6. And (3) welding process: after the coating material is attached to the cast ingot, the periphery of the coating material is 20-30mm away from the edge, the coating material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy, so that the fixing strength of the coating material is ensured, and the coating material has high ductility.
7. The hot rolling process comprises the following steps: and (4) placing the composite ingot into a preheating furnace, heating to the temperature of 450-470 ℃, preserving heat for 2-5h, and then carrying out hot rolling. Setting hot rolling for 20-25 times, and performing the first two times of welding rolling, wherein the rolling reduction is controlled to be 1-3mm, and the rolling speed is 0.35-0.5 m/s. The latter pass adopts conventional rolling mode, and the 3 rd pass opens the emulsion, and the spraying amount is 20% and 50% respectively, and the spraying amount of the emulsion from 9 th to 9 th is 40% and 80% respectively, and the last pass of rolling is kept. The rolling reduction of each pass is controlled to be less than or equal to 30mm, the rolling speed is controlled to be less than or equal to 2.0m/s, the roller surface is cleaned by using a brush roller in the rolling gap, the final rolling temperature is controlled to be 300-330 ℃, and the thickness of the hot rolled finished product is 7.0-8.0 mm.
8. The cold rolling process comprises the following steps: and (3) carrying out 3 times of cold rolling on the hot-rolled 7.0-8.0-thickness plate to 3.25-4.75 mm aiming at the 3.25-4.75 mm-thick thin plate.
10. Annealing process: by researching annealing processes at different temperatures, the temperature is maintained at 380 ℃ for 2 hours at 370 ℃ and the temperature is reduced to less than or equal to 15 ℃/h, and the product is taken out of the furnace when the temperature is reduced to below 150 ℃. A structure with higher elongation and a completely recrystallized state is obtained.
The performance of the annealed O-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 193MPa, and the standard requirement is less than or equal to 262 MPa; the yield strength is 100 MPa; the standard requirement is less than or equal to 138MPa, the elongation is 23.0 percent and is more than or equal to 10 percent higher than the standard requirement; the uniformity fluctuation of the coating layer is about 0.5 mu m, the coating rate is 2.6-2.8%, the standard that the coating rate is more than or equal to 2% is met, and the surface quality after anodic oxidation is B-level.
Example 2
1. The invention adopts a semi-continuous casting mode to produce the flat ingot with the ingot size (400 + 620mm (thickness) × 1200 + 2200mm (width) × 2000 + 8000mm (length)) and controls the alloy components to be within the ranges of Si content being lower than 0.08%, Fe content being lower than 0.15%, Zn content being 5.6% -5.9%, Cu content being 1.3% -1.6%, Mg content being 2.4% -2.7%, Mn content being lower than 0.1%, Cr content being 0.18% -0.21%, Ti content being lower than 0.1%, other impurity elements, the single element is not more than 0.05%, and the total is not more than 0.15%.
2. The preparation method of the slab ingot alloy comprises the following steps: preparing raw materials according to the components and mass percent of the aluminum alloy sheet. Putting the raw materials into a smelting furnace, adding a remelting aluminum ingot and waste materials of the same alloy, smelting at 740 ℃, adding a covering agent after the melting is started, starting electromagnetic stirring after 60-70% of the aluminum alloy raw materials are melted, adjusting components after the aluminum alloy raw materials are completely melted, adding an intermediate alloy or an additive to adjust the components, then slagging off, sampling and detecting chemical components, and transferring the melt to a holding furnace after the components are proper. Refining by adopting mixed gas at the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, and casting into an aluminum alloy ingot through on-line (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0kg/t) and CCF two-stage filtration). The process control hydrogen content is less than 0.12mL/100g.Al, the Na content is within 2ppm, and the Ca content is within 3 ppm. The removal rate of the slag with the size of more than 20 mu m is more than 95 percent. Ensuring that the content of hydrogen and slag in the melt meets the requirement of aviation aluminum alloy.
3. And (3) homogenization process: putting the cast ingot into a homogenizing furnace for homogenizing heat treatment, adopting a two-stage homogenizing process of 460 plus or minus 3 ℃/8 to 10h plus or minus 3 ℃/20 to 25h, discharging and pushing in a cooling type rapid cooling. After the casting of the ingot is finished, a soaking ingot with the volume fraction of the residual second phase of 1.5 percent is obtained through an optimized homogenization process.
4. Coating design: the clad aluminum plate is a low-alloying 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad sheet with the finished thickness of 3.25mm-4.75mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad sheet used for the aluminum clad sheet is 13-15mm, the width of the clad sheet is the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad sheet is the core ingot length- (200 +/-10 mm) × 2.
5. Preparing before composite welding: the coating material is brushed on one side before use, the brushing quality needs to be ensured, the brushing layer is uniform and has no omission, and the brushing surface is strictly forbidden to have foreign matters such as dust, oil stain, aluminum scraps and the like, so that the surface oxide layer is removed. The surface of the cast ingot is wiped by a towel dipped with a butanone or acetone cleaning agent, the surface of the cast ingot is wiped by a clean dry towel, and the residual butanone or acetone on the surface is removed by air blowing, so that the surface is wiped by white paper after wiping and is prevented from blackening, and interlayer slag inclusion is avoided, thereby avoiding the risk of 'bag penetration' of the cladding plate in the subsequent use process.
6. And (3) welding process: after the coating material is attached to the cast ingot, the periphery of the coating material is 20-30mm away from the edge, the coating material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy, so that the fixing strength of the coating material is ensured, and the coating material has high ductility.
7. The hot rolling process comprises the following steps: and (4) placing the composite ingot into a preheating furnace, heating to the temperature of 450-470 ℃, preserving heat for 2-5h, and then carrying out hot rolling. Setting hot rolling for 20-25 times, and performing the first two times of welding rolling, wherein the rolling reduction is controlled to be 1-3mm, and the rolling speed is 0.35-0.5 m/s. The latter pass adopts conventional rolling mode, the emulsion is opened in the 6 th pass, the spraying amount is 20% and 50% respectively, and the spraying amount of the emulsion from the 8 th pass to the last pass is 40% and 80% respectively, and the last pass of rolling is kept. The rolling reduction of each pass is controlled to be less than or equal to 30mm, the rolling speed is controlled to be less than or equal to 2.0m/s, the roller surface is cleaned by using a brush roller in the rolling gap, the final rolling temperature is controlled to be 300-330 ℃, and the thickness of the hot rolled finished product is 7.0-8.0 mm.
8. The cold rolling process comprises the following steps: and (3) carrying out 3 times of cold rolling on the hot-rolled 7.0-8.0-thickness plate to 3.25-4.75 mm aiming at the 3.25-4.75 mm-thick thin plate.
10. Annealing process: by researching annealing processes at different temperatures, the temperature is maintained at 380 ℃ for 2 hours at 370 ℃ and the temperature is reduced to less than or equal to 15 ℃/h, and the product is taken out of the furnace when the temperature is reduced to below 150 ℃. A structure with higher elongation and a completely recrystallized state is obtained.
The performance of the annealed O-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 185MPa, and the standard requirement is less than or equal to 262 MPa; yield strength 96 MPa; the standard requirement is less than or equal to 138 MPa. The elongation is 20.0 percent and is more than or equal to 10 percent higher than the standard requirement; the uniformity fluctuation of the coating layer is about 0.7 mu m, the coating rate is 2.5-2.7%, the standard that the coating rate is more than or equal to 2% is met, and the surface quality after anodic oxidation is B-level.
Example 3
1. The invention adopts a semi-continuous casting mode to produce the flat ingot with the ingot size (400 + 620mm (thickness) × 1200 + 2200mm (width) × 2000 + 8000mm (length)) and controls the alloy components to be within the ranges of Si content being lower than 0.08%, Fe content being lower than 0.15%, Zn content being 5.6% -5.9%, Cu content being 1.3% -1.6%, Mg content being 2.4% -2.7%, Mn content being lower than 0.1%, Cr content being 0.18% -0.21%, Ti content being lower than 0.1%, other impurity elements, the single element is not more than 0.05%, and the total is not more than 0.15%.
2. The preparation method of the slab ingot alloy comprises the following steps: preparing raw materials according to the components and mass percent of the aluminum alloy sheet. Putting the raw materials into a smelting furnace, adding a remelting aluminum ingot and waste materials of the same alloy, smelting at 740 ℃, adding a covering agent after the melting is started, starting electromagnetic stirring after 60-70% of the aluminum alloy raw materials are melted, adjusting components after the aluminum alloy raw materials are completely melted, adding an intermediate alloy or an additive to adjust the components, then slagging off, sampling and detecting chemical components, and transferring the melt to a holding furnace after the components are proper. Refining by adopting mixed gas at the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, and casting into an aluminum alloy ingot through on-line (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0kg/t) and CCF two-stage filtration). The process control hydrogen content is less than 0.12mL/100g.Al, the Na content is within 2ppm, and the Ca content is within 3 ppm. The removal rate of the slag with the size of more than 20 mu m is more than 95 percent. Ensuring that the content of hydrogen and slag in the melt meets the requirement of aviation aluminum alloy.
3. And (3) homogenization process: placing the cast ingot into a homogenizing furnace for homogenizing heat treatment, adopting a two-stage homogenizing process of 465 +/-3 ℃/8-10h +475 +/-3 ℃/25-30h, discharging, and pushing into a cooling type for rapid cooling. After the casting of the ingot is finished, obtaining a high-quality soaking ingot with the volume fraction of the residual second phase less than 0.9% by optimizing a homogenization process.
4. Coating design: the clad aluminum plate is a low-alloying 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad sheet with the finished thickness of 3.25mm-4.75mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad sheet used for the aluminum clad sheet is 13-15mm, the width of the clad sheet is the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad sheet is the core ingot length- (200 +/-10 mm) × 2.
5. Preparing before composite welding: the coating material is brushed on one side before use, the brushing quality needs to be ensured, the brushing layer is uniform and has no omission, and the brushing surface is strictly forbidden to have foreign matters such as dust, oil stain, aluminum scraps and the like, so that the surface oxide layer is removed. The surface of the cast ingot is wiped by a towel dipped with a butanone or acetone cleaning agent, the surface of the cast ingot is wiped by a clean dry towel, and the residual butanone or acetone on the surface is removed by air blowing, so that the surface is wiped by white paper after wiping and is prevented from blackening, and interlayer slag inclusion is avoided, thereby avoiding the risk of bag penetration of the cladding plate in the subsequent use process.
6. And (3) welding process: after the coating material is attached to the cast ingot, the periphery of the coating material is 20-30mm away from the edge, the coating material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy, so that the fixing strength of the coating material is ensured, and the coating material has high ductility.
7. The hot rolling process comprises the following steps: and (4) placing the composite ingot into a preheating furnace, heating to the temperature of 450-470 ℃, preserving heat for 2-5h, and then carrying out hot rolling. Setting hot rolling for 25-30 times, and performing the first two times of welding rolling, wherein the rolling reduction is controlled to be 1-3mm, and the rolling speed is 0.35-0.5 m/s. The latter pass adopts conventional rolling mode, and the emulsion is opened in the 6 th pass, the spraying amount is 20% and 50% respectively, and the spraying amount of the emulsion from the 9 th pass to the last pass is kept, and the spraying amount of the emulsion is 40% and 80% respectively. The rolling reduction of each pass is controlled to be less than or equal to 30mm, the rolling speed is controlled to be less than or equal to 2.0m/s, the roller surface is cleaned by a brush roller in the rolling gap, the final rolling temperature is controlled to be 300 ℃ and 330 ℃, and the thickness of the finished product is 3.25mm-4.75mm by direct hot rolling.
10. Annealing process: by researching annealing processes at different temperatures, the temperature is maintained at 380 ℃ for 2 hours at 370 ℃ and the temperature is reduced to less than or equal to 15 ℃/h, and the product is taken out of the furnace when the temperature is reduced to below 150 ℃. A structure with higher elongation and a completely recrystallized state is obtained.
The performance of the annealed O-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 201MPa, and the standard requirement is less than or equal to 262 MPa; the yield strength is 108 MPa; the standard requirement is less than or equal to 138MPa, the elongation is 19.2 percent and is more than or equal to 10 percent higher than the standard requirement; the uniformity fluctuation of the coating layer is about 0.8 mu m, the coating rate is 2.5-2.7%, the standard that the coating rate is more than or equal to 2% is met, and the surface quality after anodic oxidation is B-level.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (5)
1. A production and preparation process of an aviation O-state coated 7-series aluminum alloy skin sheet is characterized by comprising the following steps of: the method comprises the following steps:
the method comprises the following steps: the cladding material is attached to the ingot, the periphery of the cladding material is 20-30mm away from the edge of the ingot, the cladding material is fixedly welded in a bolt fastening mode every 1000-1500mm in the length direction, and the welding material is 7075-F aluminum alloy;
step two: and (3) heating the composite aluminum material of the coating material and the ingot casting to 450-470 ℃, and carrying out hot rolling after heat preservation for 2-5 h. Setting hot rolling for 20-25 times, and performing the first two times of welding rolling, wherein the rolling reduction is controlled to be 1-3mm, and the rolling speed is 0.35-0.5 m/s. The subsequent passes adopt a conventional rolling mode, emulsion is added at the beginning of the sixth rolling, the opening degree of an upper emulsifier spray nozzle is 20 percent, the opening degree of a lower emulsifier spray nozzle is 50 percent, the opening degree of an upper emulsifier spray nozzle is 40 percent, the opening degree of a lower emulsifier spray nozzle is 80 percent, the reduction amount of each pass is controlled to be less than or equal to 30mm, the rolling speed is controlled to be less than or equal to 2.0m/s, a roller brush is used for cleaning the roller surface in the rolling gap, the finish rolling temperature is controlled to be 330 ℃, and the thickness of a hot rolled finished product is 7.0-8.0mm from the sixth rolling to the eighth rolling;
step three: carrying out 3 times of cold rolling on a hot-rolled plate with the thickness of 7.0-8.0 to 3.25-4.75 mm;
step four: and (3) preserving the heat of the cold-rolled plate at the temperature of 370-plus 380 ℃ for 2h, reducing the temperature to be below 150 ℃, reducing the temperature at a cooling rate of less than or equal to 15 ℃/h, and cooling to obtain the O-state coated aluminum sheet.
2. The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet according to claim 1, characterized by comprising the following steps: the alloy composition of the ingot cast in the first step is as follows: the content of i is less than 0.08 percent, the content of Fe is less than 0.15 percent, the content of Zn is 5.6 to 5.9 percent, the content of Cu is 1.3 to 1.6 percent, the content of Mg is 2.4 to 2.7 percent, the content of Mn is less than 0.1 percent, the content of Cr is 0.18 to 0.21 percent, the content of Ti is less than 0.1 percent, the content of other impurity elements is less than 0.05 percent, the sum of the impurity elements is less than 0.15 percent, and the balance is aluminum.
3. The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet according to claim 1, characterized by comprising the following steps: the preparation method of the cast ingot in the first step comprises the following steps: placing raw materials in a smelting furnace, adding a remelting aluminum ingot and waste materials of the same alloy, smelting at 740 ℃, adding a covering agent after melting, starting electromagnetic stirring after 60-70% of the aluminum alloy raw materials are melted, adjusting components after all the aluminum alloy raw materials are melted, adding an intermediate alloy or an additive to adjust the components, then skimming, sampling and detecting chemical components, transferring the melt to a holding furnace after the components are proper, then placing the ingot into a homogenizing furnace for homogenization heat treatment, adopting a two-stage homogenization process of 465 +/-3 ℃/8-10h +475 +/-3 ℃/25-30h, taking out of the furnace and pushing into a cooling chamber for rapid cooling.
4. The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet according to claim 1, characterized by comprising the following steps: in the first step, the clad material is a low-alloy 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad sheet with the finished thickness of 3.25mm-4.75mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad sheet used for the aluminum clad sheet is 13-15mm, the width of the clad sheet is the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad sheet is the core ingot length- (200 +/-10 mm) × 2.
5. The production and preparation process of the aviation O-state coated 7-series aluminum alloy skin sheet according to claim 1, characterized by comprising the following steps:
in the first step, the cladding material is brushed on one side before use, the brushing quality needs to be ensured, the brushing layer is uniform and has no omission, and the brushing surface is strictly forbidden to have foreign matters such as dust, oil stains, aluminum scraps and the like;
and (3) wiping the surface of the cast ingot in the step one by using a towel dipped with a butanone or acetone cleaning agent, wiping the surface of the cast ingot by using a clean dry towel, and blowing air to remove residual butanone or acetone on the surface, so that the surface is wiped by using white paper after wiping, and the formation of interlayer slag is avoided.
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