CN116689767A - Manufacturing method of high-strength aluminum alloy material for aerospace - Google Patents
Manufacturing method of high-strength aluminum alloy material for aerospace Download PDFInfo
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- CN116689767A CN116689767A CN202310482869.3A CN202310482869A CN116689767A CN 116689767 A CN116689767 A CN 116689767A CN 202310482869 A CN202310482869 A CN 202310482869A CN 116689767 A CN116689767 A CN 116689767A
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 128
- 239000000956 alloy Substances 0.000 title claims abstract description 56
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 27
- 239000000203 mixture Substances 0.000 claims abstract description 103
- 238000005245 sintering Methods 0.000 claims abstract description 49
- 239000002131 composite material Substances 0.000 claims abstract description 36
- 230000008859 change Effects 0.000 claims abstract description 31
- 239000000463 material Substances 0.000 claims abstract description 24
- 239000011248 coating agent Substances 0.000 claims abstract description 21
- 238000000576 coating method Methods 0.000 claims abstract description 21
- 229910052751 metal Inorganic materials 0.000 claims abstract description 14
- 239000002184 metal Substances 0.000 claims abstract description 14
- 230000007704 transition Effects 0.000 claims abstract description 12
- 239000011247 coating layer Substances 0.000 claims abstract description 11
- 239000003795 chemical substances by application Substances 0.000 claims description 28
- 238000005488 sandblasting Methods 0.000 claims description 25
- 229910018072 Al 2 O 3 Inorganic materials 0.000 claims description 16
- 239000000155 melt Substances 0.000 claims description 16
- 239000010410 layer Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 14
- 239000012298 atmosphere Substances 0.000 claims description 12
- 238000005266 casting Methods 0.000 claims description 12
- 238000002844 melting Methods 0.000 claims description 10
- 230000008018 melting Effects 0.000 claims description 10
- 239000000843 powder Substances 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 8
- 229910052725 zinc Inorganic materials 0.000 claims description 8
- 229910052749 magnesium Inorganic materials 0.000 claims description 7
- 238000002156 mixing Methods 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 3
- 229910001297 Zn alloy Inorganic materials 0.000 claims description 2
- 238000003825 pressing Methods 0.000 claims 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 abstract description 46
- 239000011162 core material Substances 0.000 abstract description 24
- 229910052742 iron Inorganic materials 0.000 abstract description 20
- 229910045601 alloy Inorganic materials 0.000 abstract description 13
- 238000004663 powder metallurgy Methods 0.000 abstract description 5
- 239000013078 crystal Substances 0.000 abstract description 4
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 abstract description 4
- 239000011701 zinc Substances 0.000 description 24
- 239000011777 magnesium Substances 0.000 description 20
- 239000011572 manganese Substances 0.000 description 12
- 238000004321 preservation Methods 0.000 description 12
- 238000003723 Smelting Methods 0.000 description 9
- 239000002245 particle Substances 0.000 description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 8
- 238000005253 cladding Methods 0.000 description 8
- 239000007789 gas Substances 0.000 description 8
- 238000005121 nitriding Methods 0.000 description 8
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 6
- 239000007788 liquid Substances 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 5
- 238000005255 carburizing Methods 0.000 description 5
- 230000000052 comparative effect Effects 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 239000011882 ultra-fine particle Substances 0.000 description 4
- 239000011800 void material Substances 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 239000010949 copper Substances 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 238000010998 test method Methods 0.000 description 3
- 229910019589 Cr—Fe Inorganic materials 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 239000012300 argon atmosphere Substances 0.000 description 2
- 238000009835 boiling Methods 0.000 description 2
- 239000003610 charcoal Substances 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 229910052748 manganese Inorganic materials 0.000 description 2
- 238000005272 metallurgy Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910001199 N alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
- 229910052718 tin Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/1003—Use of special medium during sintering, e.g. sintering aid
- B22F3/1007—Atmosphere
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/1039—Sintering only by reaction
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
-
- 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
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/002—Ferrous alloys, e.g. steel alloys containing In, Mg, or other elements not provided for in one single group C22C38/001 - C22C38/60
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/38—Ferrous alloys, e.g. steel alloys containing chromium with more than 1.5% by weight of manganese
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacturing & Machinery (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Composite Materials (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention relates to the technical field of aluminum alloy manufacturing, in particular to a manufacturing method of a high-strength aluminum alloy material for aerospace; comprises a mixture which is configured to undergo phase transition at high temperature; coating the mixture outside the aluminum alloy billet, and pressurizing to form a mixture coating layer to obtain a composite billet; sintering the obtained composite blank; the core material and the coating material of the aluminum alloy material are prepared in a segmented mode, the surface strength and the hardness of the aluminum alloy material can be effectively improved through the iron-based alloy structure outside the aluminum alloy blank, meanwhile, the iron-based material can be attached to the aluminum alloy core material in a powder metallurgy mode, then, on the one hand, the mixture can be sintered and phase-converted at high temperature through high-temperature sintering, and gaps and capillary structures are formed on the iron-based alloy through crystal form change of aluminum oxide or dissipation of low-boiling-point metal, and at the moment, the aluminum alloy of the core material can enter the gaps and the capillary structures so that the combination between the core material and the iron base is tighter.
Description
Technical Field
The invention relates to the technical field of aluminum alloy manufacturing, in particular to a manufacturing method of a high-strength aluminum alloy material for aerospace.
Background
The aluminum alloy is an alloy based on aluminum and added with a certain amount of other alloying elements, and is one of light metal materials. In addition to having the general characteristics of aluminum, aluminum alloys have specific characteristics of some alloys due to the variety and amount of alloying elements added. The density of the aluminum alloy is 2.63-2.85 g/cm < 3 >, the strength (sigma b is 110-650 MPa), the specific strength is close to that of high alloy steel, the specific rigidity is higher than that of steel, the casting performance and the plastic workability are good, the electric conductivity and the heat conductivity are good, the corrosion resistance and the weldability are good, the aluminum alloy can be used as structural materials, and the aluminum alloy has wide application in aerospace, aviation, transportation, construction, electromechanics, lightening and daily necessities.
With the rapid development of aerospace industry in China, more severe requirements are put forward on basic materials. The cross section size of the extrusion profile is required to be increased, the fixed-size length is required to be lengthened, and meanwhile, the performance of the extrusion profile is required to be matched with higher strength and toughness.
The tensile strength, toughness and surface hardness of the existing aluminum alloy section are difficult to be simultaneously considered. In order to improve the performances of the aluminum alloy material at the same time, the prior art adopts surface treatment processes such as carburization and the like to solve the problems, but the strength and the surface hardness of the aluminum alloy are difficult to obtain larger improvement due to the performance limitation of the aluminum alloy, wherein the Chinese patent with publication number CN103243246A discloses a high-quality high-hardness aluminum alloy ingot which comprises the following components in parts by weight: 2.0 to 3.0 percent of Cu; 9.5 to 11.5 percent of Si; mg:0 to 0.1 percent; 0 to 2.9 percent of Zn; 0.6 to 1.0 percent of Fe; mn 0-0.5%; ni:0 to 0.3 percent; 0 to 0.15 percent of Sn; the total of other microelements is 0 to 0.25 percent, and the balance is Al; and further provides a production method of the high-hardness aluminum alloy ingot; the aluminum alloy ingot has the advantages of high strength and hardness and stable mechanical property; the production method of the aluminum alloy ingot has the advantages of low cost, high efficiency, convenience in controlling the quality of the aluminum alloy ingot and the like.
However, this technique only provides a solution for optimizing the process steps and parameters based on the prior art, and does not substantially improve the hardness and strength of the aluminum alloy.
The Chinese patent with publication number of CN106167868A discloses a high-strength high-hardness cast aluminum alloy and a preparation method thereof, and solves the problem that the service life is influenced by easy corrosion and deformation of the existing aluminum alloy material. A high-strength high-hardness cast aluminum alloy consists of the following raw materials in percentage by mass: 8.0 to 15.0wt.% of zinc, 4.0 to 10.0wt.% of silicon, 1.5 to 4.5wt.% of copper, 0.5 to 2.0wt.% of iron, 0.03 to 0.5wt.% of manganese, 0.03 to 0.5wt.% of magnesium, 0.01 to 0.1wt.% of nickel, 0.01 to 0.1wt.% of titanium, and the balance of aluminum and unavoidable impurity elements. The invention effectively eliminates the occurrence of corrosion deformation phenomenon, prolongs the service life and shortens the service life, and can be used for high-strength high-hardness structural members and exterior parts in the fields of aerospace, electronic communication, automobiles, weapons and the like. The technology also improves the manufacture of aluminum alloy, but the hardness of the product obtained in practice is only 110HB at maximum, mainly because of the low hardness of the aluminum-based material, so that the hardness of the aluminum-based material is difficult to be directly improved to the ideal degree in an improved mode.
Disclosure of Invention
The invention aims to provide a manufacturing method of a high-strength aluminum alloy material for aerospace, which solves the following technical problems:
(1) Solves the problem that the strength and the surface hardness of the aluminum alloy are difficult to be greatly improved in the prior art.
The aim of the invention can be achieved by the following technical scheme:
a manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature;
s2, coating the mixture outside the aluminum alloy billet, and pressurizing to form a mixture coating layer to obtain a composite billet;
s3, sintering the composite blank obtained in the step S2 to obtain a presintered piece;
s4, carburizing or nitriding the alloy material obtained in the step S4 to obtain the high-strength aluminum alloy material.
As a further scheme of the invention: the pressurizing process in the step S2 is used for compacting the cladding layer material to form a shell layer cladding the aluminum alloy blank.
As a further scheme of the invention: the phase changeThe agent is beta-Al 2 O 3 、γ-Al 2 O 3 、δ-Al 2 O 3 、η-Al 2 O 3 、ρ-Al 2 O 3 、κ-Al 2 O 3 、θ-Al 2 O 3 、χ-Al 2 O 3 One of Mg or Zn.
As a further scheme of the invention: the mixture comprises the following raw materials in percentage by weight:
0.7-3.0wt% of Mn, 1.1-2.5wt% of Cr, 0.9-2.2wt% of phase change agent and the balance of Fe.
As a further scheme of the invention: the aluminum alloy is Al-Mg-Zn alloy.
As a further scheme of the invention: the aluminum alloy is prepared by smelting 2.2-2.6% of Mg, 9.0-9.7% of Zn and the balance of Al.
As a further scheme of the invention: and step S3, sintering the material and simultaneously performing carburizing or nitriding treatment to obtain the high-strength aluminum alloy material.
As a further scheme of the invention: the aluminum alloy blank in the step S2 is prepared by the following steps:
p1. Mixing and melting 2.2-2.6wt% of Mg, 9.0-9.7wt% of Zn, 0.1-1.9wt% of Cu, 0.2-0.45wt% of Mn and the balance of Al to obtain a melt, and pouring the melt into a die at 670-700 ℃;
p2, placing the casting obtained in the step P1 at 450-500 ℃ for sand blasting treatment, wherein sand blasting materials used for sand blasting are the mixture prepared in the step S1;
and P3, cooling the casting obtained by the P2 to room temperature along with a furnace after sand blasting is completed, and obtaining an aluminum alloy blank.
As a further scheme of the invention: the mixture in the step S1 is prepared by the following steps: and (3) melting the mixture under inert atmosphere, atomizing the melt, and cooling atomized metal to obtain mixture powder.
The invention has the beneficial effects that:
according to the invention, the core material and the coating material of the aluminum alloy material are prepared in sections, the surface strength and the hardness of the aluminum alloy material can be effectively improved by arranging the iron-based alloy structure outside the aluminum alloy blank, meanwhile, the iron-based material can be attached to the aluminum alloy core material in a powder metallurgy mode, and then, on one hand, the mixture can be sintered and phase-converted at high temperature by high-temperature sintering, for example, the void and the capillary structure can be generated on the iron-based alloy by the crystal form change of aluminum oxide or the dissipation of low-boiling-point metal, and at the moment, the aluminum alloy of the core material can enter the void and the capillary structure so that the combination between the core material and the iron base is tighter, and meanwhile, the effect of bridging microscopic defects generated by the phase conversion can be also achieved due to the sintering effect of the iron-based material;
the strength and hardness of the surface of the aluminum alloy can be improved by carburizing or nitriding the aluminum alloy material during sintering, and meanwhile, the carburization or nitriding depth can be obviously improved due to the capillary structure caused by phase transition, so that the surface strength of the aluminum alloy material can be further enhanced.
When Mg or Zn is adopted as the phase-change agent, the mixture is melted in an inert atmosphere, the Mg and Zn with low boiling points can enter the atmosphere before other components, then the other components enter the atmosphere through ultrasonic atomization and are cooled together with the Mg or Zn to form alloy particles, so that the uniformity of the components of the mixture can be effectively improved, meanwhile, the phase-change agent in the formed alloy particles is mostly positioned at the outer side or shallow layer of the small liquid drops due to the fact that the Mg or Zn is boiled and the other components are atomized to obtain small liquid drops, and the phase-change agent is positioned at gaps among particles of the mixture after pressurization, so that a capillary structure is easier to form, and carburization/nitrogen and aluminum alloy inner cores are conveniently combined with the mixture.
Description of the embodiments
The following description of the technical solutions in the embodiments of the present invention will be clear and complete, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments. 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.
In the invention, a light high-toughness aluminum alloy material is mainly used as a core material, and a hard iron-based alloy is used for forming a shell coated outside the core material in a powder metallurgy mode, wherein the thickness of the core material and the shell depends on the practical application requirement, the shell needs to be considered to form a denser shell besides the performance requirement, and the leakage of a core material melt at high temperature is avoided, so that certain requirements are imposed on the thickness and the pressure in a forming stage.
Examples
The invention relates to a manufacturing method of a high-strength aluminum alloy material for aerospace, which comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 3.0wt% of Mn, 1.1wt% of Cr, 2.2wt% of phase change agent and the balance of Fe, and the phase change agent is beta-Al with the particle size of 100-200nm 2 O 3 ；
S2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 2.5mm, then placing the aluminum alloy blank on the mixture, coating the mixture with a thickness of 2.5mm on the aluminum alloy blank, pressurizing to 150Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.2% of Mg, 9.7% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially increased to 800 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is increased to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
The aluminum alloy blank is prepared by the following steps:
p1, mixing and melting all the components to obtain a melt, and pouring the melt into a mold at 700 ℃;
and P2, carrying out sand blasting treatment on the casting obtained in the step P1 at the temperature of 450 ℃, wherein the sand blasting material used for sand blasting is the mixture prepared in the step S1.
Test example data show that the tensile strength of the embodiment can reach 81.5Mpa, the surface hardness is HV560, the compressive strength is 453.4Mpa, the nitriding depth is 0.9mm, compared with the comparative example 1, the difference in implementation mode is mainly that no phase change agent is added in the comparative example, the nitriding depth of the embodiment is greatly improved under the action of the phase change agent, the sintering and phase change of the mixture can be caused at high temperature through the use of a powder metallurgy process and the phase change agent on the one hand, for example, the crystal form change of aluminum oxide or the dissipation of low-boiling point metal can generate gaps and capillary structures on the iron-based alloy, at the moment, the aluminum alloy of the core material can enter the gaps and the capillary structures to enable the combination between the core material and the iron-based alloy to be more compact, and simultaneously, due to the sintering effect of the iron-based material can also play a role of micro defect generated by the phase change of the phase change, various performance indexes of the embodiment are also improved along with the change of the nitriding depth.
Examples
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 0.7wt% of Mn, 2.5wt% of Cr, 0.9wt% of phase change agent and the balance of Fe, and the phase change agent is Zn powder with the particle size of 40-80 nm;
s2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to form a thickness of 2.0mm, then placing the aluminum alloy blank on the mixture, coating the mixture of 2.0mm on the aluminum alloy blank, pressurizing to 125Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.6% of Mg, 9.0% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially raised to 800 ℃, charcoal serving as a carburizing agent is added into the sintering furnace, the temperature is kept for 60min, the temperature is raised to 1200 ℃, and the temperature is kept for 10h, and then the furnace is cooled.
The aluminum alloy blank is prepared by the following steps:
p1, mixing and melting all the components to obtain a melt, and pouring the melt into a die at 680 ℃;
and P2, placing the casting obtained in the step P1 at 480 ℃ for sand blasting treatment, wherein the sand blasting material used for sand blasting is the mixture prepared in the step S1.
In the embodiment, the tensile strength of the aluminum alloy material can reach 79.9Mpa, the surface hardness is HV590, the compressive strength is 472.1Mpa, the carburization depth is 1.3mm, and the carburization depth is remarkably improved.
Examples
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 1.5wt% of Mn, 2.0wt% of Cr, 1.5wt% of phase change agent and the balance of Fe, and the phase change agent is Mg powder with the particle size of 40-80 nm;
s2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 3.0mm, then placing the aluminum alloy blank on the mixture, coating the mixture of 3.0mm on the aluminum alloy blank, pressurizing to 175Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.4% of Mg, 9.5% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially raised to 900 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is raised to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
The aluminum alloy blank is prepared by the following steps:
p1, mixing and melting all the components to obtain a melt, and pouring the melt into a mold at 670 ℃;
and P2, carrying out sand blasting treatment on the casting obtained in the step P1 at 500 ℃, wherein the sand blasting material used for sand blasting is the mixture prepared in the step S1.
In this embodiment, the tensile strength of the aluminum alloy material can reach 80.5Mpa, the surface hardness is HV610, the compressive strength 491.6Mpa, the carburization depth is 0.9mm, and the carburization depth is substantially equal to that of embodiment 1, which is mainly because the phase change agent adopted in this embodiment is Mg, the Zn volume in the clad layer formed by the mixture is lost at high temperature, and further larger pores are formed in the clad layer, so that the infiltration of the carbon-containing atmosphere is facilitated, but at the same time, because the compression pressure in the process of forming the mixture clad layer is larger, the number of pores and the diameter of the clad layer are reduced, so that the nitriding depth is substantially equal to that in embodiment 1 under integration, but because the compression pressure of the mixture is large, the clad layer is more compact and is combined with the aluminum alloy core material in the subsequent sintering, so that the compressive strength is higher than that in embodiments 1 and 2.
Examples
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 0.7wt% of Mn, 2.5wt% of Cr, 0.9wt% of phase change agent and the balance of Fe, and the phase change agent is Zn powder with the particle size of 40-80 nm;
s2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 1.0mm, then placing the aluminum alloy blank on the mixture, coating the mixture of 1.0mm on the aluminum alloy blank, pressurizing at 125Mpa for 1min, wherein the aluminum alloy is prepared by smelting 2.6% of Mg, 9.0% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially raised to 800 ℃, charcoal serving as a carburizing agent is added into the sintering furnace, the temperature is kept for 60min, the temperature is raised to 1200 ℃, and the temperature is kept for 10h, and then the furnace is cooled.
The aluminum alloy blank in this embodiment is prepared by the following steps:
p1, mixing and melting all the components to obtain a melt, and pouring the melt into a die at 680 ℃;
p2, placing the casting obtained in the step P1 at 480 ℃ for sand blasting treatment, wherein sand blasting materials used for sand blasting are the mixture prepared in the step S1;
and P3, cooling the casting obtained by the P2 to room temperature along with a furnace after sand blasting is completed, and obtaining an aluminum alloy blank.
The mixture of the embodiment is prepared by the following steps: after the mixture is melted in argon atmosphere, the atomized metal is cooled to obtain mixture powder, in the embodiment, molten Mn, cr and Fe metal liquid is sprayed out through gas pushing to form ultrafine particles, meanwhile Zn metal flow is sprayed out oppositely to be cooled in contact with the ultrafine particles to form the mixture, wherein argon is adopted as the atomized gas, the gas spraying rate is 600m/s, and the flow ratio of the gas to the metal liquid is 10:1.
In this embodiment, the tensile strength of the aluminum alloy material can reach 81.6Mpa, the surface hardness is HV600, the compressive strength is 489.6Mpa, the carburization depth is 1.4mm, in this embodiment, because an atomization metallurgy technology is adopted, a mixture taking Mn-Cr-Fe as a core Zn as an appearance is formed, after a cladding layer is formed by pressurization, zn external structures with softer textures are mutually extruded and fused, a denser structure is formed, then, at a high temperature, the Zn structure is lost, gaps inside the cladding layer can be formed, carburization and mixture sintering can be synchronously performed, meanwhile, an aluminum alloy core material can enter the gaps from inside in the process, so that the compactness of the core material and the cladding layer is improved, the volume of the sintered aluminum alloy material is reduced compared with that of the material before sintering, in addition, the carburization depth is obviously improved compared with that of embodiment 2, and the comprehensive performance is improved.
Examples
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 1.5wt% of Mn, 2.0wt% of Cr, 1.5wt% of phase change agent and the balance of Fe, and the phase change agent is Mg powder with the particle size of 40-80 nm;
s2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 2mm, then placing the aluminum alloy blank on the mixture, coating the mixture of 2mm on the aluminum alloy blank, pressurizing to 175Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.4% of Mg, 9.5% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially raised to 900 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is raised to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
The aluminum alloy blank in this embodiment is prepared by the following steps:
p1, mixing and melting all the components to obtain a melt, and pouring the melt into a mold at 670 ℃;
p2, placing the casting obtained in the step P1 at 500 ℃ for sand blasting treatment, wherein sand blasting materials used for sand blasting are the mixture prepared in the step S1;
and P3, cooling the casting obtained by the P2 to room temperature along with a furnace after sand blasting is completed, and obtaining an aluminum alloy blank.
The mixture of the embodiment is prepared by the following steps: after the mixture is melted in argon atmosphere, the atomized metal is cooled to obtain mixture powder, in the embodiment, molten Mn, cr and Fe metal liquid is sprayed out through gas pushing to form ultrafine particles, and meanwhile, mg metal flow is sprayed out oppositely to be in contact with the ultrafine particles to be cooled to form the mixture, wherein argon is adopted as the atomized gas, the gas spraying rate is 600m/s, and the flow ratio of the gas to the metal liquid is 15:1.
In this embodiment, the tensile strength of the aluminum alloy material can reach 82.7Mpa, the surface hardness is HV610, the compressive strength is 521.6Mpa, and the carburization depth is 1.0mm, in this embodiment, because an atomization metallurgy technology is adopted, a mixture taking Mn-Cr-Fe as a core Zn as an appearance is formed, after a cladding layer is formed by pressurization, zn external structures with softer textures are mutually extruded and fused, a denser structure is formed, then a gap inside the cladding layer is formed by losing the Mg structure at a high temperature, carburization and mixture sintering can be synchronously performed, meanwhile, an aluminum alloy core material can enter the gap from inside in the process, so that the compactness of the core material and the cladding layer is improved, the volume of the sintered aluminum alloy material is reduced compared with that of the material before sintering, in addition, in the carburization depth, compared with embodiment 3, the aluminum alloy material is obviously improved, and the comprehensive performance is improved.
Comparative example 1
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 3.0wt% of Mn, 1.1wt% of Cr and the balance of Fe;
s2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 1.5mm, then placing the aluminum alloy blank on the mixture, coating the mixture with a thickness of 1.5mm on the aluminum alloy blank, pressurizing to 150Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.2% of Mg, 9.7% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially increased to 800 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is increased to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
Comparative example 2
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 3.0wt% of Mn, 1.1wt% of Cr, 2.2wt% of phase change agent and the balance of Fe, and the phase change agent is beta-Al with the particle size of 100-200nm 2 O 3 ；
S2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 1.5mm, then placing the aluminum alloy blank on the mixture, coating the mixture with a thickness of 1.5mm on the aluminum alloy blank, pressurizing for 30Mpa and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.2% of Mg, 9.7% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially increased to 800 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is increased to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
Comparative example 3
A manufacturing method of a high-strength aluminum alloy material for aerospace comprises the following steps:
s1, preparing a mixture which is subjected to phase transition at high temperature, wherein the mixture comprises 3.0wt% of Mn, 1.1wt% of Cr, 2.2wt% of phase change agent and the balance of Fe, wherein the phase change agent is particlesbeta-Al with diameter of 100-200nm 2 O 3 ；
S2, coating the mixture outside an aluminum alloy blank, pressurizing to form a mixture coating layer to obtain a composite blank, firstly paving the mixture in a die to obtain a thickness of 1.5mm, then placing the aluminum alloy blank on the mixture, coating the mixture with a thickness of 1.5mm on the aluminum alloy blank, pressurizing to 400Mpa, and maintaining the pressure for 1min, wherein the aluminum alloy is prepared by smelting 2.2% of Mg, 9.7% of Zn and the balance of Al in percentage by mass;
s3, sintering the composite blank obtained in the step S2, wherein in the step, the composite blank is placed in a sintering furnace for sintering, the temperature is initially increased to 800 ℃, ammonia gas atmosphere is introduced into the sintering furnace, the temperature is increased to 1200 ℃ after the heat preservation is carried out for 60min, and the composite blank is cooled along with the furnace after the heat preservation is carried out for 12 h.
Test examples
The surface hardness, tensile strength, compressive strength and carburization/nitrogen depth of the aluminum alloy material are detected, the surface hardness of the detected test piece is measured by a YS/T420-2000 aluminum alloy Webster hardness test method, the tensile strength is measured by a GB/T228-2002 test method, the compressive strength is measured by a GB/T7314-1987 test method, and the carburization/nitrogen depth is obtained by measuring the carburization/nitrogen depth on a cross section perpendicular to the surface of the test piece, and the test results are shown in the following table.
According to the data in the table, the embodiments of the invention are improved to a certain extent in carburization/depth, so that the surface hardness of the invention is improved correspondingly, meanwhile, due to the use of the powder metallurgy process and the phase change agent of the invention, on the one hand, the mixture can be sintered and phase-changed at high temperature through high-temperature sintering, for example, the crystal form change of aluminum oxide or the dissipation of low-boiling-point metal can generate a void and capillary structure on the iron-based alloy, at the moment, the aluminum alloy of the core material can enter the void and capillary structure to enable the combination between the core material and the iron-based alloy to be tighter, and meanwhile, the sintering effect of the iron-based material can also play a role of bridging microscopic defects generated by the phase change, so that the tensile strength and the compressive strength of the invention are also improved remarkably.
The foregoing describes one embodiment of the present invention in detail, but the description is only a preferred embodiment of the present invention and should not be construed as limiting the scope of the invention. All equivalent changes and modifications within the scope of the present invention are intended to be covered by the present invention.
Claims (9)
1. The manufacturing method of the high-strength aluminum alloy material for aerospace is characterized by comprising the following steps of:
s1, preparing a mixture which is subjected to phase transition at high temperature;
s2, coating the mixture outside the aluminum alloy billet, and pressurizing to form a mixture coating layer to obtain a composite billet;
s3, sintering the composite blank obtained in the step S2.
2. The method according to claim 1, wherein the pressing process in step S2 is used to press the clad material to form a shell layer that is clad on the exterior of the aluminum alloy blank.
3. The method for producing a high-strength aluminum alloy material for aerospace according to claim 2, wherein the phase change agent is β -Al 2 O 3 、γ-Al 2 O 3 、δ-Al 2 O 3 、η-Al 2 O 3 、ρ-Al 2 O 3 、κ-Al 2 O 3 、θ-Al 2 O 3 、χ-Al 2 O 3 One of Mg or Zn.
4. The method for manufacturing a high-strength aluminum alloy material for aerospace according to claim 3, wherein the mixture comprises the following raw materials in percentage by weight:
0.7-3.0wt% of Mn, 1.1-2.5wt% of Cr, 0.9-2.2wt% of phase change agent and the balance of Fe.
5. The method for producing a high-strength aluminum alloy material for aerospace according to claim 1, wherein the aluminum alloy is an Al-Mg-Zn alloy.
6. The method for producing a high-strength aluminum alloy material for aerospace according to claim 5, wherein the aluminum alloy is produced by melting 2.2 to 2.6% by mass of mg, 9.0 to 9.7% by mass of zn, and the balance of Al.
7. The method for producing a high-strength aluminum alloy material for aerospace according to claim 1, wherein the step S3 material is carburized or nitrided while being sintered to obtain the high-strength aluminum alloy material.
8. The method for manufacturing a high-strength aluminum alloy material for aerospace according to claim 1, wherein the aluminum alloy blank in step S2 is manufactured by:
p1. Mixing and melting 2.2-2.6wt% of Mg, 9.0-9.7wt% of Zn, 0.1-1.9wt% of Cu, 0.2-0.45wt% of Mn and the balance of Al to obtain a melt, and pouring the melt into a die at 670-700 ℃;
p2, placing the casting obtained in the step P1 at 450-500 ℃ for sand blasting treatment, wherein sand blasting materials used for sand blasting are the mixture prepared in the step S1;
and P3, cooling the casting obtained by the P2 to room temperature along with a furnace after sand blasting is completed, and obtaining an aluminum alloy blank.
9. The method for manufacturing a high-strength aluminum alloy material for aerospace according to claim 1, wherein the mixture in step S1 is prepared by the steps of: and (3) melting the mixture under inert atmosphere, atomizing the melt, and cooling atomized metal to obtain mixture powder.
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| US4154900A (en) * | 1976-05-14 | 1979-05-15 | Taiho Kogyo Co., Ltd. | Composite material of ferrous cladding material and aluminum cast matrix and method for producing the same |
| US20060134447A1 (en) * | 1999-07-09 | 2006-06-22 | Taiho Kogyo Co., Ltd. | Flame-sprayed copper-aluminum composite material and its production method |
| CN112063868A (en) * | 2020-08-27 | 2020-12-11 | 湘潭大学 | Preparation method of oxide dispersion strengthened Al-Mg-Si aluminum alloy |
| CN114293077A (en) * | 2021-12-29 | 2022-04-08 | 北京理工大学 | High-strength aluminum-copper alloy for aerospace structural member and preparation method thereof |
| CN116024447A (en) * | 2022-12-30 | 2023-04-28 | 中国科学院金属研究所 | Preparation method of aluminum alloy material |
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| US4154900A (en) * | 1976-05-14 | 1979-05-15 | Taiho Kogyo Co., Ltd. | Composite material of ferrous cladding material and aluminum cast matrix and method for producing the same |
| US20060134447A1 (en) * | 1999-07-09 | 2006-06-22 | Taiho Kogyo Co., Ltd. | Flame-sprayed copper-aluminum composite material and its production method |
| CN112063868A (en) * | 2020-08-27 | 2020-12-11 | 湘潭大学 | Preparation method of oxide dispersion strengthened Al-Mg-Si aluminum alloy |
| CN114293077A (en) * | 2021-12-29 | 2022-04-08 | 北京理工大学 | High-strength aluminum-copper alloy for aerospace structural member and preparation method thereof |
| CN116024447A (en) * | 2022-12-30 | 2023-04-28 | 中国科学院金属研究所 | Preparation method of aluminum alloy material |
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