CN115874031A - Machining method of 2A12 aluminum alloy plate for aviation - Google Patents
Machining method of 2A12 aluminum alloy plate for aviation Download PDFInfo
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- CN115874031A CN115874031A CN202211566925.3A CN202211566925A CN115874031A CN 115874031 A CN115874031 A CN 115874031A CN 202211566925 A CN202211566925 A CN 202211566925A CN 115874031 A CN115874031 A CN 115874031A
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 66
- 238000000034 method Methods 0.000 title claims abstract description 43
- 238000003754 machining Methods 0.000 title description 2
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 45
- 239000000956 alloy Substances 0.000 claims abstract description 45
- 238000010438 heat treatment Methods 0.000 claims abstract description 39
- 238000005266 casting Methods 0.000 claims abstract description 31
- 238000003672 processing method Methods 0.000 claims abstract description 15
- 238000005096 rolling process Methods 0.000 claims description 39
- 238000001816 cooling Methods 0.000 claims description 16
- 238000003723 Smelting Methods 0.000 claims description 11
- 239000010949 copper Substances 0.000 claims description 9
- 238000005098 hot rolling Methods 0.000 claims description 7
- 230000010354 integration Effects 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 6
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 6
- 238000009529 body temperature measurement Methods 0.000 claims description 6
- 239000000498 cooling water Substances 0.000 claims description 6
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 239000000839 emulsion Substances 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- 239000012856 weighed raw material Substances 0.000 claims description 6
- 238000007599 discharging Methods 0.000 claims description 5
- 238000010008 shearing Methods 0.000 claims description 5
- 238000005303 weighing Methods 0.000 claims description 5
- 238000003801 milling Methods 0.000 claims description 4
- QQHSIRTYSFLSRM-UHFFFAOYSA-N alumanylidynechromium Chemical compound [Al].[Cr] QQHSIRTYSFLSRM-UHFFFAOYSA-N 0.000 claims description 2
- 229910018125 Al-Si Inorganic materials 0.000 claims 2
- 229910018520 Al—Si Inorganic materials 0.000 claims 2
- 229910018575 Al—Ti Inorganic materials 0.000 claims 2
- 229910018580 Al—Zr Inorganic materials 0.000 claims 2
- 229910001030 Iron–nickel alloy Inorganic materials 0.000 claims 2
- 238000001514 detection method Methods 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 10
- 238000000265 homogenisation Methods 0.000 abstract description 6
- 238000002360 preparation method Methods 0.000 abstract description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- ZGUQGPFMMTZGBQ-UHFFFAOYSA-N [Al].[Al].[Zr] Chemical compound [Al].[Al].[Zr] ZGUQGPFMMTZGBQ-UHFFFAOYSA-N 0.000 description 4
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 4
- CSDREXVUYHZDNP-UHFFFAOYSA-N alumanylidynesilicon Chemical compound [Al].[Si] CSDREXVUYHZDNP-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- UGKDIUIOSMUOAW-UHFFFAOYSA-N iron nickel Chemical compound [Fe].[Ni] UGKDIUIOSMUOAW-UHFFFAOYSA-N 0.000 description 4
- KBMLJKBBKGNETC-UHFFFAOYSA-N magnesium manganese Chemical compound [Mg].[Mn] KBMLJKBBKGNETC-UHFFFAOYSA-N 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- 239000012535 impurity Substances 0.000 description 3
- 239000011572 manganese Substances 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 239000011701 zinc Substances 0.000 description 3
- 238000000137 annealing Methods 0.000 description 2
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000010915 one-step procedure Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
A processing method of an aviation 2A12 aluminum alloy plate relates to a processing method of an aluminum alloy plate. The invention aims to solve the technical problems of complex homogenization treatment and heating process and long processing time of the 2A12 alloy. When the ingot casting homogenization treatment and the ingot casting heating are carried out, the two steps of working procedures are shortened into one step of working procedure by adopting a uniform fire heating integrated method, the production process takes about 40 hours, at least 15 hours are saved compared with the prior art, the mechanical property same as that of a hot rolled plate is obtained, the productivity is greatly saved, and the production cost is reduced; the flaw detection results of the 2A12 aluminum alloy plate prepared by the method are all above A grade, and part of the flaw detection results can reach AA grade or AAA grade, while the flaw detection results of the plate obtained by the original preparation method are basically B grade or not reach the lowest grade.
Description
Technical Field
The invention relates to a processing method of an aluminum alloy plate.
Background
The 2A12 aluminum alloy (Al-Cu-Mg series alloy) is a heat-treatable reinforced alloy, and is an aluminum alloy structural material which is widely applied in China and has good comprehensive performance. The composite material has the characteristics of small density, high strength, excellent corrosion resistance, good formability, good low-temperature performance and the like, and is widely applied to the field of military materials such as aviation, aerospace, ship manufacturing and the like. The main states of the 2A12 aluminum alloy include H112, T351 and T4 states, and the 2A12 aluminum alloy is mainly used for manufacturing parts such as skeletons, skins, ribs and spars of airplanes. The 2A12 aluminum alloy plate needs to be subjected to homogenizing annealing and ingot heating before rolling, and the homogenizing annealing aims to enable unbalanced eutectic structures in the ingot to be distributed in a matrix to tend to be uniform and eliminate casting stress; the purpose of ingot heating is to reduce the metal deformation resistance and improve the alloy plasticity for subsequent production and processing. However, the homogenization treatment and heating process of the 2A12 alloy is complex, the processing time is long, and the processing efficiency is influenced.
Disclosure of Invention
The invention provides a processing method of an aviation 2A12 aluminum alloy plate, aiming at solving the technical problems of complex homogenization treatment and heating process and long processing time of a 2A12 alloy.
The processing method of the 2A12 aluminum alloy plate for aviation comprises the following steps:
1. respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials according to the mass percentage of elements of 0.1-0.27% of Si, 0.15-0.45% of Fe, 4.55-4.85% of Cu, 0.5-0.80% of Mn, 1.5-1.8% of Mg, 0-0.1% of Ni, 0.08-0.2% of Zn, 0-0.1% of Ti, 0.05-0.15% of Zr, 0-0.5% of Fe + Ni and the balance of Al, placing the weighed raw materials in a dry smelting furnace, and smelting for 5-6 hours at 890-924 ℃ to obtain an aluminum alloy solution;
in the 2A12 aluminum alloy plate for aviation, the content of single impurities is less than or equal to 0.05 percent, the content of all impurities is less than 0.1 percent, and the impurities in the range have no influence on the performance of the plate;
2. casting the aluminum alloy solution in the step one into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width of the aluminum alloy square ingot is 1820mm;
the semi-continuous water-cooling casting method comprises the following process parameters: the casting temperature is 750-770 ℃, the casting speed is 80-12 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. and D, placing the aluminum alloy square ingot obtained in the step two into a longitudinal pushing type heating furnace after face milling and sawing, and performing uniform heating integrated treatment to obtain an aluminum alloy ingot which can be directly rolled:
the process of the uniform fire heating integration comprises the following steps: vertically arraying aluminum alloy square ingots, arranging a plurality of N-type or K-type couples among all layers for metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the set temperature to be 490-500 ℃ when the high point temperature of the ingots measured by the couples reaches 480 +/-5 ℃, changing the set temperature to be 475-480 ℃ when the low point temperature of the ingots measured by the couples reaches 475 +/-5 ℃, preserving the heat for 19-22 h, and discharging the ingots for rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot obtained in the third step at the rolling temperature of 470-480 ℃, controlling the maximum processing deformation to be 32-41%, rolling the plate to 74-82% of the thickness of the finished product, and reserving 18-26% of the thickness allowance to obtain a hot-rolled long plate;
5. carrying out temperature control rolling on the hot-rolled long plate obtained in the fourth step, carrying out spray type cooling on the plate by using emulsion of a hot rolling mill, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the fourth step, and shearing according to multiple scales to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameter was 2.4% ± 0.2.
The invention adopts the production process of uniform heating integration in the third step, greatly shortens the production period of the 2A12 aluminum alloy plate and improves the flaw detection grade of the plate.
The invention has the advantages that:
1. the invention is a novel simple processing method of 2A12 aluminum alloy sheet material, during ingot casting homogenization treatment and ingot casting heating, the two-step procedure is shortened into one-step procedure by adopting a uniform fire heating integrated method, the production process of the invention consumes about 40h, saves at least 15h compared with the prior art, obtains the same mechanical property with a hot rolled sheet material, greatly saves the productivity and reduces the production cost;
2. compared with the plate prepared by the original method, the 2A12 aluminum alloy plate prepared by the invention utilizes the temperature-controlled rolling process technology, and simultaneously increases Zr element control, can greatly improve the flaw detection result of the plate, and has better safety level when being applied to the fields of aviation, aerospace and the like. By taking GB/T6519-2013 as a detection standard, the flaw detection results of the aluminum alloy plate prepared by the method are all above A level, and part of the flaw detection results can reach AA level or AAA level, while the flaw detection results of the plate obtained by the original preparation method are basically B level or not reach the lowest level.
Drawings
FIG. 1 is a photograph of the metallographic structure of a 2A12-H112 alloy using a conventional "ingot homogenization + ingot heating" process;
FIG. 2 is a photograph of the metallographic structure of the 2A12-H112 alloy prepared by the process of test one.
Detailed Description
The first specific implementation way is as follows: the embodiment is a processing method of an aviation 2A12 aluminum alloy plate, which is specifically carried out according to the following steps:
1. respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials according to the mass percentage of elements of 0.1-0.27% of Si, 0.15-0.45% of Fe, 4.55-4.85% of Cu, 0.5-0.80% of Mn, 1.5-1.8% of Mg, 0-0.1% of Ni, 0.08-0.2% of Zn, 0-0.1% of Ti, 0.05-0.15% of Zr, 0-0.5% of Fe + Ni and the balance of Al, placing the weighed raw materials in a dry smelting furnace, and smelting for 5-6 hours at 890-924 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the step one into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width of the aluminum alloy square ingot is 1820mm;
the semi-continuous water-cooling casting method comprises the following process parameters: the casting temperature is 750-770 ℃, the casting speed is 80-120 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. and D, placing the aluminum alloy square ingot obtained in the step two into a longitudinal pushing type heating furnace after face milling and sawing, and performing uniform heating integrated treatment to obtain an aluminum alloy ingot which can be directly rolled:
the process of the uniform fire heating integration comprises the following steps: vertically arraying aluminum alloy square ingots, arranging a plurality of N-type or K-type couples among all layers for metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the set temperature to be 490-500 ℃ when the high point temperature of the ingots measured by the couples reaches 480 +/-5 ℃, changing the set temperature to be 475-480 ℃ when the low point temperature of the ingots measured by the couples reaches 475 +/-5 ℃, preserving the temperature for 19-22 h, and discharging the ingots for rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot obtained in the third step at the rolling temperature of 470-480 ℃, controlling the maximum processing deformation to be 32-41%, rolling the plate to 74-82% of the thickness of the finished product, and reserving 18-26% of the thickness allowance to obtain a hot-rolled long plate;
5. carrying out temperature control rolling on the hot-rolled long plate obtained in the fourth step, carrying out spray type cooling on the plate by using emulsion of a hot rolling mill, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the fourth step, and shearing according to multiple scales to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameter was 2.4% ± 0.2.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: in the first step, according to the mass percent of elements, si is 0.12%, fe is 0.18%, cu is 4.51%, mn is 0.63%, mg is 1.57%, ni is 0.0053%, zn is 0.068%, ti is 0.0264%, zr is 0.11%, fe + Ni is 0-0.5% and the balance is Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-chromium intermediate alloy, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, putting the weighed raw materials into a dry smelting furnace, and smelting for 5.5 hours at 915 ℃ to obtain an aluminum alloy solution. The rest is the same as the first embodiment.
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that: the technological parameters of the semi-continuous water-cooling casting method in the step two are as follows: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa. The others are the same as in the first or second embodiment.
The fourth concrete implementation mode: the difference between this embodiment mode and one of the first to third embodiment modes is: the process of the uniform fire heating integration in the third step comprises the following steps: vertically arraying aluminum alloy square ingots, arranging a plurality of N-type or K-type couples among all layers for metal temperature measurement, setting the heating temperature to be 530 ℃, changing the set temperature to be 490 ℃ when the high point temperature of the ingots measured by the couples reaches 480 ℃, changing the set temperature to be 475 ℃ when the low point temperature of the ingots measured by the couples reaches 475 ℃, preserving heat for 19 hours, and discharging and rolling the ingots when the temperature of the ingots reaches 475 ℃. The rest is the same as one of the first to third embodiments.
The fifth concrete implementation mode: the fourth difference between the present embodiment and the specific embodiment is that: and step four, rolling the cast ingot obtained in the step three at the rolling temperature of 476 ℃, controlling the maximum processing deformation to be 40%, rolling the plate to be 81% of the thickness of the finished product, and reserving the thickness allowance of 20% to obtain the hot-rolled long plate. The rest is the same as in the fourth embodiment.
The sixth specific implementation mode: the fifth embodiment is different from the fifth embodiment in that: and fifthly, performing temperature control rolling on the hot-rolled long plate obtained in the fourth step, performing spray cooling on the plate by using emulsion of a hot rolling mill, controlling the temperature of the plate to be 175 ℃, continuing rolling, finishing rolling of the thickness allowance reserved in the fourth step, and shearing according to multiple scales to obtain the prefabricated plate. The rest is the same as the fifth embodiment.
The seventh concrete implementation mode: the sixth embodiment is different from the specific embodiment in that: step six, stretching the prefabricated plate obtained in the step five, and then sawing to obtain a finished plate; the elongation parameter was 2.5%. The rest is the same as the sixth embodiment.
The invention was verified with the following tests:
the first test: the test is a processing method of an aviation 2A12 aluminum alloy plate, and is specifically carried out according to the following steps:
1. respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials according to the mass percentage of elements of 0.12% of Si, 0.18% of Fe, 4.51% of Cu, 0.63% of Mn, 1.57% of Mg, 0.0053% of Ni, 0.068% of Zn, 0.0264% of Ti, 0.11% of Zr, 0-0.5% of Fe + Ni and the balance of Al, putting the weighed raw materials into a dry smelting furnace, and smelting for 5.5 hours at 915 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the step one into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width of the aluminum alloy square ingot is 1820mm;
the semi-continuous water-cooling casting method comprises the following process parameters: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa;
3. and D, placing the aluminum alloy square ingot obtained in the step two into a longitudinal pushing type heating furnace after face milling and sawing, and performing uniform heating integrated treatment to obtain a directly-rolled aluminum alloy ingot:
the process of the uniform heating integration comprises the following steps: vertically arraying aluminum alloy square ingots, arranging a plurality of N-type couples among all layers to carry out metal temperature measurement, setting the heating temperature to be 530 ℃, changing the set temperature to be 490 ℃ when the high point temperature of the ingots measured by the couples reaches 480 ℃, changing the set temperature to be 475 ℃ when the low point temperature of the ingots measured by the couples reaches 475 ℃, preserving heat for 19 hours, and discharging and rolling the ingots when the temperature of the ingots reaches 475 ℃;
4. rolling the cast ingot obtained in the third step at the rolling temperature of 476 ℃, controlling the maximum processing deformation to be 40%, rolling the plate to 81% of the thickness of the finished product, and reserving the thickness allowance of 20% to obtain a hot-rolled long plate;
5. carrying out temperature control rolling on the hot-rolled long plate obtained in the fourth step, carrying out spray type cooling on the plate by using emulsion of a hot rolling mill, controlling the temperature of the plate to be 175 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the fourth step, and shearing according to multiple scales to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameter was 2.5%.
Mechanical property data comparison is carried out on finished products with different thicknesses obtained in the traditional process of ingot homogenizing and ingot heating and the process of ingot homogenizing and heating integration in the first test:
and (3) analysis: the performance indexes of the 2A12-H112 alloy in the conventional 'ingot homogenizing and heating' process under different thicknesses are counted, and the performance indexes of the 2A12-H112 alloy in the 'ingot homogenizing and heating integrated' process in the first test and the corresponding thickness are counted; the indexes of the tensile strength, the yield strength and the elongation percentage of the aluminum alloy plate are close to each other, so that the conclusion can be drawn that the mechanical performance indexes of the 2A12 aluminum alloy plate prepared by the uniform fire heating integrated process and the conventional cast ingot uniform fire and cast ingot heating process are consistent, but the preparation method can be achieved by only one step of working procedure, the production time is greatly reduced, and the mechanical performance of the material can be ensured.
FIG. 1 is a photograph of the metallographic structure of a 2A12-H112 alloy prepared by a conventional "ingot homogenizing and heating" process, FIG. 2 is a photograph of the metallographic structure of a 2A12-H112 alloy prepared by a process of test one, and it can be seen from an observation of FIGS. 1 and 2 that the alloy prepared by the conventional "ingot homogenizing and heating" process and the ingot obtained by the process regime of the present invention have substantially crushed and uniformly distributed compounds after hot rolling, but the latter has a larger crushing degree and a smaller size than the former; according to the corresponding relation between the material performance and the compound size, the compound with smaller size has smaller negative influence on the plate, so that the plate has better performance, and the grade which can be achieved by flaw detection is higher, therefore, the invention has positive influence on the flaw detection grade of the plate.
Claims (7)
1. A processing method of an aviation 2A12 aluminum alloy plate is characterized in that the processing method of the aviation 2A12 aluminum alloy plate is carried out according to the following steps:
1. according to the mass percent of elements, si is 0.1% -0.27%, fe is 0.15% -0.45%, cu is 4.55% -4.85%, mn is 0.5% -0.80%, mg is 1.5% -1.8%, ni is 0-0.1%, zn is 0.08% -0.2%, ti is 0-0.1%, zr is 0.05% -0.15%, fe + Ni is 0-0.5% and the balance is Al, respectively weighing an Al-Si intermediate alloy, an Fe-Ni intermediate alloy, electrolytic copper, a Mg-Mn intermediate alloy, a pure zinc ingot, an Al-Ti intermediate alloy, an Al-Zr intermediate alloy and an Al ingot as raw materials, putting the weighed raw materials into a dry smelting furnace, and smelting for 5-6 h at 890-924 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the step one into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width of the aluminum alloy square ingot is 1820mm;
the semi-continuous water-cooling casting method comprises the following process parameters: the casting temperature is 750-770 ℃, the casting speed is 80-120 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. and D, placing the aluminum alloy square ingot obtained in the step two into a longitudinal pushing type heating furnace after face milling and sawing, and performing uniform heating integrated treatment to obtain an aluminum alloy ingot which can be directly rolled:
the process of the uniform heating integration comprises the following steps: vertically arraying aluminum alloy square ingots, arranging a plurality of N-type or K-type couples among all layers for metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the set temperature to be 490-500 ℃ when the high point temperature of the ingots measured by the couples reaches 480 +/-5 ℃, changing the set temperature to be 475-480 ℃ when the low point temperature of the ingots measured by the couples reaches 475 +/-5 ℃, preserving the heat for 19-22 h, and discharging the ingots for rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot obtained in the third step at the rolling temperature of 470-480 ℃, controlling the maximum processing deformation to be 32-41%, rolling the plate to 74-82% of the thickness of the finished product, and keeping 18-26% of the thickness of the plate for the rest to obtain a hot-rolled long plate;
5. carrying out temperature control rolling on the hot-rolled long plate obtained in the fourth step, carrying out spray type cooling on the plate by using emulsion of a hot rolling mill, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the fourth step, and shearing according to multiple scales to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameter was 2.4% ± 0.2.
2. The method for processing an aviation 2A12 aluminum alloy plate according to claim 1, wherein in the step one, according to the mass percentages of the elements, si is 0.12%, fe is 0.18%, cu is 4.51%, mn is 0.63%, mg is 1.57%, ni is 0.0053%, zn is 0.068%, ti is 0.0264%, zr is 0.11%, fe + Ni is 0-0.5%, and the balance is Al, an Al-Si intermediate alloy, an Fe-Ni intermediate alloy, electrolytic copper, a Mg-Mn intermediate alloy, a pure zinc ingot, an Al-Cr intermediate alloy, an Al-Ti intermediate alloy, an Al-Zr intermediate alloy, and an Al ingot are respectively weighed as raw materials, and the weighed raw materials are placed in a dry smelting furnace to be smelted for 5.5 hours at 915 ℃ to obtain an aluminum alloy solution.
3. The processing method of the aviation 2A12 aluminum alloy plate as claimed in claim 1, wherein the technological parameters of the semi-continuous water-cooling casting method in the second step are as follows: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa.
4. The processing method of the aviation 2A12 aluminum alloy plate according to claim 1, wherein the process of the step three in which the uniform heating is integrated is as follows: aluminum alloy square ingots are vertically listed, a plurality of N-type or K-type couples are arranged among all the layers for metal temperature measurement, the heating temperature is set to 530 ℃, the set temperature is changed to 490 ℃ when the high point temperature of the ingots measured by the couples reaches 480 ℃, the set temperature is changed to 475 ℃ when the low point temperature of the ingots measured by the couples reaches 475 ℃, the temperature is kept for 19 hours, and the ingots are discharged and rolled when the temperature of the ingots reaches 475 ℃.
5. The processing method of the aviation 2A12 aluminum alloy plate according to claim 1, wherein in the fourth step, the ingot obtained in the third step is rolled at 476 ℃ under the maximum processing deformation of 40%, the plate is rolled to 81% of the thickness of the finished product, and the balance of the thickness is 20% to obtain the hot-rolled long plate.
6. The processing method of the aviation 2A12 aluminum alloy plate according to claim 1, wherein in the fifth step, the hot-rolled long plate obtained in the fourth step is subjected to temperature-controlled rolling, the plate is subjected to spray cooling by using emulsion of a hot rolling mill, the temperature of the plate is controlled to be 175 ℃, the rolling is continued, the thickness allowance reserved in the fourth step is rolled, and the plate is cut according to multiple scales to obtain a prefabricated plate.
7. The processing method of the aviation 2A12 aluminum alloy plate as claimed in claim 1, wherein in the sixth step, the prefabricated plate obtained in the fifth step is stretched and then sawed to obtain a finished plate; the elongation parameter was 2.5%.
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Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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