CN113996655A - Preparation method of 7075 aluminum alloy clad skin sheet for T6-state aviation - Google Patents
Preparation method of 7075 aluminum alloy clad skin sheet for T6-state aviation Download PDFInfo
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- CN113996655A CN113996655A CN202110954331.9A CN202110954331A CN113996655A CN 113996655 A CN113996655 A CN 113996655A CN 202110954331 A CN202110954331 A CN 202110954331A CN 113996655 A CN113996655 A CN 113996655A
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- 229910001008 7075 aluminium alloy Inorganic materials 0.000 title claims abstract description 17
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- 238000000137 annealing Methods 0.000 claims abstract description 13
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
- B21B1/38—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling sheets of limited length, e.g. folded sheets, superimposed sheets, pack rolling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B37/00—Control devices or methods specially adapted for metal-rolling mills or the work produced thereby
- B21B37/56—Elongation control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B37/00—Control devices or methods specially adapted for metal-rolling mills or the work produced thereby
- B21B37/74—Temperature control, e.g. by cooling or heating the rolls or the product
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B45/00—Devices for surface or other treatment of work, specially combined with or arranged in, or specially adapted for use in connection with, metal-rolling mills
- B21B45/02—Devices for surface or other treatment of work, specially combined with or arranged in, or specially adapted for use in connection with, metal-rolling mills for lubricating, cooling, or cleaning
- B21B45/0239—Lubricating
- B21B45/0245—Lubricating devices
- B21B45/0248—Lubricating devices using liquid lubricants, e.g. for sections, for tubes
- B21B45/0251—Lubricating devices using liquid lubricants, e.g. for sections, for tubes for strips, sheets, or plates
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B47/00—Auxiliary arrangements, devices or methods in connection with rolling of multi-layer sheets of metal
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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
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
- B21B1/38—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling sheets of limited length, e.g. folded sheets, superimposed sheets, pack rolling
- B21B2001/383—Cladded or coated products
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
- B21B1/38—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling sheets of limited length, e.g. folded sheets, superimposed sheets, pack rolling
- B21B2001/386—Plates
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
- B21B2003/001—Aluminium or its alloys
Abstract
A preparation method of a 7075 aluminum alloy clad skin sheet for T6-state aviation comprises the following steps: the method comprises the following steps: after the coating material is attached to the ingot, the periphery of the coating material is 20-30mm away from the edge of the ingot, and the 7075 state aluminum alloy is used as a welding material for fixed welding every 1000-1500mm in the length direction; step two: heating and hot rolling the cladding material obtained in the step one and the clad cast ingot welded by the cast ingot; step three: carrying out 2-3 cold rolling on a hot-rolled plate with the thickness of 7.0-7.5mm to 1.60-3.25 mm; step four: preserving the heat of the cold-rolled plate at the temperature of 370-380 ℃ for 2h, and cooling; step five: after the annealing is finished, the temperature is kept for 30-60min at the temperature of 465-470 ℃, the temperature is reduced by quenching, the steel plate is sent into an aging furnace, the aging temperature is 120-125 ℃, the aging time is 24-36h, and the temperature is reduced to the room temperature, so that the T6-state plate is obtained. According to the invention, by improving the rolling process, the thickness of the composite skin sheet and the heat treatment process, the performance of the prepared large-scale 7075 aluminum alloy T6-state coated sheet meets the AMS4048 standard, the coating layer is uniform in thickness, the plate type accuracy is high, and the comprehensive performance reaches the international advanced level.
Description
Technical Field
The invention belongs to the field of aviation profiles, and particularly relates to a preparation method of a 7075 aluminum alloy coated skin thin plate for T6-state aviation.
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 T6-state clad sheet has the difficulties of low plate thickness control precision, poor surface quality, non-compliance of mechanical properties with standard requirements and the like in the process of cladding and rolling in the development process, so that the comprehensive properties can not meet the technical design requirements, and the skin materials of the domestic large aircraft project are always imported. 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.
According to the invention, through technical means of alloy component optimization, composite casting welding process, hot-cold rolling process matching and the like, the 7075 alloy T6 state coated skin thin plate for civil aircraft skin is developed, wherein each performance index of the 7075 alloy T6 state coated skin thin plate can fully meet the performance requirement of AMS4049 standard.
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 T6 state clad sheet is used as a final state for supplying to a large civil aircraft skin sheet, however, 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 is required to innovate from the technologies of alloy components, a cladding process, a rolling process, a heat treatment process and the like.
In the prior art, process optimization and performance improvement are carried out according to the use environment and performance requirements of customers on the aviation skin thin plate on the premise that production meets AMS4049 standards and requirements of domestic large airplane projects as technology research and development. 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, no mature production method exists in China, and in the actual production process, because the thickness of the plate is thinner and is only 1.6-3.25mm, particularly in the process of well controlling the hot finish rolling, good deformation conditions are provided for the subsequent cold rolling process, otherwise, the conditions of plate performance difference and uneven thickness control are easy to occur. It also results in cracking, deformation, etc. during use, which has a significant impact on the useful life of the wing skin.
Disclosure of Invention
The invention provides a preparation method of a 7075 aluminum alloy clad skin sheet for T6-state aviation, which is used for solving the defects in the prior art.
The invention is realized by the following technical scheme:
a preparation method of a 7075 aluminum alloy clad skin sheet for T6-state aviation comprises the following steps:
the method comprises the following steps: after the coating material is attached to the ingot, the periphery of the coating material is 20-30mm away from the edge of the ingot, and the fixed welding is carried out by taking 7075-F state aluminum alloy as a welding material every 1000-1500mm in the length direction;
step two: heating the cladding ingot welded with the cladding material obtained in the step one and the ingot to 450-grade 470 ℃, preserving heat for 2-5h, carrying out hot rolling, setting 20-23 hot rolling passes in the hot rolling, carrying out the first two welding rolling passes, controlling the reduction amount to be 2-3mm, controlling the rolling speed to be 0.35-0.5m/s, adopting a conventional rolling mode in the latter pass, adding emulsion at the beginning of the sixth rolling pass, controlling the opening degree of an upper emulsifier spray nozzle to be 10% in the sixth rolling pass to the eighth rolling pass, controlling the opening degree of a lower emulsifier spray nozzle to be 40%, controlling the opening degree of an upper emulsifier spray nozzle to be 40% in the ninth rolling pass to the last rolling pass, controlling the opening degree of a lower emulsifier spray nozzle to be 80%, and keeping the last rolling pass; controlling the rolling reduction of each pass at the beginning of the third rolling to be less than or equal to 30mm, controlling the rolling speed to be less than or equal to 2.0m/s, cleaning the roll surface of a rolling gap by using a brush roll, controlling the thickness of hot rough rolling to be 35-45mm, performing 5-8 passes of hot finish rolling, controlling the finish rolling temperature to be 300-330 ℃ and controlling the thickness of a hot rolled finished product to be 3.5-7.0 mm;
step three: carrying out 2-3 cold rolling on a hot-rolled plate with the thickness of 7.0-7.5mm to 1.60-3.25 mm;
step four: preserving the heat of the cold-rolled plate for 2h at the temperature of 370-380 ℃, cooling to below 150 ℃ and discharging;
step five: after the annealing is finished, the temperature is kept for 30-60min at the temperature of 465-470 ℃, the temperature is reduced by quenching, the steel plate is sent into an aging furnace, the aging temperature is 120-125 ℃, the aging time is 24-36h, and the temperature is reduced to the room temperature, so that the T6-state plate is obtained.
The preparation method of the 7075 aluminum alloy clad skin sheet for T6-state aviation comprises the following steps: the steel is characterized by comprising the following components, by weight, less than 0.08% of Si, less than 0.12% of Fe, 5.6% -5.9% of Zn, 1.3% -1.6% of Cu, 2.4% -2.7% of Mg, less than 0.1% of Mn, 0.18% -0.21% of Cr, less than 0.1% of Ti, no more than 0.05% of other impurity elements, no more than 0.15% of the total, and the balance of aluminum.
The preparation method of the 7075 aluminum alloy clad skin sheet for T6-state aviation 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 cast ingot in 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, pushing the cast ingot into a cooling chamber for rapid cooling.
According to the preparation method of the 7075 aluminum alloy clad skin sheet for T6-state aviation, the clad material is a low-alloy 7-series aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the clad aluminum sheet with the finished thickness of 1.6-3.25mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad plate used for the clad aluminum sheet is 13-15mm, the width of the clad plate is equal to the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad plate is equal to the length of the core ingot- (200 +/-10 mm) × 2. The preparation method of the T6-state 7075 aluminum alloy clad skin sheet for aviation is described above.
The invention has the advantages that:
1. according to the invention, by improving the rolling process, the thickness of the composite skin sheet and the heat treatment process, the performance of the prepared large-scale 7075 aluminum alloy T6-state coated sheet meets the AMS4048 standard, the thickness of the coating is uniform, the plate type accuracy is high, and the comprehensive performance reaches the international advanced level; meanwhile, 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 percent; the pass setting in the hot rolling process, the precise control of hot rough rolling and hot finish rolling, the use of lubricant pass and the control of cold rolling deformation, the design target that the coating reaches more than 2 percent is realized aiming at a 1.60-3.25mm thin plate, and the problems of uneven thickness of the coating layer and poor surface quality are successfully ensured; the mass of the surface after anodic oxidation is more than grade B; the problem of unstable process in the production process is solved.
2. The rolling process of the invention is excellent: the hot rough rolling, the hot finish rolling and the high-precision cold rolling are matched with each other, the opening pass and the spraying amount of the lubricating emulsion are accurately controlled, and the aviation-grade aluminum alloy coated skin sheet with a high-quality surface, no plate warping and high coating uniformity and with the thickness of 1.60-3.25mm can be obtained. The produced plate not only ensures the warping phenomenon between the cladding plate and the substrate, but also ensures the quality of the anodized surface to reach B level due to the subsequent sufficient lubrication
3. Thickness of the composite skin sheet: the invention develops the clad thin plate with the thickness ranging from 1.60 mm to 3.25mm, and the clad T6-state thin plate with the thickness can be directly used as a skin outer plate of a large airplane.
4. The heat treatment process comprises the following steps: by adopting continuous annealing line production equipment with high intelligent control and high temperature control precision control, the optimized parameters of the heat treatment process are reasonably formulated, and all performance indexes meeting the standard requirements are obtained.
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 map of the invention after cold rolling;
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. chemical components of the ingot casting: the content of Si is less than 0.08%, the content of Fe is less than 0.12%, the content of Zn is 5.6% -5.9%, the content of Cu is 1.3% -1.6%, the content of Mg is 2.4% -2.7%, the content of Mn is less than 0.1%, the content of Cr is 0.18% -0.21%, the content of Ti is less than 0.1%, the content of other impurity elements is less than 0.05% individually, and the total content is less 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. Placing the 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, slagging off, sampling to detect chemical components, and transferring the melt to a holding furnace after the components are proper. Refining the mixed gas on the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, performing online (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0 kg/t) and CCF two-stage filtration), and casting into an aluminum alloy cast ingot. 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: and (3) 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 chamber 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-alloy 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad thin plate with the finished product thickness of 1.60-3.25mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the thickness T of a clad plate used for the aluminum clad thin plate is 13-15mm, the width of the clad plate is equal to the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad plate is equal to the length of the core ingot- (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 at intervals of 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 roughing for 20-23 times, welding and rolling the first two times, controlling the rolling reduction by 2-3mm, and controlling the rolling speed to be 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 10% and 40% 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 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, the roller surface is cleaned by using a brush roller in the rolling gap, the thickness of hot rough rolling is controlled to be 35-45mm, 5-8 passes of hot finish rolling are carried out, the finish rolling temperature is controlled to be 300-330 ℃, and the thickness of a hot rolled finished product is 3.5-7.0 mm.
8. The cold rolling process comprises the following steps: for a thin plate with the thickness of 1.60-3.25mm, a hot-rolled plate with the thickness of 7.0-7.5mm is subjected to 2-3 cold rolling processes until the thickness is 1.60-3.25 mm.
9. 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.
10. Solid solution aging process: the annealed sheet has a fine annealed grain structure considering that the annealed structure only has a small amount of undissolved precipitated phases, and if high-temperature solid solution is adopted, fine grains grow abnormally to form a coarse crystal form so as to influence the performance of the clad sheet. The solid solution and aging are carried out in a continuous annealing line, the solid solution temperature is 465-470 ℃, the aging time is 30-60min, the solid solution is directly quenched in a quenching zone after solid solution, and then enters an aging zone to be aged to a T6 state, the aging system is 120-125 ℃, and the aging time is 24-36 h.
The performance of the T6-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 555MPa, and the standard requirement is more than or equal to 510 MPa; the yield strength is 486 MPa; the standard requirement is more than or equal to 441MPa, the elongation is 15.0 percent and is more than or equal to 9 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 percent, the standard that the coating rate is more than or equal to 2 percent is met, and the surface quality after anodic oxidation is B grade.
Example 2
1. Chemical components of the ingot casting: the content of Si is less than 0.08%, the content of Fe is less than 0.12%, the content of Zn is 5.6% -5.9%, the content of Cu is 1.3% -1.6%, the content of Mg is 2.4% -2.7%, the content of Mn is less than 0.1%, the content of Cr is 0.18% -0.21%, the content of Ti is less than 0.1%, the content of other impurity elements is less than 0.05% individually, and the total content is less 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. Placing the 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, slagging off, sampling to detect chemical components, and transferring the melt to a holding furnace after the components are proper. Refining the mixed gas on the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, performing online (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0 kg/t) and CCF two-stage filtration), and casting into an aluminum alloy cast ingot. 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: and (3) 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 chamber 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-alloy 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad thin plate with the finished product thickness of 1.60-3.25mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the thickness T of a clad plate used for the aluminum clad thin plate is 13-15mm, the width of the clad plate is equal to the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad plate is equal to the length of the core ingot- (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 at intervals of 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 roughing for 20-23 times, welding and rolling the first two times, controlling the rolling reduction by 2-3mm, and controlling the rolling speed to be 0.35-0.5 m/s. The latter pass adopts conventional rolling mode, the 4 th pass opens the emulsion, the spraying amount is 10% and 40% respectively, and the spraying amount of the emulsion from 9 th to 9 th pass is 40% and 50% respectively, and the last pass of rolling is kept. The rolling 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, the roller surface is cleaned by using a brush roller in the rolling gap, the thickness of hot rough rolling is controlled to be 35-45mm, 5-8 passes of hot finish rolling are carried out, the finish rolling temperature is controlled to be 300-330 ℃, and the thickness of a hot rolled finished product is 3.5-7.0 mm.
8. The cold rolling process comprises the following steps: for a thin plate with the thickness of 1.60-3.25mm, a hot-rolled plate with the thickness of 7.0-7.5mm is subjected to 2-3 cold rolling processes until the thickness is 1.60-3.25 mm.
9. 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.
10. Solid solution aging process: the annealed sheet has a fine annealed grain structure considering that the annealed structure only has a small amount of undissolved precipitated phases, and if high-temperature solid solution is adopted, fine grains grow abnormally to form a coarse crystal form so as to influence the performance of the clad sheet. The solid solution and aging are carried out in a continuous annealing line, the solid solution temperature is 465-470 ℃, the aging time is 30-60min, the solid solution is directly quenched in a quenching zone after solid solution, and then enters an aging zone to be aged to a T6 state, the aging system is 120-125 ℃, and the aging time is 24-36 h.
The performance of the T6-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 553MPa, and the standard requirement is more than or equal to 510 MPa; the yield strength is 482 MPa; the standard requirement is more than or equal to 441MPa, the elongation is 14.5 percent and is more than or equal to 9 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 percent, the standard that the coating rate is more than or equal to 2 percent is met, and the surface quality after anodic oxidation is B grade.
Example 3
1. Chemical components of the ingot casting: the content of Si is less than 0.08%, the content of Fe is less than 0.12%, the content of Zn is 5.6% -5.9%, the content of Cu is 1.3% -1.6%, the content of Mg is 2.4% -2.7%, the content of Mn is less than 0.1%, the content of Cr is 0.18% -0.21%, the content of Ti is less than 0.1%, the content of other impurity elements is less than 0.05% individually, and the total content is less 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. Placing the 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, slagging off, sampling to detect chemical components, and transferring the melt to a holding furnace after the components are proper. Refining the mixed gas on the furnace side for 30-50min, standing for 40min when the temperature of the melt reaches 710-740 ℃, performing online (SNIF degassing, adding a refiner (Al5Ti1B point input amount is 1.5-2.0 kg/t) and CCF two-stage filtration), and casting into an aluminum alloy cast ingot. 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: and (3) 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 chamber 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-alloy 7xxx aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the aluminum clad thin plate with the finished product thickness of 1.60-3.25mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the thickness T of a clad plate used for the aluminum clad thin plate is 13-15mm, the width of the clad plate is equal to the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad plate is equal to the length of the core ingot- (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 at intervals of 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 roughing for 20-23 times, welding and rolling the first two times, controlling the rolling reduction by 2-3mm, and controlling the rolling speed to be 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 10% and 40% 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 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, the roller surface is cleaned by using a brush roller in the rolling gap, the thickness of hot rough rolling is controlled to be 35-45mm, 5-8 passes of hot finish rolling are carried out, the finish rolling temperature is controlled to be 300-330 ℃, and the thickness of a hot rolled finished product is 3.5-7.0 mm.
8. The cold rolling process comprises the following steps: for a thin plate with the thickness of 1.60-3.25mm, a hot-rolled plate with the thickness of 7.0-7.5mm is subjected to 2-3 cold rolling processes until the thickness is 1.60-3.25 mm.
9. 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.
10. Solid solution aging process: the annealed sheet has a fine annealed grain structure considering that the annealed structure only has a small amount of undissolved precipitated phases, and if high-temperature solid solution is adopted, fine grains grow abnormally to form a coarse crystal form so as to influence the performance of the clad sheet. The solid solution aging is carried out in a continuous annealing line, the solid solution temperature is 467-.
The performance of the T6-state coated aluminum sheet meets the AMS4048 requirement, the tensile strength is 525MPa, and the standard requirement is more than or equal to 510 MPa; the yield strength is 472 MPa; the standard requirement is more than or equal to 441MPa, the elongation is 16.0 percent and is more than or equal to 9 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 percent, the standard that the coating rate is more than or equal to 2 percent is met, and the surface quality after anodic oxidation is B grade.
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 (4)
1. A preparation method of a 7075 aluminum alloy clad skin sheet for T6-state aviation is characterized by comprising the following steps: the method comprises the following steps:
the method comprises the following steps: after the coating material is attached to the ingot, the periphery of the coating material is 20-30mm away from the edge of the ingot, and the fixed welding is carried out by taking 7075-F state aluminum alloy as a welding material every 1000-1500mm in the length direction;
step two: heating the clad ingot welded with the clad material obtained in the step one and the ingot to 450-grade 470 ℃, preserving heat for 2-5h, carrying out hot rolling, setting 20-23 hot rolling passes in the hot rolling, carrying out the first two welding rolling passes, controlling the reduction amount to be 2-3mm, controlling the rolling speed to be 0.35-0.5m/s, adopting a conventional rolling mode in the later pass, adding emulsion at the beginning of the sixth rolling pass, controlling the opening degree of an upper emulsifier spray nozzle to be 10% in the sixth rolling pass to the eighth rolling pass, controlling the opening degree of a lower emulsifier spray nozzle to be 40%, controlling the opening degree of an upper emulsifier spray nozzle to be 40% in the ninth rolling pass to the last rolling pass, and controlling the opening degree of a lower emulsifier spray nozzle to be 80%; controlling the rolling reduction of each pass at the beginning of the third rolling to be less than or equal to 30mm, controlling the rolling speed to be less than or equal to 2.0m/s, cleaning the roll surface of a rolling gap by using a brush roll, controlling the thickness of hot rough rolling to be 35-45mm, performing 5-8 passes of hot finish rolling, controlling the finish rolling temperature to be 300-330 ℃ and controlling the thickness of a hot rolled finished product to be 7.0-7.5 mm;
step three: carrying out 2-3 cold rolling on a hot-rolled plate with the thickness of 7.0-7.5mm to 1.60-3.25 mm;
step four: preserving the heat of the cold-rolled plate for 2h at the temperature of 370-380 ℃, cooling to below 150 ℃ and discharging;
step five: after the annealing is finished, the temperature is kept for 30-60min at the temperature of 465-470 ℃, the temperature is reduced by quenching, the steel plate is sent into an aging furnace, the aging temperature is 120-125 ℃, the aging time is 24-36h, and the temperature is reduced to the room temperature, so that the T6-state plate is obtained.
2. The method for preparing the 7075 aluminum alloy clad skin sheet for T6 mode aviation according to claim 1, wherein the method comprises the following steps: the alloy composition of the ingot cast in the first step is as follows: the steel is characterized by comprising the following components, by weight, less than 0.08% of Si, less than 0.12% of Fe, 5.6% -5.9% of Zn, 1.3% -1.6% of Cu, 2.4% -2.7% of Mg, less than 0.1% of Mn, 0.18% -0.21% of Cr, less than 0.1% of Ti, no more than 0.05% of other impurity elements, no more than 0.15% of the total, and the balance of aluminum.
3. The preparation method of the 7075 aluminum alloy clad skin sheet for T6 mode aviation according to claim 1 or 2, characterized by comprising the following steps: the preparation method of the cast ingot 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 cast ingot in 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, pushing the cast ingot into a cooling chamber for rapid cooling.
4. The method for preparing the 7075 aluminum alloy clad skin sheet for T6 mode aviation according to claim 1, wherein the method comprises the following steps: the clad material adopts a low-alloy 7-series aluminum plate with higher corrosion resistance, and the thickness of the clad plate is 13-15 mm. For the clad aluminum sheet with the finished thickness of 1.6-3.25mm, the minimum cladding rate is 2%, the nominal cladding rate is 3%, the thickness of the clad plate used for the clad aluminum sheet is 13-15mm, the width of the clad plate is equal to the effective rolling face width of the core ingot- (25 +/-15 mm) × 2, and the length of the clad plate is equal to the length of the core ingot- (200 +/-10 mm) × 2.
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| CN115572924A (en) * | 2022-09-28 | 2023-01-06 | 中国航发北京航空材料研究院 | Process method for reducing damage tolerance anisotropy of 7000 series aircraft plate |
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| 增广根 等著: "GB/T 3190-2020变形铝及铝合金化学成分", vol. 1, 31 December 2019, 四川大学出版社, pages: 158 - 160 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114653772A (en) * | 2022-02-18 | 2022-06-24 | 西南铝业（集团）有限责任公司 | 7-series aluminum alloy and preparation process thereof |
| CN115572924A (en) * | 2022-09-28 | 2023-01-06 | 中国航发北京航空材料研究院 | Process method for reducing damage tolerance anisotropy of 7000 series aircraft plate |
| CN115572924B (en) * | 2022-09-28 | 2023-11-21 | 中国航发北京航空材料研究院 | Technological method for reducing damage tolerance anisotropy of 7000 series aircraft plates |
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