CN118006981A - High-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and preparation method thereof - Google Patents
High-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and preparation method thereof Download PDFInfo
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 139
- 239000000956 alloy Substances 0.000 title claims abstract description 139
- 229910017982 Ag—Si Inorganic materials 0.000 title claims abstract description 27
- 238000002360 preparation method Methods 0.000 title abstract description 15
- 239000012535 impurity Substances 0.000 claims abstract description 4
- 239000000126 substance Substances 0.000 claims abstract description 4
- 230000032683 aging Effects 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 17
- 238000000137 annealing Methods 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 16
- 238000004321 preservation Methods 0.000 claims description 16
- 238000010791 quenching Methods 0.000 claims description 16
- 230000000171 quenching effect Effects 0.000 claims description 16
- 229910000838 Al alloy Inorganic materials 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 10
- 238000005097 cold rolling Methods 0.000 claims description 8
- 238000005098 hot rolling Methods 0.000 claims description 7
- 238000001192 hot extrusion Methods 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 238000005242 forging Methods 0.000 claims description 3
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- 229910052802 copper Inorganic materials 0.000 abstract description 5
- 229910052709 silver Inorganic materials 0.000 abstract description 3
- 229910052725 zinc Inorganic materials 0.000 abstract description 2
- 229910052804 chromium Inorganic materials 0.000 abstract 1
- 229910052742 iron Inorganic materials 0.000 abstract 1
- 229910052748 manganese Inorganic materials 0.000 abstract 1
- 229910052726 zirconium Inorganic materials 0.000 abstract 1
- 239000000243 solution Substances 0.000 description 16
- 230000000694 effects Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 238000005728 strengthening Methods 0.000 description 5
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- 239000002184 metal Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
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- 229910019015 Mg-Ag Inorganic materials 0.000 description 2
- 229910017706 MgZn Inorganic materials 0.000 description 2
- 238000003723 Smelting Methods 0.000 description 2
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- 229910016943 AlZn Inorganic materials 0.000 description 1
- 229910018569 Al—Zn—Mg—Cu Inorganic materials 0.000 description 1
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- 229910052691 Erbium Inorganic materials 0.000 description 1
- 229910019064 Mg-Si Inorganic materials 0.000 description 1
- 229910019406 Mg—Si Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009749 continuous casting Methods 0.000 description 1
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/06—Alloys based on aluminium with magnesium 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
- 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
- C22C21/00—Alloys based on aluminium
- C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
- C22C21/08—Alloys based on aluminium with magnesium 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
- 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
- C22F1/047—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 magnesium as the next major constituent
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Abstract
The invention provides a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and a preparation method thereof, wherein the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy comprises the following chemical components in percentage by mass: 4.0 to 7.0 percent of Mg, 1.0 to 5.0 percent of Zn, less than or equal to 1.5 percent of Cu, less than or equal to 0.5 percent of Ag, less than or equal to 0.4 percent of Si, less than or equal to 0.4 percent of Fe, less than or equal to 0.3 percent of Zr, less than or equal to 0.2 percent of Cr, less than or equal to 0.2 percent of Mn, less than or equal to 0.2 percent of Ti, and the balance of Al and unavoidable impurities.
Description
[ Field of technology ]
The invention relates to the technical field of nonferrous metal preparation, in particular to a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and a preparation method thereof.
[ Background Art ]
Aluminum alloy is widely applied to important parts such as aircraft skins, stringers, skeletons and the like as an important material for light aircraft, and along with the increasing of the navigational speed of civil and military aircraft, stricter requirements are put on the strength and the high-temperature thermal stability of the component materials.
The 7XXX (Al-Zn-Mg-Cu) series alloy belongs to the category of heat treatable strengthening alloys, which are widely used as fuselage materials due to their high specific strength, one of the most representative alloys being 7075 alloy. The main strengthening phase is eta-MgZn 2. The 7075 alloy can exhibit excellent strength at room temperature by aging to a T6 state. The patent CN113913656B effectively solves the problems of coarse and uneven structure, lower mechanical property, poorer consistency, poorer stress corrosion sensitivity and quenching sensitivity and the like of the conventional continuous casting 7075 alloy by adding Er, gd and Ge elements into the 7075 alloy. However, when the aircraft speed reaches around mach 2, the skin temperature can reach 160-190 ℃ due to the intense friction between the fuselage and the air, and the local skin temperature can even reach 200 ℃. At this time, coarsening of eta' phase will result in significant reduction of alloy strength, severely affecting aircraft safety.
2XXX (Al-Cu-Mg) based alloys also fall into the category of heat treatable strengthening alloys, such as 2219, 2519 and 2618, which are commonly used for various parts of aircraft due to their good high temperature stability, however, with the continued increase in aircraft speed, new challenges are presented to the room temperature and high temperature mechanical properties of these alloys. Patent CN2007100348528.X, CN200710192544.2 and CN2007100360721.1 disclose that rare earth elements are adopted for microalloying treatment, as-cast Al-Cu-Mg-Ag crystal grains are thinned, hot extrusion and solid solution aging treatment are carried out, the aging precipitation process of the alloy is improved, and the heat resistance of the alloy is improved, but the crystal grains of the alloy are still larger after hot extrusion deformation, so that the improvement of the mechanical property of the alloy is limited. CN101245430a discloses an Al-Cu-Mg-Ag alloy with high Ag/Mg mass ratio, more Ag precipitates more Ω phases in the alloy, so that the room temperature and high temperature mechanical properties of the alloy are improved, however, the application range is severely limited due to high production cost.
Therefore, the novel alloy with excellent room temperature mechanical property and high temperature stability is developed, and the novel alloy has become a new strategic target in various material fields such as aerospace and the like at present.
Accordingly, there is a need to develop a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and a method for preparing the same to address the deficiencies of the prior art, to solve or alleviate one or more of the problems described above.
[ Invention ]
Aiming at the problem that the room temperature/high temperature mechanical properties of the 2XXX series and 7XXX series aluminum alloy in the field of aerospace materials are poor in matching property, the invention provides a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and a preparation method thereof.
On one hand, the invention provides a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, which comprises the following chemical components in percentage by mass: 4.0 to 7.0 portions of Mg, 1.0 to 5.0 portions of Zn, less than or equal to 1.5 portions of Cu, less than or equal to 0.5 portions of Ag, less than or equal to 0.4 portions of Si, less than or equal to 0.4 portions of Fe, less than or equal to 0.3 portions of Zr, less than or equal to 0.2 portions of Cr, less than or equal to 0.2 portions of Mn, less than or equal to 0.2 portions of Ti, and the balance of Al and unavoidable impurities.
In the aspects and any possible implementation manner described above, there is further provided an implementation manner, wherein the mass ratio of the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy satisfies (zn+cu+ag+si)/Mg is less than or equal to 1.0.
In accordance with aspects and any possible implementation manner of the foregoing, there is further provided a method for preparing a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, for preparing the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, the method comprising the steps of:
S1: pre-configuring an original alloy, and carrying out homogenizing annealing treatment on the original alloy to obtain an alloy in a homogenized state;
s2: carrying out heat deformation treatment on the homogenized alloy to obtain the alloy in a heat deformation state;
s3: performing intermediate annealing treatment on the alloy in the thermal deformation state to obtain the alloy in the intermediate annealing state;
s4: cold rolling the intermediate annealed alloy to obtain a cold rolled alloy;
s5: carrying out solution quenching treatment on the cold-rolled alloy to obtain a solution quenched alloy;
s6: prestretching the solution quenched alloy to obtain a prestretched alloy;
S7: and (3) carrying out aging treatment on the pre-stretched alloy to obtain the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy.
In the aspect and any possible implementation manner as described above, there is further provided an implementation manner, where the original alloy preconfigured in S1 is an aluminum alloy ingot.
In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the homogenizing annealing treatment in S1 is specifically: placing the aluminum alloy ingot into a heat treatment furnace at the temperature of less than or equal to 500 ℃ for heat preservation for less than or equal to 30 hours, and heating/cooling the aluminum alloy ingot along with the furnace to obtain the homogenized alloy.
In aspects and any one of the possible implementations described above, there is further provided an implementation in which the heat deformation treatment in S2 is required to be a heat deformation temperature of 400 ℃ or higher, a heat deformation amount of 50% or higher, the heat deformation treatment including but not limited to hot rolling, hot forging, and hot extrusion; the total deformation of the S4 cold rolling is required to be 0-90%.
In the aspect and any possible implementation manner as described above, there is further provided an implementation manner, in S3, a temperature of the intermediate annealing is set to: the heat preservation time is 300-400 ℃, and the heat preservation time is as follows: and 0-120 min.
In the aspect and any possible implementation manner as described above, there is further provided an implementation manner, where solution hardening in S5 is specifically: and (3) placing the cold-rolled alloy in an air furnace with the temperature less than or equal to 500 ℃ for 0-60 min, then heating to 400-550 ℃ and preserving the heat for 0-60 min, and finally performing water quenching to obtain the solution quenching alloy.
In the aspect and any possible implementation manner as described above, there is further provided an implementation manner, where the pre-stretching process in S6 is specifically: and pre-stretching the solution quenched alloy by 0-5% to obtain the pre-stretched alloy.
In the aspect and any possible implementation manner as described above, further provided is an implementation manner, where the aging treatment in S7 is specifically: the prestretched alloy is placed in an aging furnace at 70-120 ℃ for heat preservation for 0-50 h, and then placed in a heat treatment furnace at 120-180 ℃ for heat preservation for 0-30 h.
Compared with the prior art, the invention can obtain the following technical effects:
1. The Al-Mg-Zn-Cu-Ag-Si alloy prepared by the process has excellent room temperature and high temperature mechanical properties, and provides great application potential for various material fields such as aerospace and the like;
2. The Al-Mg-Zn-Cu-Ag-Si alloy prepared by the process can reach 600MPa of room temperature yield strength and 360MPa of high temperature tensile yield strength at 200 ℃.
Of course, it is not necessary for any of the products embodying the invention to achieve all of the technical effects described above at the same time.
[ Description of the drawings ]
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of the preparation of a high strength heat resistant Al-Mg-Zn-Cu-Ag-Si alloy according to one embodiment of the present invention.
[ Detailed description ] of the invention
For a better understanding of the technical solution of the present invention, the following detailed description of the embodiments of the present invention refers to the accompanying drawings.
It should be understood that the described embodiments are merely some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The invention provides a high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, which comprises the following chemical components in percentage by mass: 4.0 to 7.0 portions of Mg, 1.0 to 5.0 portions of Zn, less than or equal to 1.5 portions of Cu, less than or equal to 0.5 portions of Ag, less than or equal to 0.4 portions of Si, less than or equal to 0.4 portions of Fe, less than or equal to 0.3 portions of Zr, less than or equal to 0.2 portions of Cr, less than or equal to 0.2 portions of Mn, less than or equal to 0.2 portions of Ti, and the balance of Al and unavoidable impurities. The mass ratio of the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy satisfies (Zn+Cu+Ag+Si)/Mg not more than 1.0.
As shown in FIG. 1, the invention also provides a preparation method of the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, which is used for preparing the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy, and comprises the following steps:
S1: pre-configuring an original alloy, and carrying out homogenizing annealing treatment on the original alloy to obtain an alloy in a homogenized state;
s2: carrying out heat deformation treatment on the homogenized alloy to obtain the alloy in a heat deformation state;
s3: performing intermediate annealing treatment on the alloy in the thermal deformation state to obtain the alloy in the intermediate annealing state;
s4: cold rolling the intermediate annealed alloy to obtain a cold rolled alloy;
s5: carrying out solution quenching treatment on the cold-rolled alloy to obtain a solution quenched alloy;
s6: prestretching the solution quenched alloy to obtain a prestretched alloy;
S7: and (3) carrying out aging treatment on the pre-stretched alloy to obtain the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy.
The original alloy preconfigured in the step S1 is an aluminum alloy cast ingot.
The homogenizing annealing treatment in the step S1 specifically comprises the following steps: placing the aluminum alloy ingot into a heat treatment furnace at the temperature of less than or equal to 500 ℃ for heat preservation for less than or equal to 30 hours, and heating/cooling the aluminum alloy ingot along with the furnace to obtain the homogenized alloy.
The thermal deformation treatment in S2 is required to be that the thermal deformation temperature is more than or equal to 400 ℃, the thermal deformation amount is more than or equal to 50%, and the thermal deformation treatment comprises but is not limited to hot rolling, hot forging and hot extrusion.
The total deformation of the S4 cold rolling is required to be 0-90%.
In S3, the temperature of the intermediate annealing is set as follows: the heat preservation time is 300-400 ℃, and the heat preservation time is as follows: and 0-120 min.
The solution hardening in S5 specifically comprises the following steps: and (3) placing the cold-rolled alloy in an air furnace with the temperature less than or equal to 500 ℃ for 0-60 min, then heating to 400-550 ℃ and preserving the heat for 0-60 min, and finally performing water quenching to obtain the solution quenching alloy.
The pre-stretching treatment in the step S6 specifically comprises the following steps: and pre-stretching the solution quenched alloy by 0-5% to obtain the pre-stretched alloy.
The aging treatment in the step S7 specifically comprises the following steps: the prestretched alloy is placed in an aging furnace at 70-120 ℃ for heat preservation for 0-50 h, and then placed in a heat treatment furnace at 120-180 ℃ for heat preservation for 0-30 h.
In the present invention, the main strengthening phase of the alloy prepared by steps S1 to S7 is T-Mg32 (AlZn) 49 phase, and alloying elements such as Cu, ag and Si are added in addition to the basic alloying elements Mg and Zn. The alloy is placed in the temperature of 70-120 ℃ for 0-50h in S7, cu participates in the formation of Mg-Zn clusters in the early aging process, so that the preferential nucleation of an S-Al 2 CuMg phase is inhibited, the increase of the number density of GP zones (T-phase precursors) is promoted, and the aging response behavior of the alloy is more remarkable; compared with Cu, ag has higher binding energy and can capture more quenching vacancies, so that more T-phase nucleation sites are formed, ag has stronger binding property with other solute atoms, and the effect of inhibiting growth of the T phase can be achieved in the aging process. And a proper amount of Si is added into the alloy, so that a large amount of Mg in the alloy is in an excessive state, and according to the size difference effect, the Mg and the Si are preferentially combined so as to relieve the strain caused by Mg-Si clusters and matrix coherence, and the dual-phase strengthening of a T phase and a beta phase is more beneficial to improving the aging response behavior of the alloy. The microalloying method has remarkable effect in improving the room temperature mechanical property of the alloy.
In addition, electrons between atoms of eta-MgZn 2 phases mainly exist in a metal bond mode, and electrons between atoms of T-Mg 32(AlZnX)49 exist in a partial covalent bond mode besides the metal bond mode, so that compared with eta phases, the cohesive energy of the T phases is lower, the cohesive energy of the T phases is also high, the structural stability of the T phases is high, and Cu and Ag also participate in the formation of the T phases, and the high bonding energy of the Cu and Ag enables the structural stability of the T phases to be higher, so that the high-temperature mechanical property of the alloy is better.
Examples 1-4 and comparative examples 1-2:
The following six sets of experiments were conducted for comparison to verify the product characteristics of the present invention, including examples 1-4 and comparative examples 1-2.
Table 1 laboratory preparation of alloy compositions
Comparative example 1# to example 4#: smelting and casting according to the alloy compositions shown in table 1; placing the cast ingot into a heat treatment furnace, raising the temperature from room temperature to 470 ℃ at a speed of 30 ℃/h, preserving heat for 24 hours, cooling to room temperature along with the furnace, and homogenizing; the hot rolling start temperature is 430 ℃, the thickness of the rolled plate is 6mm, and the hot rolling is finished; intermediate annealing at 375 deg.c, maintaining for 75min and air cooling; cold rolling the sheet material to 1mm, and finishing the cold rolling; placing the cold-rolled sheet in an air furnace at 470 ℃, preserving the temperature for 30min, and then performing water quenching to finish solution quenching; placing the quenched plate in a heat treatment furnace at 90 ℃, preserving heat for 48 hours, air-cooling, then placing in an air furnace at 140 ℃, preserving heat for 26 hours, air-cooling, and finishing ageing. The laboratory prepared alloy has room temperature mechanical property test results shown in Table 2, 200 ℃ heat exposure test results shown in Table 3, and 200 ℃ high temperature instantaneous tensile test results shown in Table 4.
Table 2 laboratory results of room temperature mechanical properties test of the prepared alloys
Table 3 laboratory prepared alloys 200 ℃ heat exposure test results
Table 4 laboratory preparation of the results of the 200 ℃ instantaneous high temperature tensile test of the alloy
As can be seen from table 3, the inventive alloy has more excellent mechanical properties at room temperature than the comparative alloy, and in addition, the inventive alloy exhibits very excellent mechanical properties in a high temperature environment in combination with tables 4 and 5.
Table 5 industrial preparation of alloy compositions
Example 5#: smelting and casting according to alloy compositions in table 2; placing the cast ingot into a heat treatment furnace, raising the temperature from room temperature to 465 ℃ at a speed of 30 ℃/h, preserving heat for 24 hours, cooling to room temperature along with the furnace, and homogenizing; the hot rolling start temperature is 410 ℃, the thickness of the rolled plate is 20mm, and the hot rolling is finished; placing the hot rolled plate in an air furnace at 465 ℃ for heat preservation for 30min, and then performing water quenching and solution quenching to finish; pre-stretching the quenched plate by 2% to eliminate quenching residual stress; placing the quenched plate in a heat treatment furnace at 90 ℃, preserving heat for 24 hours, air-cooling, then placing in an air furnace at 140 ℃, preserving heat for 24 hours, air-cooling, and finishing ageing. The results of the room temperature mechanical property test and 200 ℃ heat exposure test of the industrial preparation alloy are shown in Table 6 and Table 7 respectively, and the results of the 200 ℃ high temperature instantaneous tensile test are shown in Table 8.
TABLE 6 results of mechanical Properties test of industrially prepared alloys at room temperature
TABLE 7 Industrial preparation of alloys 200 ℃ Heat Exposure test results
TABLE 8 Industrial preparation of alloys 200 ℃ instantaneous high temperature tensile test results
As can be seen from tables 6, 7 and 8, the industrially produced alloy also has excellent mechanical properties at room temperature and at high temperature, which means that the inventive alloy already has mature industrial production conditions.
In summary, with respect to the 2XXX and 7XXX aluminum alloys that are currently predominant in the aerospace material field, alloys such as 2219 and 2618 have room temperature yield strengths of about 400MPa and 200 ℃ high temperature tensile yield strengths of about 300MPa, while 7075 alloys have room temperature yield strengths of about 500MPa and 200 ℃ high temperature tensile yield strengths of about 100MPa. Compared with the alloys, the invention provides the Al-Mg-Zn-Cu-Ag-Si alloy with excellent high temperature and high temperature mechanical properties, the room temperature yield strength can reach 600MPa, the high temperature tensile yield strength at 200 ℃ can reach 360MPa, and the alloy provides great application potential for the field of aerospace materials.
The high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy and the preparation method thereof provided by the embodiment of the application are described in detail. The above description of embodiments is only for aiding in the understanding of the method of the present application and its core ideas; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present application, the present description should not be construed as limiting the present application in view of the above.
Certain terms are used throughout the description and claims to refer to particular components. Those of skill in the art will appreciate that a hardware manufacturer may refer to the same component by different names. The description and claims do not take the form of an element differentiated by name, but rather by functionality. As referred to throughout the specification and claims, the terms "comprising," including, "and" includes "are intended to be interpreted as" including/comprising, but not limited to. By "substantially" is meant that within an acceptable error range, a person skilled in the art is able to solve the technical problem within a certain error range, substantially achieving the technical effect. The description hereinafter sets forth a preferred embodiment for practicing the application, but is not intended to limit the scope of the application, as the description is given for the purpose of illustrating the general principles of the application. The scope of the application is defined by the appended claims.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a product or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such product or system. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a commodity or system comprising such elements.
It should be understood that the term "and/or" as used herein is merely one relationship describing the association of the associated objects, meaning that there may be three relationships, e.g., a and/or B, may represent: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.
While the foregoing description illustrates and describes the preferred embodiments of the present application, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the inventive concept as expressed herein, either as a result of the foregoing teachings or as a result of the knowledge or technology of the relevant art. And that modifications and variations which do not depart from the spirit and scope of the application are intended to be within the scope of the appended claims.
Claims (10)
1. The high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy is characterized by comprising the following chemical components in percentage by mass: 4.0 to 7.0 portions of Mg, 1.0 to 5.0 portions of Zn, less than or equal to 1.5 portions of Cu, less than or equal to 0.5 portions of Ag, less than or equal to 0.4 portions of Si, less than or equal to 0.4 portions of Fe, less than or equal to 0.3 portions of Zr, less than or equal to 0.2 portions of Cr, less than or equal to 0.2 portions of Mn, less than or equal to 0.2 portions of Ti, and the balance of Al and unavoidable impurities.
2. The high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy according to claim 1, wherein the mass ratio of the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy satisfies (Zn+Cu+Ag+Si)/Mg is not more than 1.0.
3. A method for preparing a high strength heat resistant Al-Mg-Zn-Cu-Ag-Si alloy according to any one of claims 1-2, characterized in that the method comprises the steps of:
S1: pre-configuring an original alloy, and carrying out homogenizing annealing treatment on the original alloy to obtain an alloy in a homogenized state;
s2: carrying out heat deformation treatment on the homogenized alloy to obtain the alloy in a heat deformation state;
s3: performing intermediate annealing treatment on the alloy in the thermal deformation state to obtain the alloy in the intermediate annealing state;
s4: cold rolling the intermediate annealed alloy to obtain a cold rolled alloy;
s5: carrying out solution quenching treatment on the cold-rolled alloy to obtain a solution quenched alloy;
s6: prestretching the solution quenched alloy to obtain a prestretched alloy;
S7: and (3) carrying out aging treatment on the pre-stretched alloy to obtain the high-strength heat-resistant Al-Mg-Zn-Cu-Ag-Si alloy.
4. The method according to claim 3, wherein the pre-configured master alloy in S1 is an aluminum alloy ingot.
5. The method according to claim 4, wherein the homogenizing annealing treatment in S1 is specifically: placing the aluminum alloy ingot into a heat treatment furnace at the temperature of less than or equal to 500 ℃ for heat preservation for less than or equal to 30 hours, and heating/cooling the aluminum alloy ingot along with the furnace to obtain the homogenized alloy.
6. The method according to claim 3, wherein the heat deformation treatment in S2 is required to have a heat deformation temperature of 400 ℃ or higher and a heat deformation amount of 50% or higher, and the heat deformation treatment includes but is not limited to hot rolling, hot forging and hot extrusion; the total deformation of the S4 cold rolling is required to be 0-90%.
7. A production method according to claim 3, wherein in S3, the temperature of the intermediate annealing is set to: the heat preservation time is 300-400 ℃, and the heat preservation time is as follows: and 0-120 min.
8. The method according to claim 3, wherein the solution hardening in S5 is specifically: and (3) placing the cold-rolled alloy in an air furnace with the temperature less than or equal to 500 ℃ for 0-60 min, then heating to 400-550 ℃ and preserving the heat for 0-60 min, and finally performing water quenching to obtain the solution quenching alloy.
9. The method according to claim 3, wherein the pre-stretching treatment in S6 is specifically: and pre-stretching the solution quenched alloy by 0-5% to obtain the pre-stretched alloy.
10. The method according to claim 3, wherein the aging treatment in S7 is specifically: the prestretched alloy is placed in an aging furnace at 70-120 ℃ for heat preservation for 0-50 h, and then placed in a heat treatment furnace at 120-180 ℃ for heat preservation for 0-30 h.
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