CN112792150A - Extrusion method of 7150 alloy profile - Google Patents
Extrusion method of 7150 alloy profile Download PDFInfo
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- CN112792150A CN112792150A CN202011542661.9A CN202011542661A CN112792150A CN 112792150 A CN112792150 A CN 112792150A CN 202011542661 A CN202011542661 A CN 202011542661A CN 112792150 A CN112792150 A CN 112792150A
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- 239000000956 alloy Substances 0.000 title claims abstract description 80
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 79
- 238000001125 extrusion Methods 0.000 title claims abstract description 76
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 22
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000010438 heat treatment Methods 0.000 claims abstract description 11
- 230000032683 aging Effects 0.000 claims abstract description 10
- 230000006698 induction Effects 0.000 claims abstract description 8
- 238000010791 quenching Methods 0.000 claims abstract description 8
- 230000000171 quenching effect Effects 0.000 claims abstract description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 6
- 238000003723 Smelting Methods 0.000 claims description 16
- 239000011777 magnesium Substances 0.000 claims description 14
- 229910052749 magnesium Inorganic materials 0.000 claims description 14
- VVTRNRPINJRHBQ-UHFFFAOYSA-N [Cl].[Ar] Chemical compound [Cl].[Ar] VVTRNRPINJRHBQ-UHFFFAOYSA-N 0.000 claims description 10
- 238000007670 refining Methods 0.000 claims description 10
- 229910018167 Al—Be Inorganic materials 0.000 claims description 9
- 229910052804 chromium Inorganic materials 0.000 claims description 9
- 239000011651 chromium Substances 0.000 claims description 9
- 239000002994 raw material Substances 0.000 claims description 9
- 239000010936 titanium Substances 0.000 claims description 9
- 229910052719 titanium Inorganic materials 0.000 claims description 9
- 238000005303 weighing Methods 0.000 claims description 9
- 239000011701 zinc Substances 0.000 claims description 9
- 229910052725 zinc Inorganic materials 0.000 claims description 9
- 229910052726 zirconium Inorganic materials 0.000 claims description 9
- 238000009749 continuous casting Methods 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 5
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 5
- 229910001093 Zr alloy Inorganic materials 0.000 claims description 5
- ZGUQGPFMMTZGBQ-UHFFFAOYSA-N [Al].[Al].[Zr] Chemical compound [Al].[Al].[Zr] ZGUQGPFMMTZGBQ-UHFFFAOYSA-N 0.000 claims description 5
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 5
- QQHSIRTYSFLSRM-UHFFFAOYSA-N alumanylidynechromium Chemical compound [Al].[Cr] QQHSIRTYSFLSRM-UHFFFAOYSA-N 0.000 claims description 5
- 238000000137 annealing Methods 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 5
- 230000004907 flux Effects 0.000 claims description 5
- 238000000265 homogenisation Methods 0.000 claims description 5
- 239000010985 leather Substances 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 3
- 239000006104 solid solution Substances 0.000 claims description 3
- 238000002844 melting Methods 0.000 claims 1
- 230000008018 melting Effects 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 7
- 238000012545 processing Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C25/00—Profiling tools for metal extruding
- B21C25/02—Dies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/002—Extruding materials of special alloys so far as the composition of the alloy requires or permits special extruding methods of sequences
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
- B21C23/04—Making uncoated products by direct extrusion
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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Abstract
The invention discloses an extrusion method of a 7150 alloy profile, relates to the technical field of aluminum alloy extrusion material processing, and particularly relates to an extrusion method of a 7150 alloy profile. The invention aims to solve the technical problem that the performance index of the existing 7150 alloy section bar cannot meet the AMS4345 standard requirement. The method comprises the following steps: heating the 7150 alloy cast ingot in an induction furnace, putting the heated alloy cast ingot into an extruder, extruding the heated alloy cast ingot by using an extrusion die, carrying out solution treatment, then carrying out water quenching, and then carrying out three-stage aging treatment on the section to finish the process. The 7150 alloy section prepared by the invention meets the AMS4345 standard requirements on the uniformity of extrusion structure performance, the overall dimension and the performance indexes, and the performance statistic CV value of different wall thickness positions is less than or equal to 3 percent. The method is used for preparing the 7150 alloy profile.
Description
Technical Field
The invention relates to the technical field of aluminum alloy extrusion material processing, in particular to an extrusion method of a 7150 alloy profile.
Background
The 7150-T77511 extruded section has excellent comprehensive properties such as high strength, good toughness and corrosion resistance, can be widely applied to large and medium-sized airplanes (such as C919, ARJ21 and the like) and certain types of military airplanes as key structural materials such as airplane wing stringers, keel beams and the like, can be widely applied to various types of aircrafts as a fourth-generation aluminum alloy material abroad, has a tendency of further expanding application, and has good market application prospect and great social significance.
The 7150-T77511 extruded section is limited by the monopoly of foreign technology, the 7150-T77511 extruded section is always purchased in American aluminum in China, and in order to break the limit of the foreign rapid development of the aerospace industry in China, the 7150-T77511 alloy extruded section meeting the AMS4345 standard is urgently and independently developed, and meanwhile, the statistical CV value of the performance is less than or equal to 3%.
Disclosure of Invention
The invention provides an extrusion method of a 7150 alloy section, aiming at solving the technical problem that the performance index of the existing 7150 alloy section cannot meet the AMS4345 standard requirement.
An extrusion method of 7150 alloy profiles is completed according to the following steps:
firstly, heating a 7150 alloy ingot to 465-480 ℃, preserving heat for 24-36 h, carrying out homogenization annealing treatment, air-cooling to room temperature, and then sawing and turning a leather to obtain an ingot to be treated;
and secondly, putting the ingot to be treated obtained in the step one into an induction furnace, heating to 400-430 ℃, putting the ingot into an extruder for extrusion, carrying out solid solution treatment for 50-70 min at the temperature of 460-480 ℃ after extrusion, then carrying out water quenching, and carrying out three-stage aging treatment on the section bar at the temperature of 115-180 ℃ to obtain the 7150 alloy section bar.
Furthermore, an extrusion die adopted in the extrusion in the step two is provided with an extrusion cavity, and the cavity type of the extrusion cavity is gradually reduced along the thickness direction of the extrusion die in a gradient manner.
The 7150 alloy ingot is prepared by a semi-continuous casting method, and the preparation method comprises the following steps:
the alloy is characterized in that the alloy comprises the following components in percentage by mass: 1.9% -2.5%, Mg: 2.0% -2.7%, Zn: 5.9% -6.9%, Zr: 0.10-0.13%, Cr: 0.02-0.04%, Ti: weighing the following raw materials in a ratio of 0.01-0.04% and the balance of Al: putting the aluminum ingot, the cathode copper, the zinc ingot, the aluminum zirconium alloy ingot, the aluminum chromium intermediate alloy ingot and the aluminum titanium wire into a smelting furnace for smelting to obtain aluminum alloy melt;
slagging off the aluminum alloy melt obtained in the step I, controlling the slagging-off temperature to Be 720-760 ℃, then controlling the temperature to Be the smelting temperature, adding Al-Be intermediate alloy and the primary magnesium ingot weighed in the step I, and refining for 10-20 min by adopting argon-chlorine mixed gas;
thirdly, introducing the aluminum alloy melt processed in the second step into a standing furnace, refining for 15-20 min by adopting argon-chlorine mixed gas, then covering with a No. 2 flux, standing, and casting into 7150 alloy cast ingots by adopting a semi-continuous casting mode.
The invention has the beneficial effects that:
1. the extrusion method of the 7150 alloy profile is combined with the characteristics of the 7150 alloy, and a special extrusion die is designed for profile extrusion, and the extrusion die is designed to perform gradient deformation for many times and increase the structural uniformity of each section position of the profile, so that the performance uniformity is improved, the problem of non-uniform structural performance of the profile with complex section and different wall thicknesses is solved, and the statistical CV value of the performance of each position with different wall thicknesses of a final product is ensured to be less than or equal to 3%.
2. The 150 alloy section prepared by the invention has the characteristics of high strength, high corrosion resistance and the like, and repeated examination and verification prove that the 7150 alloy section meets the requirements of AMS4345 standard on the uniformity of extrusion structure performance, the overall dimension and the performance index, and the CV value of performance statistics is less than or equal to 3%, meets the airworthiness certification requirement of large passenger plane materials, obtains an engineering material approval certificate issued by a commercial and aviation company, can be widely applied to the aerospace field of China, achieves the purposes of replacing imports and realizing the urgent need of guarantee.
The method is used for preparing the 7150 alloy profile.
Drawings
FIG. 1 is a front view of a die during extrusion in an extruder according to one embodiment;
FIG. 2 is a schematic diagram of a die cavity of a die during extrusion by an extruder according to an embodiment;
FIG. 3 is a photograph of a die during extrusion in an extruder according to one embodiment;
fig. 4 is a photograph of alloy section 7150 obtained 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 provides an extrusion method of a 7150 alloy profile, which comprises the following steps:
firstly, heating a 7150 alloy ingot to 465-480 ℃, preserving heat for 24-36 h, carrying out homogenization annealing treatment, air-cooling to room temperature, and then sawing and turning a leather to obtain an ingot to be treated;
and secondly, putting the ingot to be treated obtained in the step one into an induction furnace, heating to 400-430 ℃, putting the ingot into an extruder for extrusion, carrying out solid solution treatment for 50-70 min at the temperature of 460-480 ℃ after extrusion, then carrying out water quenching, and carrying out three-stage aging treatment on the section bar at the temperature of 115-180 ℃ to obtain the 7150 alloy section bar.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: and in the second step, the ingot to be treated is placed into an induction furnace, heated to 415-420 ℃ and then placed into an extruder. 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: and in the second step, the extrusion speed is controlled to be less than or equal to 0.4 mm/s. 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: and step two, an extrusion die adopted for extrusion is provided with an extrusion cavity, and the cavity type of the extrusion cavity is gradually reduced along the thickness direction of the extrusion die. 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: step one, the 7150 alloy ingot is prepared by a semi-continuous casting method, and the preparation method comprises the following steps:
the alloy is characterized in that the alloy comprises the following components in percentage by mass: 1.9% -2.5%, Mg: 2.0% -2.7%, Zn: 5.9% -6.9%, Zr: 0.10-0.13%, Cr: 0.02-0.04%, Ti: weighing the following raw materials in a ratio of 0.01-0.04% and the balance of Al: putting the aluminum ingot, the cathode copper, the zinc ingot, the aluminum zirconium alloy ingot, the aluminum chromium intermediate alloy ingot and the aluminum titanium wire into a smelting furnace for smelting to obtain aluminum alloy melt;
slagging off the aluminum alloy melt obtained in the step I, controlling the slagging-off temperature to Be 720-760 ℃, then controlling the temperature to Be the smelting temperature, adding Al-Be intermediate alloy and the primary magnesium ingot weighed in the step I, and refining for 10-20 min by adopting argon-chlorine mixed gas;
thirdly, introducing the aluminum alloy melt processed in the second step into a standing furnace, refining for 15-20 min by adopting argon-chlorine mixed gas, then covering with a No. 2 flux, standing, and casting into 7150 alloy cast ingots by adopting a semi-continuous casting mode. 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: the method comprises the following steps of: 2.2%, Mg: 2.1%, Zn: 6.4%, Zr: 0.12%, Cr: 0.03%, Ti: weighing raw materials according to the proportion of 0.03 percent and the balance of Al. 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: the method comprises the following steps of: 2.1%, Mg: 2.2%, Zn: 6.3%, Zr: 0.12%, Cr: 0.04%, Ti: weighing raw materials according to the proportion of 0.02 percent and the balance of Al. 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: step two, the smelting temperature is 750 ℃. 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 step two, the adding amount of the Al-Be intermediate alloy is 0.02 to 0.04 percent of the mass of the aluminum alloy melt. 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 step three, controlling the standing time to be 30-150 min. 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 extrusion die that adopts in the embodiment is opened has the extrusion chamber, and the extrusion chamber reduces the chamber type step by step along extrusion die's thickness direction gradient, and the extrusion chamber comprises first horizontal chamber 1, vertical seam chamber 2 and the horizontal chamber 3I-shaped of second, and the length an of first horizontal chamber 1 is 16mm, and the width b of first horizontal chamber 1 is 6mm, and the length of vertical seam chamber 2 is 18mm, and the width of vertical seam chamber 2 is 3mm, and the length c of the horizontal chamber 3 of second is 16 mm.
The first embodiment is as follows:
the present embodiment is a method for extruding 7150 alloy profile, which comprises the following steps:
firstly, according to the mass percentage of elements as Cu: 2.1%, Mg: 2.2%, Zn: 6.3%, Zr: 00.12%, Cr: 0.04%, Ti: weighing the following raw materials in proportion of 0.02 percent and the balance of Al: putting the aluminum ingot, the cathode copper, the zinc ingot, the aluminum zirconium alloy ingot, the aluminum chromium intermediate alloy ingot and the aluminum titanium wire into a smelting furnace for smelting to obtain aluminum alloy melt;
secondly, slagging off the aluminum alloy melt obtained in the first step, controlling the slagging-off temperature to Be 752 ℃, then controlling the temperature to Be a smelting temperature, adding Al-Be intermediate alloy and the primary magnesium ingot weighed in the first step, and refining for 18min by adopting argon-chlorine mixed gas; the adding amount of the Al-Be intermediate alloy is 0.03 percent of the mass of the aluminum alloy melt;
thirdly, introducing the aluminum alloy melt processed in the second step into a standing furnace, refining for 16min by adopting argon-chlorine mixed gas, covering with a No. 2 flux, standing for 120min, and casting into 7150 alloy ingot by adopting a semi-continuous casting mode, wherein the specification of the 7150 alloy ingot is phi 124mm round ingot;
fourthly, heating the 7150 alloy ingot to 470 ℃, preserving heat for 30 hours, carrying out homogenization annealing treatment, cooling in air to room temperature, and then sawing and cutting a leather to obtain an ingot to be treated; the size of the ingot to be treated is phi 120mm multiplied by 300 mm;
fifthly, putting the ingot to be treated obtained in the fourth step into an induction furnace, heating to 420 ℃, putting the ingot into an extruder for extrusion, carrying out solution treatment for 60min at the temperature of 479 ℃ after extrusion, then carrying out water quenching, carrying out primary and tertiary aging treatment on the section bar at the temperature of 115-125 ℃ in a 24-meter aging furnace, and carrying out secondary aging treatment on the section bar at the temperature of 170-180 ℃ in a 24-meter roller-hearth quenching furnace to obtain the 7150 alloy section bar.
The 7150 alloy section obtained in the embodiment is tested, the tensile strength is 612-635 MPa, the yield strength is 586-608 MPa, the elongation percentage range is 7.4-12.2%, and the performance statistic CV value is as follows: 1.57 percent.
Example two:
the present embodiment is a method for extruding 7150 alloy profile, which comprises the following steps:
firstly, according to the mass percentage of elements as Cu: 2.1%, Mg: 2.2%, Zn: 6.3%, Zr: 00.12%, Cr: 0.04%, Ti: weighing the following raw materials in proportion of 0.02 percent and the balance of Al: putting the aluminum ingot, the cathode copper, the zinc ingot, the aluminum zirconium alloy ingot, the aluminum chromium intermediate alloy ingot and the aluminum titanium wire into a smelting furnace for smelting to obtain aluminum alloy melt;
secondly, slagging off the aluminum alloy melt obtained in the first step, controlling the slagging-off temperature to Be 752 ℃, then controlling the temperature to Be a smelting temperature, adding Al-Be intermediate alloy and the primary magnesium ingot weighed in the first step, and refining for 18min by adopting argon-chlorine mixed gas; the adding amount of the Al-Be intermediate alloy is 0.03 percent of the mass of the aluminum alloy melt;
thirdly, introducing the aluminum alloy melt processed in the second step into a standing furnace, refining for 16min by adopting argon-chlorine mixed gas, covering with a No. 2 flux, standing for 120min, and casting into 7150 alloy ingot by adopting a semi-continuous casting mode, wherein the specification of the 7150 alloy ingot is phi 124mm round ingot;
fourthly, heating the 7150 alloy ingot to 470 ℃, preserving heat for 30 hours, carrying out homogenization annealing treatment, cooling in air to room temperature, and then sawing and cutting a leather to obtain an ingot to be treated; the size of the ingot to be treated is phi 120mm multiplied by 300 mm;
fifthly, putting the ingot to be treated obtained in the fourth step into an induction furnace, heating to 430 ℃, putting the ingot into a 1100-ton extruding machine for extrusion, controlling the extrusion ratio to be 39.8, the temperature of an extruding cylinder to be 450 ℃ and the extrusion speed to be 0.3mm/s for forward extrusion, carrying out solution treatment for 66min at the temperature of 475 ℃ after extrusion, then carrying out water quenching, carrying out primary and tertiary aging treatment on the section bar at the temperature of 115-125 ℃ in a 24-meter aging furnace, and carrying out secondary aging treatment on the section bar at the temperature of 170-180 ℃ in a 24-meter roller hearth quenching furnace to obtain the 7150 alloy section bar.
Through tests, the tensile strength of the 7150 alloy section obtained in the embodiment is 615-640 MPa, the yield strength is 576-606 MPa, the elongation percentage range is 7.2-12.5%, and the performance statistic CV value is as follows: 1.64%, more ordinary flat die extrusion section bar, the statistics of performance CV value: 2.17%, the performance stability is greatly improved.
The beneficial effects of the embodiment:
1. the invention relates to an extrusion method of a 7150 alloy profile, which combines the characteristics of 7150 alloy and designs a special extrusion die for profile extrusion, wherein the extrusion die is provided with an extrusion cavity, the extrusion cavity gradually reduces the cavity along the thickness direction of the extrusion die in a gradient manner, the extrusion die designs multiple gradient deformation and increases the tissue uniformity of each section position of the profile, thereby improving the uniformity of performance, solving the problem of non-uniform tissue performance of the profile with complex section and different wall thicknesses, and ensuring that the statistical CV value of the performance of each section with different wall thicknesses of a final product is less than or equal to 3%.
2. The extrusion method of the 7150 alloy profile prepared by the invention has the characteristics of high strength, high corrosion resistance and the like, and after repeated examination and verification, the requirement of AMS4345 standard is met, the CV value of performance statistics is less than or equal to 3%, the airworthiness certification requirement of large passenger plane materials is met, an engineering material approval certificate issued by a commercial airliner company is obtained, the extrusion method can be widely applied to the aerospace field of China, the import is replaced, and the purpose of ensuring urgent need is realized.
Claims (10)
1. The extrusion method of the 7150 alloy profile is characterized by comprising the following steps of:
firstly, heating a 7150 alloy ingot to 465-480 ℃, preserving heat for 24-36 h, carrying out homogenization annealing treatment, air-cooling to room temperature, and then sawing and turning a leather to obtain an ingot to be treated;
and secondly, putting the ingot to be treated obtained in the step one into an induction furnace, heating to 400-430 ℃, putting the ingot into an extruder for extrusion, carrying out solid solution treatment for 50-70 min at the temperature of 460-480 ℃ after extrusion, then carrying out water quenching, and carrying out three-stage aging treatment on the section bar at the temperature of 115-180 ℃ to obtain the 7150 alloy section bar.
2. The extrusion method of a 7150 alloy profile according to claim 1, wherein in the second step, the ingot to be treated is placed in an induction furnace, heated to 415-420 ℃ and then placed in an extruder.
3. The extrusion method of 7150 alloy profile according to claim 1, wherein in the second step, the extrusion speed is controlled to be less than or equal to 0.4 mm/s.
4. The extrusion method of a 7150 alloy profile according to claim 1, wherein an extrusion die used in the extrusion in the second step is provided with an extrusion cavity, and the extrusion cavity gradually reduces the cavity shape along the thickness direction of the extrusion die.
5. The extrusion method of a 7150 alloy profile according to claim 1, wherein in the step one, said 7150 alloy ingot is prepared by a semi-continuous casting method, and the preparation method comprises the following steps:
the alloy is characterized in that the alloy comprises the following components in percentage by mass: 1.9% -2.5%, Mg: 2.0% -2.7%, Zn: 5.9% -6.9%, Zr: 0.10-0.13%, Cr: 0.02-0.04%, Ti: weighing the following raw materials in a ratio of 0.01-0.04% and the balance of Al: putting the aluminum ingot, the cathode copper, the zinc ingot, the aluminum zirconium alloy ingot, the aluminum chromium intermediate alloy ingot and the aluminum titanium wire into a smelting furnace for smelting to obtain aluminum alloy melt;
slagging off the aluminum alloy melt obtained in the step I, controlling the slagging-off temperature to Be 720-760 ℃, then controlling the temperature to Be the smelting temperature, adding Al-Be intermediate alloy and the primary magnesium ingot weighed in the step I, and refining for 10-20 min by adopting argon-chlorine mixed gas;
thirdly, introducing the aluminum alloy melt processed in the second step into a standing furnace, refining for 15-20 min by adopting argon-chlorine mixed gas, then covering with a No. 2 flux, standing, and casting into 7150 alloy cast ingots by adopting a semi-continuous casting mode.
6. The extrusion method of 7150 alloy profiles as recited in claim 5, wherein in step (r) the weight percentage of elements is Cu: 2.2%, Mg: 2.1%, Zn: 6.4%, Zr: 0.12%, Cr: 0.03%, Ti: weighing raw materials according to the proportion of 0.03 percent and the balance of Al.
7. The extrusion method of 7150 alloy profiles as recited in claim 5, wherein in step (r) the weight percentage of elements is Cu: 2.1%, Mg: 2.2%, Zn: 6.3%, Zr: 0.12%, Cr: 0.04%, Ti: weighing raw materials according to the proportion of 0.02 percent and the balance of Al.
8. The extrusion method of 7150 alloy profile according to claim 5, wherein said melting temperature is 750 ℃.
9. The extrusion method of 7150 alloy profile according to claim 5, wherein the amount of Al-Be master alloy added in the second step is 0.02-0.04% of the mass of the molten aluminum alloy.
10. The extrusion method of 7150 alloy profiles as recited in claim 5, wherein the standing time is controlled to be 30-150 min.
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| CN112792150B CN112792150B (en) | 2023-04-07 |
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| CN115161523A (en) * | 2022-06-30 | 2022-10-11 | 苏州浪潮智能科技有限公司 | Aluminum alloy section for radiator and preparation method thereof |
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Cited By (2)
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|---|---|---|---|---|
| CN115161523A (en) * | 2022-06-30 | 2022-10-11 | 苏州浪潮智能科技有限公司 | Aluminum alloy section for radiator and preparation method thereof |
| CN115161523B (en) * | 2022-06-30 | 2023-01-20 | 苏州浪潮智能科技有限公司 | Aluminum alloy section for radiator and preparation method thereof |
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