CN102319757B - Preparation method of magnesium alloy variable-section cylindrical member by composite extrusion deformation - Google Patents
Preparation method of magnesium alloy variable-section cylindrical member by composite extrusion deformation Download PDFInfo
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- CN102319757B CN102319757B CN2011102399578A CN201110239957A CN102319757B CN 102319757 B CN102319757 B CN 102319757B CN 2011102399578 A CN2011102399578 A CN 2011102399578A CN 201110239957 A CN201110239957 A CN 201110239957A CN 102319757 B CN102319757 B CN 102319757B
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- 229910000861 Mg alloy Inorganic materials 0.000 title claims abstract description 92
- 238000001125 extrusion Methods 0.000 title claims abstract description 74
- 238000002360 preparation method Methods 0.000 title claims abstract description 14
- 239000002131 composite material Substances 0.000 title claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 150000001875 compounds Chemical class 0.000 claims description 30
- 238000012545 processing Methods 0.000 claims description 21
- 230000003044 adaptive effect Effects 0.000 claims description 9
- 239000000463 material Substances 0.000 abstract description 22
- 238000000034 method Methods 0.000 abstract description 19
- 238000001192 hot extrusion Methods 0.000 abstract description 14
- 238000000265 homogenisation Methods 0.000 abstract 1
- 239000000956 alloy Substances 0.000 description 7
- 239000013078 crystal Substances 0.000 description 7
- 229910000838 Al alloy Inorganic materials 0.000 description 5
- 238000004458 analytical method Methods 0.000 description 5
- 238000010835 comparative analysis Methods 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 5
- 238000005070 sampling Methods 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000011343 solid material Substances 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 238000003825 pressing Methods 0.000 description 2
- 238000007670 refining Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000004580 weight loss Effects 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
A preparation method of a magnesium alloy variable-section cylindrical member by composite extrusion deformation is characterized in that the method comprises the following steps: firstly, orderly performing homogenization pretreatment and hot extrusion deformation of an AZ80 magnesium alloy blank; preparing a variable-section cylindrical force-bearing member by forward and backward composite extrusion; finally performing turning and heat treatment to obtain a magnesium alloy variable-section cylindrical member. Compared with the prior art, the invention has the following advantages that the invention can prepare large-size cylindrical members; the material grain is fine; the mechanical properties are high; and the procedures are simple.
Description
Technical field
The present invention relates to a kind of preparation method of magnesium alloy variable-section cylindrical.This magnesium alloy variable-section cylindrical is mainly used on aircraft as bearing member.
Background technology
Aircraft weight has direct impact to performances such as payload capability, flying speed, flight maneuvers, and the lightweight of structural member can increase the combination properties such as payload capability, quickening flying speed, raising mobility.Therefore, the lightweight of Flight Vehicle Structure spare is the emphasis of aircraft development all the time, and light material and forming technique thereof realize light-weighted key.While adopting aluminium alloy to prepare Flight Vehicle Structure spare, with steel, compare and can reach 20～25% weight loss effect.But, along with the requirement that the aircraft combination property further improves, be badly in need of the more excellent light material of lightweight effect.
Magnesium and alloy thereof are the lightest present structural metallic materials, compare with aluminium alloy, have lower density (density only have aluminium alloy 2/3), higher specific strength and specific stiffness, adopt magnesium alloy substitution of Al alloy to prepare the aircraft bearing member, can realize 20～25% weight loss effect, thereby improve the combination property of aircraft.
As shown in Figure 1, the bearing member of aircraft is the variable cross-section Cylinder shape constructional element, and size is larger, the design of many places variable cross-section, complex structure.Can prepare moulding by following several modes at present:
The first, adopt casting method, the method to be easy to be shaped, but cast magnesium alloy exist coarse grains, mechanical property poor, easily produce the shortcoming such as defect, can't meet the mechanical property requirements of aircraft bearing member;
The second, Equal-channel Angular Pressing method (ECAP) is Refining Mg Alloy crystal grain significantly, but there is obvious texture tendency in the material of preparation;
The third, rolling can prepare the material of even tissue performance excellence, but only is suitable for preparing sheet material.
The 4th kind, by plastic processing method such as extruding, forging, rolling etc. can the Refining Mg Alloy tissue, improve its mechanical property.Similarly technical literature can referenced patent number (publication number is CN1827829A for the Chinese invention patent of ZL200610041960.8 " the continuous variable cross section cycle extrusion prepares the device and method of grained material ", Granted publication number is CN100386466C), this patent alternately repeatedly carries out obtaining the accumulation strain amount by crimp and Upsetting to be made material structure obtain refinement to improve performance, and the required operation of the method is various and the technological requirement condition is higher.It can also application reference number be 201010032431.8 Chinese invention patent application " device and method of preparing fine-grained material by directly extruding continuous variable cross section " (publication No. is CN101767120A), this patent adopts the mode of classification transition to prepare the continuous variable cross section solid material, only limit to the solid material preparation, and also need to remove the closure of the port of export in preparation process, complex procedures, efficiency are low., although above-mentioned pressing method to a certain extent can thinning microstructure and improved material property, only limit to the material preparation, and, due to technique self, be confined to prepare at present solid material more.How to suitability for industrialized production, to make the transition,, for the preparation of the large scale variable-section cylindrical, need some general character underlying issues are further probed into.
Summary of the invention
Technical problem to be solved by this invention is that the For The Deformation of Combined Extrusion preparation method of the magnesium alloy variable-section cylindrical that a kind of material grains is tiny, mechanical property is high is provided in addition for the above-mentioned state of the art.
Another technical problem to be solved by this invention is that the For The Deformation of Combined Extrusion preparation method of the simple magnesium alloy variable-section cylindrical of a kind of operation is provided for the above-mentioned state of the art.
The present invention solves the problems of the technologies described above the technical scheme that adopts: a kind of For The Deformation of Combined Extrusion preparation method of magnesium alloy variable-section cylindrical is characterized in that comprising the steps:
At first, adopt AZ80 magnesium alloy blank, successively by homogenising pretreatment and hot extrusion deformation; Prepare variable cross-section tubular bearing member through positive and negative Compound Extrusion again; Heat-treat after last turning, obtain magnesium alloy variable-section cylindrical.
As preferably, described homogenising pretreatment temperature is 380～420 ℃, and the processing time is 10～18h.
As preferably, described hot extrusion deformation meets following condition: magnesium alloy blank preheat temperature is 330～380 ℃, and the hot-extrusion mold temperature is 180～230 ℃, and extrusion speed is 0.5～3mm/s, and obtaining diameter is the magnesium alloy rod of 145～175mm.
As preferably, described positive and negative Compound Extrusion meets following condition: the blank preheat temperature is 280～330 ℃, and the composite extrusion die temperature is 200～260 ℃, and extrusion speed is 3～5mm/s, obtains magnesium alloy variable-section tubular bearing member.
Further, described composite extrusion die comprises Compound Extrusion core and the workbench of Compound Extrusion drift, Compound Extrusion die, middle part projection, aforesaid Compound Extrusion drift is over against Compound Extrusion die port and have the variable cross-section projection adaptive with the magnesium alloy variable-section cylindrical internal diameter, and this variable cross-section projection comprises columnar portion and is positioned at the tapering of columnar portion front end; Aforesaid Compound Extrusion die is located on workbench and is had the variable cross-section internal diameter adaptive with the magnesium alloy variable-section cylindrical external diameter; Aforesaid Compound Extrusion core is positioned at the bottom of Compound Extrusion die and has the protuberance adaptive with the magnesium alloy variable-section cylindrical lower port.
Described heat treatment temperature is 170～180 ℃, and the processing time is 12h～24h, is cooled to room temperature after processing in air, obtains magnesium alloy variable-section cylindrical.
Compared with prior art, the invention has the advantages that:
1). by pretreatment and heat engine tool extruding predeformation, acquisition crystal grain is tiny, the AZ80 magnesium alloy of even tissue, for follow-up positive and negative For The Deformation of Combined Extrusion provides the blank assurance;
2). adopt positive and negative compound extrusion forming, solved the plastic forming technology problem of large scale variable-section cylindrical, realized simultaneously effective combination of deformation strengthening and near-net-shape, wherein forward extrusion realizes the deformation strengthening of magnesium alloy materials, reverse extrusion is realized the near-net-shape of variable-section cylindrical, and stock utilization is higher;
3). warm compound extrusion forming during the present invention adopts, forming temperature is lower, overcome the problem of magnesium alloy grain growth under high temperature, the dislocation that has reduced simultaneously microstructure merges and the driving force of integrating, greatly improved the entanglement degree of distortion dislocation, make the deformation strengthening effect be better than conventional hot extrusion, for finally preparing intensity, over the high-strength magnesium alloy bearing member more than 330MPa, established technical foundation;
4). the technology of the present invention can obviously improve the mechanical property of AZ80 magnesium alloy tubular bearing member, and co-occurrence is compared with the aluminium alloy bearing member, and reducing weight can reach more than 20%.
Description of drawings
Fig. 1 is the cross-sectional view of variable cross-section tubular bearing member in prior art.
Fig. 2 is structural representation during hot extrusion deformation in embodiment.
Fig. 3 is For The Deformation of Combined Extrusion original state structural representation.
Fig. 4 is that in For The Deformation of Combined Extrusion, the descending rear blank of Compound Extrusion drift is filled structural representation behind the variable cross-section extrusion die shape chamber of sealing fully.
Fig. 5 is the metallograph of the microscopic structure of gained magnesium alloy variable-section cylindrical in embodiment 1.
The specific embodiment
Embodiment is described in further detail the present invention below in conjunction with accompanying drawing.
Embodiment 1:
Determine magnesium alloy materials.According to the instructions for use of high-speed aircraft bearing member, by performance and cost comparative analysis, Analysis of Chemical Compatibility, the AZ80 magnesium alloy that selection intensity is high, corrosion resistance is better, material cost is moderate is as manufactured materials;
1. the magnesium alloy blank is carried out the homogenising pretreatment.Treatment temperature is 410 ℃, and the processing time is 8h;
Magnesium alloy blank 31 after 1. step is processed is carried out heat engine tool extruding predeformation.Magnesium alloy blank preheat temperature is 340 ℃, the hot-extrusion mold temperature is 200 ℃, and extrusion speed is 3mm/s, and obtaining diameter is the magnesium alloy rod of 150mm, as shown in Figure 2, hot-extrusion mold comprises extruding punching head 11, hot extrusion die 21, the new film 41 of hot extrusion and workbench 51;
To through step 2. the magnesium alloy blank 31 after predeformation cut, obtain predeformation blank 3-1, the predeformation charge length is 220mm;
predeformation blank after 3. step processes is carried out positive and negative For The Deformation of Combined Extrusion, predeformation blank 3-1 preheat temperature is 300 ℃, the composite extrusion die temperature is 200 ℃, extrusion speed is 4.5mm/s, obtain magnesium alloy variable-section tubular bearing member 3-2, see Fig. 3 and shown in Figure 4, composite extrusion die comprises Compound Extrusion drift 21, Compound Extrusion die 22, Compound Extrusion core 23 and workbench 25, Compound Extrusion drift 21 is over against Compound Extrusion die 22 ports and have the variable cross-section projection 211 adaptive with the magnesium alloy variable-section cylindrical internal diameter, this variable cross-section projection 211 comprises columnar portion and is positioned at the tapering of columnar portion front end, Compound Extrusion die 22 is located on workbench and is had the variable cross-section internal diameter adaptive with the magnesium alloy variable-section cylindrical external diameter, Compound Extrusion core 23 is positioned at the bottom of Compound Extrusion die 22 and has the protuberance 231 adaptive with the magnesium alloy variable-section cylindrical lower port.
To carrying out subsequent heat treatment after the magnesium alloy variable-section tubular bearing member 3-2 turning after 4. step is processed, treatment temperature is 177 ℃, and the processing time is 12h, be cooled to room temperature after processing in air, member crystal grain is tiny, sees accompanying drawing 5, obtains finally magnesium alloy variable-section cylindrical 3-3.
This embodiment products obtained therefrom carries out sampling and testing:
Embodiment 2:
Determine magnesium alloy materials.According to the instructions for use of high-speed aircraft bearing member, by performance and cost comparative analysis, Analysis of Chemical Compatibility, the AZ80 magnesium alloy that selection intensity is high, corrosion resistance is better, material cost is moderate is as manufactured materials;
1. the magnesium alloy blank is carried out the homogenising pretreatment.Treatment temperature is 400 ℃, and the processing time is 12h;
Magnesium alloy after 1. step is processed is carried out heat engine tool extruding predeformation.Magnesium alloy blank preheat temperature is 360 ℃, and the hot-extrusion mold temperature is 200 ℃, and extrusion speed is 3mm/s, and obtaining diameter is the magnesium alloy rod of 160mm;
To through step 2. the magnesium alloy after predeformation carry out machined, obtain the predeformation blank.The predeformation billet size calculates according to size and the following process surplus of bearing member;
Predeformation blank after 3. step processes is carried out For The Deformation of Combined Extrusion,, the blank preheat temperature is 320 ℃, and the composite extrusion die temperature is 200 ℃, and extrusion speed is 4.5mm/s, obtains the tiny magnesium alloy tubular bearing member of crystal grain;
To carrying out subsequent heat treatment after the magnesium alloy tubular bearing member turning after 4. step is processed.Treatment temperature is 177 ℃, and the processing time is 16h, is cooled to room temperature after processing in air, obtains finally magnesium alloy variable-section cylindrical.
This embodiment products obtained therefrom carries out sampling and testing:
Embodiment 3:
Determine magnesium alloy materials.According to the instructions for use of high-speed aircraft bearing member, by performance and cost comparative analysis, Analysis of Chemical Compatibility, the AZ80 magnesium alloy that selection intensity is high, corrosion resistance is better, material cost is moderate is as manufactured materials;
1. the magnesium alloy blank is carried out the homogenising pretreatment.Treatment temperature is 400 ℃, and the processing time is 12h;
Magnesium alloy after 1. step is processed is carried out heat engine tool extruding predeformation.Magnesium alloy blank preheat temperature is 380 ℃, and the hot-extrusion mold temperature is 220 ℃, and extruding depression bar speed is 3mm/s, and obtaining diameter is the magnesium alloy rod of 170mm;
To through step 2. the magnesium alloy after predeformation carry out machined, obtain the predeformation blank.The predeformation billet size calculates according to size and the following process surplus of bearing member;
Predeformation blank after 3. step processes is carried out For The Deformation of Combined Extrusion.The blank preheat temperature is 330 ℃, and the composite extrusion die temperature is 220 ℃, and extrusion speed is 5mm/s, obtains the tiny magnesium alloy tubular bearing member of crystal grain;
To carrying out subsequent heat treatment after the magnesium alloy tubular bearing member turning after 4. step is processed.Treatment temperature is 175 ℃, and the processing time is 18h, is cooled to room temperature after processing in air, obtains finally magnesium alloy variable-section cylindrical.
This embodiment products obtained therefrom carries out sampling and testing:
Embodiment 4:
Determine magnesium alloy materials.According to the instructions for use of high-speed aircraft bearing member, by performance and cost comparative analysis, Analysis of Chemical Compatibility, the AZ80 magnesium alloy that selection intensity is high, corrosion resistance is better, material cost is moderate is as manufactured materials;
The magnesium alloy blank is carried out the homogenising pretreatment.Treatment temperature is 390 ℃, and the processing time is 16h;
Magnesium alloy after 1. step is processed is carried out heat engine tool extruding predeformation, and magnesium alloy blank preheat temperature is 330 ℃, and the hot-extrusion mold temperature is 220 ℃, and extrusion speed is 0.8mm/s, and obtaining diameter is the magnesium alloy rod of 150mm;
To through step 2. the magnesium alloy after predeformation carry out machined, obtain the predeformation blank.The predeformation billet size calculates according to size and the following process surplus of bearing member;
Predeformation blank after 3. step processes is carried out For The Deformation of Combined Extrusion.The blank preheat temperature is 330 ℃, and the composite extrusion die temperature is 250 ℃, and extrusion speed is 3mm/s, obtains the tiny magnesium alloy tubular bearing member of crystal grain;
To carrying out subsequent heat treatment after the magnesium alloy tubular bearing member turning after 4. step is processed.Treatment temperature is 170 ℃, and the processing time is 24h, is cooled to room temperature after processing in air, obtains finally magnesium alloy variable-section cylindrical.
This embodiment products obtained therefrom carries out sampling and testing:
Embodiment 5:
Determine magnesium alloy materials.According to the instructions for use of high-speed aircraft bearing member, by performance and cost comparative analysis, Analysis of Chemical Compatibility, the AZ80 magnesium alloy that selection intensity is high, corrosion resistance is better, material cost is moderate is as manufactured materials;
1. the magnesium alloy blank is carried out the homogenising pretreatment.Treatment temperature is 390 ℃, and the processing time is 16h;
Magnesium alloy after 1. step is processed is carried out heat engine tool extruding predeformation.Magnesium alloy blank preheat temperature is 360 ℃, and the hot-extrusion mold temperature is 220 ℃, and extrusion speed is 3mm/s, and obtaining diameter is the magnesium alloy rod of 150mm;
To through step 2. the magnesium alloy after predeformation carry out machined, obtain the predeformation blank.The predeformation billet size calculates according to size and the following process surplus of bearing member;
Predeformation blank after 3. step processes is carried out For The Deformation of Combined Extrusion.The blank preheat temperature is 330 ℃, and the composite extrusion die temperature is 220 ℃, and extrusion speed is 5mm/s, obtains the tiny magnesium alloy tubular bearing member of crystal grain;
To carrying out subsequent heat treatment after the magnesium alloy tubular bearing member turning after 4. step is processed.Treatment temperature is 180 ℃, and the processing time is 12h, is cooled to room temperature after processing in air, obtains finally magnesium alloy variable-section cylindrical.
This embodiment products obtained therefrom carries out sampling and testing:
Claims (2)
1. the For The Deformation of Combined Extrusion preparation method of a magnesium alloy variable-section cylindrical is characterized in that in turn including the following steps:
1. AZ80 magnesium alloy blank is carried out the homogenising pretreatment, treatment temperature is 380～420 ℃, and the processing time is 10～18h;
2. the pretreated magnesium alloy of homogenising is carried out heat engine tool extruding predeformation, magnesium alloy blank preheat temperature is 330～380 ℃, and the extrusion die temperature is 180～230 ℃, and extrusion speed is 0.5～3mm/s, and obtaining diameter is the magnesium alloy rod of 145～175mm;
3. the magnesium alloy rod after predeformation is cut, obtain the predeformation blank;
4. the predeformation blank is carried out positive and negative compound extrusion forming, predeformation blank preheat temperature is 280～330 ℃, and the composite extrusion die temperature is 200～260 ℃, and extrusion speed is 3～5mm/s, obtains magnesium alloy variable-section tubular bearing member;
5. to carrying out subsequent heat treatment after the turning of magnesium alloy variable-section tubular bearing member, treatment temperature is 170～180 ℃, and the processing time is 12h～24h, is cooled to room temperature after processing in air, obtains magnesium alloy variable-section cylindrical.
2. preparation method according to claim 1, it is characterized in that described composite extrusion die comprises Compound Extrusion core and the workbench of Compound Extrusion drift, Compound Extrusion die, middle part projection, aforesaid Compound Extrusion drift is over against Compound Extrusion die port and have the variable cross-section projection adaptive with the magnesium alloy variable-section cylindrical internal diameter, and this variable cross-section projection comprises columnar portion and is positioned at the tapering of columnar portion front end; Aforesaid Compound Extrusion die is located on workbench and is had the variable cross-section internal diameter adaptive with the magnesium alloy variable-section cylindrical external diameter; Aforesaid Compound Extrusion core is positioned at the bottom of Compound Extrusion die and has the protuberance adaptive with the magnesium alloy variable-section cylindrical lower port.
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