CN110983133A - Method for eliminating coarse crystal ring of aluminum alloy bar for spaceflight - Google Patents
Method for eliminating coarse crystal ring of aluminum alloy bar for spaceflight Download PDFInfo
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- CN110983133A CN110983133A CN201911350004.1A CN201911350004A CN110983133A CN 110983133 A CN110983133 A CN 110983133A CN 201911350004 A CN201911350004 A CN 201911350004A CN 110983133 A CN110983133 A CN 110983133A
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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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
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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
- C22C1/026—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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
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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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
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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
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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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
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Abstract
The invention discloses a method for eliminating a macrocrystalline ring of an aluminum alloy bar for aerospace, and relates to the field of aluminum alloy bar methods for aerospace. The invention aims to solve the technical problem that the aerospace bar coarse crystal ring prepared by extrusion in the prior art exceeds the standard requirement. The method comprises the following steps: firstly, casting an aluminum alloy ingot; secondly, heating and extruding the cast ingot; thirdly, annealing; fourthly, end processing; fifthly, passing through a die for cold drawing; sixthly, quenching; seventhly, stretching and straightening; and eighthly, straightening in a roller mode, and thus obtaining the aerospace aluminum alloy bar material with the coarse crystal ring eliminated. The aluminum alloy bar prepared by the invention can reach the condition of no coarse crystal ring and meet the standard requirement; and the mechanical property also meets the application requirement of aerospace products. The method is used for preparing the aluminum alloy bar for spaceflight.
Description
Technical Field
The invention relates to the field of aluminum alloy bar material method for spaceflight.
Background
The parts in fighters of fighters series in China need novel alloy bars which cannot be replaced due to the alloy characteristics, and the alloy parts are used under high temperature conditions, so that the conditions are severe, the requirements on performance and macrostructure are strict, and the requirement on coarse crystal rings is particularly met at most 2mm while the mechanical performance is ensured. However, the depth of the coarse crystal ring of the bar produced according to the prior art is still 2.5mm until the head end is the minimum, and the coarse crystal ring which does not meet the standard specification is less than or equal to 2mm, so that the application requirement of the bar cannot be met.
Disclosure of Invention
The invention provides a method for eliminating macrocrystalline rings of an aerospace aluminum alloy bar, aiming at solving the technical problem that the macrocrystalline rings of the aerospace bar prepared by extrusion in the prior art exceed the standard requirements.
A method for eliminating macrocrystalline rings of an aluminum alloy bar for aerospace is characterized by comprising the following steps:
firstly, according to the mass percentage of elements as Mg: 1.7-2.3%, less than or equal to 0.2% of Si, less than or equal to 0.3% of Fe, Cu: 3.8% -4.3%, Mn: 0.40-0.9 percent of Al ingot, less than or equal to 0.1 percent of Ti, less than or equal to 0.1 percent of Zn and the balance of Al, weighing the aluminum ingot, the Mg ingot, the Al-Cu intermediate alloy and the Al-Mn intermediate alloy, and then carrying out fusion casting to obtain an aluminum alloy ingot;
secondly, placing the aluminum alloy ingot prepared in the first step into a resistance heating furnace, heating to the temperature of 440-460 ℃, and extruding by using an aluminum alloy bar mold to obtain an aluminum alloy bar blank;
thirdly, heating the rough aluminum alloy bar material obtained in the second step to 430-450 ℃, preserving heat for 3-3.5 hours, then cooling to below 270 ℃, discharging, and carrying out annealing treatment;
fourthly, carrying out end treatment on the rough material of the aluminum alloy bar processed in the third step;
fifthly, cold drawing the rough material of the aluminum alloy bar processed in the step four by adopting a drawing die;
sixthly, heating the rough materials of the aluminum alloy bar processed in the step five to 495-504 ℃, preserving heat, and then soaking the rough materials into water with the temperature of 10-35 ℃ for quenching within 30 s;
seventhly, stretching and straightening the rough aluminum alloy bar material processed in the step six;
and eighthly, carrying out roller straightening on the rough aluminum alloy bar material treated in the step seven to obtain an aluminum alloy bar material, and finishing the method for eliminating the macrocrystalline ring of the aluminum alloy bar material for spaceflight.
The end of the rough material of the aluminum alloy bar is processed by a head rolling machine in the fourth step, the end of the rough material of the aluminum alloy bar is flat after being processed, a clamping head is favorably adopted to tightly clamp the rough material of the aluminum alloy bar, and the drawing is convenient;
and step six, determining the heat preservation time according to the specification of the aluminum alloy bar.
In the invention, Si, Fe, Ti and Zn are impurity elements.
The invention has the beneficial effects that:
according to the invention, the over-mold cold drawing procedure is added before quenching, and a reasonable annealing system is adopted, so that the depth of the coarse crystal ring of the bar material is reduced under the condition of ensuring the surface quality and the mechanical property of the bar material, the defect of the coarse crystal ring is basically and completely eliminated, the waste of the coarse crystal ring is reduced, and the energy waste caused by repeated sampling is avoided; the plasticity of the bar blank before cold stretching is a necessary condition for determining the quality of the bar and whether the stretching is smooth, and the invention selects proper annealing temperature, thereby not only ensuring the surface quality of the cold-drawn bar, but also ensuring that the performance index and the macroscopic crystal ring condition of the prepared bar meet the standard and the user requirement; the grain size of the bar depends on the deformation before quenching, the bar with the deformation below 13.8 percent has coarse grains, the small deformation creates conditions for the rapid growth of the grains, and the performance is reduced along with the rapid growth. The bar without the coarse crystal ring has a fine crystal structure, so the fine crystal structure is formed in the quenched bar and has a large deformation amount.
According to the invention, the cold stretching process is added after extrusion, the heat treatment system is optimized, the comprehensive requirements of users on the macroscopic crystal ring and the performance of the alloy bar are met, the prepared aluminum alloy bar has good physical size and surface quality, the macroscopic crystal ring completely eliminates the requirements of users, the comprehensive mechanical property is excellent, the tensile strength of the bar with the diameter not larger than 22mm is not smaller than 390MPa, the yield strength is not smaller than 275MPa, the elongation after breakage is not smaller than 10%, the tensile strength of the bar with the diameter larger than 22mm is not smaller than 420MPa, the yield strength is not smaller than 295MPa, and the elongation after breakage is not smaller than 8% through GB/T228 'Metal Material Room temperature tensile Property test method'.
The method is used for preparing the aluminum alloy bar for spaceflight.
Drawings
FIG. 1 is a photograph of a macrostructure of an aluminum alloy rod for aerospace manufactured according to the first embodiment;
FIG. 2 is a photograph of the microstructure of the aerospace aluminum alloy rod prepared in the first example.
Detailed Description
The technical solution of the present invention is not limited to the specific embodiments listed below, and includes any combination of the specific embodiments.
The first embodiment is as follows: the embodiment of the invention relates to a method for eliminating coarse grain rings of an aluminum alloy bar for aerospace, which is carried out according to the following steps:
firstly, according to the mass percentage of elements as Mg: 1.7-2.3%, less than or equal to 0.2% of Si, less than or equal to 0.3% of Fe, Cu: 3.8% -4.3%, Mn: 0.40-0.9 percent of Al ingot, less than or equal to 0.1 percent of Ti, less than or equal to 0.1 percent of Zn and the balance of Al, weighing the aluminum ingot, the Mg ingot, the Al-Cu intermediate alloy and the Al-Mn intermediate alloy, and then carrying out fusion casting to obtain an aluminum alloy ingot;
secondly, placing the aluminum alloy ingot prepared in the first step into a resistance heating furnace, heating to the temperature of 440-460 ℃, and extruding by using an aluminum alloy bar mold to obtain an aluminum alloy bar blank;
thirdly, heating the rough aluminum alloy bar material obtained in the second step to 430-450 ℃, preserving heat for 3-3.5 hours, then cooling to below 270 ℃, discharging, and carrying out annealing treatment;
fourthly, carrying out end treatment on the rough material of the aluminum alloy bar processed in the third step;
fifthly, cold drawing the rough material of the aluminum alloy bar processed in the step four by adopting a drawing die;
sixthly, heating the rough materials of the aluminum alloy bar processed in the step five to 495-504 ℃, preserving heat, and then soaking the rough materials into water with the temperature of 10-35 ℃ for quenching within 30 s;
seventhly, stretching and straightening the rough aluminum alloy bar material processed in the step six;
and eighthly, carrying out roller straightening on the rough aluminum alloy bar material treated in the step seven to obtain an aluminum alloy bar material, and finishing the method for eliminating the macrocrystalline ring of the aluminum alloy bar material for spaceflight.
According to the embodiment, the cold stretching process is added after extrusion, the heat treatment system is optimized, the comprehensive requirements of users on the macroscopic crystal ring and the performance of the alloy bar are met, the prepared aluminum alloy bar is good in physical size and surface quality, the macroscopic crystal ring can be completely eliminated, the comprehensive mechanical performance is excellent, the tensile strength of the bar with the diameter not larger than 22mm is not smaller than 390MPa, the yield strength is not smaller than 275MPa, the elongation after breakage is not smaller than 10%, the tensile strength of the bar with the diameter larger than 22mm is not smaller than 420MPa, the yield strength is not smaller than 295MPa, and the elongation after breakage is not smaller than 8% through GB/T228 metal material room temperature tensile property test method.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: in the first step, the mass percentages of elements are Mg: 2.03%, Si: 0.05%, Fe: 0.16%, Cu: 3.81%, Mn: 0.63%, Ti: 0.02%, Zn: 0.02 percent and the balance of Al are fused and cast. 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: in the first step, the casting temperature is 700-750 ℃. The other is 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: heating to 450 ℃ in the second step. The others are the same as in one of the first to third embodiments.
The fifth concrete implementation mode: the difference between this embodiment and one of the first to fourth embodiments is: and step three, heating to 440 ℃, and preserving heat for 3 hours. The other is the same as one of the first to fourth embodiments.
The sixth specific implementation mode: the difference between this embodiment and one of the first to fifth embodiments is: in the third step, the cooling rate is controlled to be 30 ℃/h. The other is the same as one of the first to fifth embodiments.
The seventh embodiment: the difference between this embodiment and one of the first to sixth embodiments is: and fifthly, controlling the cold working deformation of the rough aluminum alloy bar to be 18.1% for cold drawing. The other is the same as one of the first to sixth embodiments.
The specific implementation mode is eight: the present embodiment differs from one of the first to seventh embodiments in that: in the sixth step, the rough material of the aluminum alloy bar is heated to 500 ℃, and the temperature is kept for 120-210 min. The other is the same as one of the first to seventh embodiments.
The specific implementation method nine: the present embodiment differs from the first to eighth embodiments in that: and seventhly, controlling the stretching straightening deformation rate to be 1-3%. The rest is the same as the first to eighth embodiments.
The detailed implementation mode is ten: the present embodiment differs from one of the first to ninth embodiments in that: and seventhly, controlling the stretching straightening deformation rate to be 1.5%. The other is the same as one of the first to ninth embodiments.
The following examples were used to demonstrate the beneficial effects of the present invention:
the first embodiment is as follows:
the embodiment provides a method for eliminating macrocrystalline rings on an aluminum alloy bar for aerospace, which is carried out according to the following steps:
firstly, according to the mass percentage of elements as Mg: 2.03%, Si: 0.05%, Fe: 0.16%, Cu: 3.81%, Mn: 0.63%, Ti: 0.02%, Zn: weighing an aluminum ingot, an Mg ingot, an Al-Cu intermediate alloy and an Al-Mn intermediate alloy according to 0.02% and the balance of Al, and then carrying out fusion casting to obtain an aluminum alloy ingot; the casting temperature is 730 ℃;
secondly, placing the aluminum alloy ingot prepared in the first step into a resistance heating furnace, heating to 450 ℃, and extruding by using an aluminum alloy bar mold to obtain an aluminum alloy bar blank;
thirdly, heating the rough aluminum alloy bar material obtained in the second step to 440 ℃, preserving heat for 3 hours, then controlling the cooling rate to be 30 ℃/h, cooling to below 270 ℃, discharging, and carrying out annealing treatment;
fourthly, carrying out end treatment on the rough material of the aluminum alloy bar processed in the third step;
fifthly, cold drawing the rough aluminum alloy bar processed in the fourth step by using a drawing die, and controlling the cold working deformation of the rough aluminum alloy bar to be 18.1%;
sixthly, heating the rough aluminum alloy bar material processed in the step five to 500 ℃, preserving heat for 150min, and then soaking the rough aluminum alloy bar material into water at the temperature of 10-35 ℃ within 30s for quenching;
seventhly, performing stretching straightening on the aluminum alloy bar blank processed in the step six, and controlling the stretching straightening deformation rate to be 1.5%;
and eighthly, carrying out roller straightening on the rough aluminum alloy bar material treated in the step seven to obtain an aluminum alloy bar material, and finishing the method for eliminating the macrocrystalline ring of the aluminum alloy bar material for spaceflight.
FIG. 1 is a photograph of a macrostructure of an aluminum alloy rod for aerospace manufactured according to the first embodiment; FIG. 2 is a photograph of the microstructure of the aerospace aluminum alloy rod prepared in the first example. The photos show that the aluminum alloy bar prepared in the first embodiment has good physical size and surface quality, good macroscopic structure and fine grains, and thoroughly eliminates the defect of coarse crystal rings. The aluminum alloy bar has good formability in industrial production and excellent comprehensive mechanical property, and is tested to have the tensile strength of 443-449 MPa, the non-proportional elongation strength of 317-327 MPa and the elongation after fracture of 19.2% -23.4%.
Claims (10)
1. A method for eliminating macrocrystalline rings of an aluminum alloy bar for aerospace is characterized by comprising the following steps:
firstly, according to the mass percentage of elements as Mg: 1.7-2.3%, less than or equal to 0.2% of Si, less than or equal to 0.3% of Fe, Cu: 3.8% -4.3%, Mn: 0.40-0.9 percent of Al ingot, less than or equal to 0.1 percent of Ti, less than or equal to 0.1 percent of Zn and the balance of Al, weighing the aluminum ingot, the Mg ingot, the Al-Cu intermediate alloy and the Al-Mn intermediate alloy, and then carrying out fusion casting to obtain an aluminum alloy ingot;
secondly, placing the aluminum alloy ingot prepared in the first step into a resistance heating furnace, heating to the temperature of 440-460 ℃, and extruding by using an aluminum alloy bar mold to obtain an aluminum alloy bar blank;
thirdly, heating the rough aluminum alloy bar material obtained in the second step to 430-450 ℃, preserving heat for 3-3.5 hours, then cooling to below 270 ℃, discharging, and carrying out annealing treatment;
fourthly, carrying out end treatment on the rough material of the aluminum alloy bar processed in the third step;
fifthly, cold drawing the rough material of the aluminum alloy bar processed in the step four by adopting a drawing die;
sixthly, heating the rough materials of the aluminum alloy bar processed in the step five to 495-504 ℃, preserving heat, and then soaking the rough materials into water with the temperature of 10-35 ℃ for quenching within 30 s;
seventhly, stretching and straightening the rough aluminum alloy bar material processed in the step six;
and eighthly, carrying out roller straightening on the rough aluminum alloy bar material treated in the step seven to obtain an aluminum alloy bar material, and finishing the method for eliminating the macrocrystalline ring of the aluminum alloy bar material for spaceflight.
2. The method for eliminating the macrocrystalline ring of the aluminum alloy bar for the aerospace use as claimed in claim 1, wherein the ratio of the elements in the first step is Mg: 2.03%, Si: 0.05%, Fe: 0.16%, Cu: 3.81%, Mn: 0.63%, Ti: 0.02%, Zn: 0.02 percent and the balance of Al are fused and cast.
3. The method for eliminating macrocrystalline rings of aluminum alloy bar for aerospace use as claimed in claim 1, wherein the melting and casting temperature in the first step is 700-750 ℃.
4. The method for eliminating macrocrystalline rings of aluminum alloy bar for aerospace use as claimed in claim 1, wherein the heating temperature in the second step is 450 ℃.
5. The method for eliminating the macrocrystalline ring of the aluminum alloy bar for aerospace as claimed in claim 1, wherein the temperature in the third step is 440 ℃ and the temperature is kept for 3 hours.
6. The method for eliminating the macrocrystalline ring of the aluminum alloy bar for aerospace as claimed in claim 1, wherein the temperature reduction rate in the third step is controlled to be 30 ℃/h.
7. The method for eliminating the macrocrystalline ring of the aluminum alloy bar for the aerospace use as claimed in claim 1, wherein the step five is to control the rough cold deformation of the aluminum alloy bar to be 18.1% for cold drawing.
8. The method for eliminating the macrocrystalline ring of the aluminum alloy bar for the aerospace as claimed in claim 1, wherein in the sixth step, the rough material of the aluminum alloy bar is heated to 500 ℃ and is kept warm for 120-210 min.
9. The method for eliminating macrocrystalline rings of an aluminum alloy bar for aerospace use as claimed in claim 1, wherein the stretch-straightening deformation rate in the seventh step is controlled to be 1-3%.
10. The method for eliminating macrocrystalline rings of aluminum alloy rods for aerospace as claimed in claim 9, wherein the stretch-straightening deformation rate in the seventh step is controlled to be 1.5%.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112323000A (en) * | 2020-11-13 | 2021-02-05 | 西南铝业（集团）有限责任公司 | Method for eliminating coarse crystal ring of alloy extrusion product |
| CN112522649A (en) * | 2020-12-03 | 2021-03-19 | 东北轻合金有限责任公司 | Manufacturing method of high-strength high-toughness large-size aluminum alloy plate for large passenger plane |
| CN112725668A (en) * | 2020-12-28 | 2021-04-30 | 东北轻合金有限责任公司 | 6061 aluminum alloy bar production method capable of eliminating coarse crystal ring |
| CN113293273A (en) * | 2021-04-13 | 2021-08-24 | 中铝材料应用研究院有限公司 | Processing method of 2xxx series aluminum alloy bar and wire for fastener |
| CN114277294A (en) * | 2021-12-24 | 2022-04-05 | 东北轻合金有限责任公司 | Preparation method of aluminum alloy bar with high temperature resistance |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114277294A (en) * | 2021-12-24 | 2022-04-05 | 东北轻合金有限责任公司 | Preparation method of aluminum alloy bar with high temperature resistance |
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