CN116652078A - Preparation method of magnesium alloy cabin - Google Patents
Preparation method of magnesium alloy cabin Download PDFInfo
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- CN116652078A CN116652078A CN202310609057.0A CN202310609057A CN116652078A CN 116652078 A CN116652078 A CN 116652078A CN 202310609057 A CN202310609057 A CN 202310609057A CN 116652078 A CN116652078 A CN 116652078A
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- 229910000861 Mg alloy Inorganic materials 0.000 title claims abstract description 25
- 238000002360 preparation method Methods 0.000 title claims abstract description 7
- 238000005242 forging Methods 0.000 claims abstract description 118
- 238000001125 extrusion Methods 0.000 claims abstract description 76
- 238000003825 pressing Methods 0.000 claims abstract description 34
- 238000000034 method Methods 0.000 claims abstract description 26
- 238000000137 annealing Methods 0.000 claims abstract description 24
- 238000010438 heat treatment Methods 0.000 claims abstract description 18
- 230000032683 aging Effects 0.000 claims abstract description 13
- 238000005266 casting Methods 0.000 claims abstract description 13
- 229910001297 Zn alloy Inorganic materials 0.000 claims abstract description 12
- 238000003723 Smelting Methods 0.000 claims abstract description 9
- 238000005520 cutting process Methods 0.000 claims abstract description 9
- 238000003754 machining Methods 0.000 claims abstract description 9
- 230000008569 process Effects 0.000 claims description 21
- 229910045601 alloy Inorganic materials 0.000 claims description 16
- 239000000956 alloy Substances 0.000 claims description 16
- 239000011777 magnesium Substances 0.000 claims description 4
- 239000012535 impurity Substances 0.000 claims description 2
- 230000000052 comparative effect Effects 0.000 description 13
- 238000001953 recrystallisation Methods 0.000 description 8
- 229910052751 metal Inorganic materials 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 238000001816 cooling Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 239000013078 crystal Substances 0.000 description 3
- 239000002775 capsule Substances 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 230000006911 nucleation Effects 0.000 description 2
- 238000010899 nucleation Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/002—Extruding materials of special alloys so far as the composition of the alloy requires or permits special extruding methods of sequences
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular operations
- B21J5/08—Upsetting
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
- C22C23/06—Alloys based on magnesium with a rare earth metal as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/06—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of magnesium or alloys based thereon
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
- Extrusion Of Metal (AREA)
Abstract
The invention discloses a preparation method of a magnesium alloy cabin, which comprises the following steps: A. smelting and casting a cylindrical Mg-Y-Zn alloy ingot blank; B. homogenizing and annealing the ingot blank; C. extrusion molding is performed in an extrusion cylinder. The extrusion speed of the extrusion rod is 1-5mm/s, and the extrusion ratio is 4-9; D. cutting the extrusion rod into sections, heating to 420-460 ℃, preserving heat for 1.5-3 hours, upsetting and deforming, wherein the upsetting direction is vertical to the I-ED, pressing to 90-110mm in height, and machining into forging stock with the diameter of 200-230mm and the height of 85-105mm after upsetting, wherein the height direction of the forging stock is consistent with the upsetting direction; E. forging the forging stock; before die forging, heating the die and the forging stock to 380-430 ℃ and preserving heat for 1.5-3 hours, and then die forging is carried out at a pressing speed of 2-8mm/s, wherein the die forging direction is consistent with the upsetting direction; F. and (5) aging the cabin body after die forging. The magnesium alloy cabin member prepared by the method has high strength, good plasticity and weak anisotropy of mechanical properties, and widens the application scene of the magnesium alloy cabin member.
Description
Technical Field
The invention relates to the field of magnesium alloy deformation processing, in particular to a preparation method of a magnesium alloy cabin.
Background
As the lightest practical metallic structural material at present, magnesium alloys have been widely studied in the fields of aerospace, automobile industry and the like in recent years. However, magnesium alloys of close-packed hexagonal structure are difficult to plastically deform, have serious anisotropy, and have absolute strength generally lower than that of aluminum alloys, steel materials, and the like, which limits the application range thereof.
The directional die forging can crush coarse casting structures, improves the uniformity and fineness of material structures through plastic deformation and recrystallization, and improves the mechanical properties of materials, so that the die forging forming technology has been widely applied to the production of cabins. However, when the magnesium alloy is die-forged, macroscopic fiber structures or streamline structures are generated along the metal flow direction, so that the strength and plasticity of the finally formed cabin member along the metal flow direction (generally the axial direction of the cabin) are superior to those of other directions, the cabin member has obvious anisotropy, and the lower strength and plasticity of the other directions are formed into a short plate, so that the application scene of the member is greatly limited.
In Mg-RE-Zn alloys, zn, RE solute atoms are biased to form a long-period ordered structural phase (LPSO). The LPSO phase has important influence on the mechanical properties of the magnesium alloy, on one hand, the LPSO phase can promote non-basal plane slip and inhibit basal plane slip, and is beneficial to improving the strength and the plasticity of the alloy simultaneously; on the other hand, the recrystallization behavior of the magnesium alloy can be influenced, the recrystallization nucleation is promoted by a second phase particle induced nucleation (PSN) mechanism, and the grain size is reduced. However, the LPSO phase tends to align in the extrusion direction after extrusion, resulting in better mechanical properties in the extrusion direction than in other directions. The invention makes full use of the characteristics of LPSO phase, prepares the quasi-isotropic high-strength and high-toughness magnesium alloy cabin body by improving the forming process, and widens the application range of the magnesium alloy component.
Disclosure of Invention
The invention provides a preparation method of a magnesium alloy cabin, which comprises the following specific technical scheme:
A. smelting and casting a cylindrical Mg-Y-Zn alloy ingot blank, wherein the alloy comprises the following components in percentage by mass: 3.5-9.5%, zn:0.5-2.5%, the balance being Mg and non-removable impurity elements;
B. homogenizing and annealing the ingot blank;
C. and extruding the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder to form, wherein the extrusion rod has an extrusion speed of 1-5mm/s and an extrusion ratio of 4-9, and the diameter of the extruded bar is 160-200mm. Defining the initial extrusion direction as I-ED;
D. cutting the extrusion rod into sections, heating the ingot blank to 420-460 ℃, preserving heat for 1.5-3 hours, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 5-20mm/s, and the pressing height is 90-110mm; machining into forging stock with diameter of 200-230mm and height of 85-105mm after upsetting, wherein the height direction of the forging stock is consistent with the upsetting direction;
E. performing die forging forming on the forging stock to prepare a cabin; before die forging, heating the die and the forging stock to 380-430 ℃ and preserving heat for 1.5-3 hours, and then die forging is carried out at a pressing speed of 2-8mm/s, wherein the die forging direction is consistent with the upsetting direction;
F. and (5) aging the cabin body after die forging.
Preferably, in the step B, the annealing process is as follows: preserving the temperature at 495-525 ℃ for 30-80h.
Preferably, in the step C, the ingot blank and the mould are preheated before extrusion, and are heated to 380-440 ℃ and are kept for 0.5-3.5 hours.
Preferably, in the step F, the aging process is to keep the temperature at 190-240 ℃ for 40-100h, and air-cool to room temperature.
Wherein, the room temperature yield strength of the die forging cabin member after aging treatment in the step F is more than or equal to 240MPa, the tensile strength is more than or equal to 300MPa, the elongation after forging is more than or equal to 8.0, the absolute value of the strength difference of the member along the axial direction and the circumferential direction is less than 15MPa, and the absolute value of the elongation difference after forging is less than 2%.
In the scheme, the aim of homogenizing annealing treatment of the cast ingot at 495-525 ℃ for 30-80 hours is mainly to promote the dissolution of an as-cast alloy eutectic structure, fully diffuse Y, zn atoms into a Mg matrix and provide sufficient solid solution atoms for the subsequent precipitation of a large number of LPSO phases in alpha-Mg crystal grains. Secondly, the homogenizing annealing can homogenize the structure of the casting, reduce dendrite segregation and eliminate residual stress, further improve the plastic deformation capacity of the casting and prevent the casting from cracking prematurely in the subsequent forming. In the subsequent extrusion treatment process, extrusion deformation with the extrusion ratio of 4-9 is carried out by taking 380-440 ℃ as the initial temperature, so that the alloy can be prevented from cracking due to too low temperature and too large deformation in the deformation process, and the LPSO phase is promoted to be directionally arranged along the extrusion direction. The LPSO phase can change the recrystallization behavior of the alloy, promote the recrystallization in the plastic deformation process of the subsequent process, reduce the grain size and improve the strength and the elongation of the alloy. However, the LPSO phase alignment produces a short fiber reinforcement effect, resulting in an alloy that has higher strength and ductility in the extrusion direction than in the other directions.
Upsetting is a pre-deformation prior to the swaging process that further refines the grain size of the final die forging. The upsetting direction is perpendicular to the initial extrusion direction I-ED, not only making it difficult for the LPSO phase to kink or bend, but also increasing the degree of ordered arrangement of the LPSO phase. The die forging direction coincides with the upsetting direction, and the metal flows to form a streamline which is vertical to the LPSO phase directional arrangement direction during die forging, so that the mechanical property anisotropy caused by the LPSO phase is relieved. Through fine process parameter design, the mechanical properties in all directions tend to be identical, the improvement effect of the relative mechanical properties of fine crystals and LPSO is reserved to the maximum extent, and finally the anisotropy weakening of the cabin die forging is realized while the strength and the plasticity of the alloy are enhanced.
The invention has the main advantages that: the preparation method of the quasi-isotropic high-strength and high-toughness magnesium alloy cabin body is provided by comprehensively utilizing the characteristics of the directional arrangement of LPSO (low pressure so) phases in the Mg-Y-Zn alloy and the reinforcement and plasticization of metal streamline in the die forging in a single direction of the material, and the application scene of the magnesium alloy cabin body component is widened.
Drawings
FIG. 1 is a CAD dimensional drawing of a capsule forging of example 1;
FIG. 2 is a scanning electron microscope microstructure of the extruded rod of example 1;
FIG. 3 is a scanning electron microscope microstructure of the sample after upsetting in example 1;
FIG. 4 is a scanning electron microscope microstructure of the nacelle die forging of example 1;
FIG. 5 is a scanning electron microscope microstructure of the nacelle die forging of example 2;
FIG. 6 is a scanning electron microscope microstructure of the nacelle die forging of comparative example 1;
FIG. 7 is a scanning electron microscope microstructure of the nacelle die forging of comparative example 2;
FIG. 8 is a scanning electron microscope microstructure of the nacelle die forging of comparative example 3.
Detailed Description
A large number of comparison experiments are carried out by adjusting the forming process parameters. The invention is further illustrated by the following examples. These examples are given for the purpose of illustration and are not intended to be limiting, and modifications in the process of the invention are within the scope of the invention.
Example 1: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-9.5Y-2.5Zn. The homogenizing annealing process of the ingot blank is to keep the temperature at 525 ℃ for 30 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 440 ℃ and kept for 0.5h. In extrusion, the extrusion rod advancing speed was 5mm/s, the extrusion ratio was 4, the diameter of the extruded rod was 200mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingots with the length of 160mm, heating the ingots to 460 ℃, preserving heat for 1.5h, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 20mm/s, and the pressing height is 90mm. After upsetting, machining into forging stock with diameter of 230mm and height of 85mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 430 ℃ and preserving heat for 1.5 hours before die forging, and then performing die forging at a pressing speed of 8mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 240 ℃ for 40 hours, and then cooling to room temperature in air. The CAD size diagram of the cabin die forging is shown in fig. 1, the scanning electron microscope microstructure of the extruded bar is shown in fig. 2, the scanning electron microscope microstructure of the upsetted sample is shown in fig. 3, and the scanning electron microscope microstructure of the obtained cabin die forging is shown in fig. 4. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Example 2: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-3.5Y-0.5Zn. The homogenizing annealing process of the ingot blank is carried out at 495 ℃ for 80 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 380 ℃ and kept for 3.5 hours. During extrusion, the extrusion rod advancing speed was 1mm/s, the extrusion ratio was 9, the diameter of the extruded rod was 160mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingot blanks with the length of 200mm, heating the ingot blanks to 420 ℃, preserving heat for 3 hours, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 5mm/s, and the pressing height is 110mm. And (5) after upsetting, machining into a forging stock with the diameter of 200mm and the height of 105mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 380 ℃ and preserving heat for 3 hours before die forging, and then performing die forging at a pressing speed of 2mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 190 ℃ for 100h, and then cooling to room temperature in air. The scanning electron microscope microstructure of the obtained cabin die forging piece is shown in figure 5. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Example 3: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-5.2Y-0.8Zn. The homogenizing annealing process of the ingot blank is to keep the temperature at 510 ℃ for 50 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 390 ℃ and kept for 2.5 hours. During extrusion, the extrusion rod advancing speed was 3mm/s, the extrusion ratio was 6.3, the diameter of the extruded rod was 180mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingots with the length of 190mm, heating the ingots to 440 ℃, preserving heat for 2 hours, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 10mm/s, and the pressing height is 108mm. After upsetting, machining into forging stock with the diameter of 205mm and the height of 100mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 400 ℃ and preserving heat for 2.5 hours before die forging, and then performing die forging at a pressing speed of 5mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 220 ℃ for 70 hours, and then cooling to room temperature in air. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Comparative example 1: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-9.5Y-2.5Zn. The homogenizing annealing process of the ingot blank is to keep the temperature at 525 ℃ for 20 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 440 ℃ and kept for 0.5h. In extrusion, the extrusion rod advancing speed was 5mm/s, the extrusion ratio was 4, the diameter of the extruded rod was 200mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingots with the length of 160mm, heating the ingots to 460 ℃, preserving heat for 1.5h, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 20mm/s, and the pressing height is 90mm. After upsetting, machining into forging stock with diameter of 230mm and height of 85mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 430 ℃ and preserving heat for 1.5 hours before die forging, and then performing die forging at a pressing speed of 8mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 240 ℃ for 40 hours, and then cooling to room temperature in air. The scanning electron microscope microstructure of the obtained cabin die forging piece is shown in figure 6. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Comparative example 2: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-9.5Y-2.5Zn. The homogenizing annealing process of the ingot blank is to keep the temperature at 525 ℃ for 30 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 440 ℃ and kept for 0.5h. In extrusion, the extrusion rod advancing speed was 5mm/s, the extrusion ratio was 4, the diameter of the extruded rod was 200mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingots with the length of 160mm, heating the ingots to 460 ℃, preserving heat for 1.5h, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 20mm/s, and the pressing height is 90mm. After upsetting, machining into forging stock with diameter of 230mm and height of 85mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 450 ℃ and preserving heat for 1.5 hours before die forging, and then performing die forging at a pressing speed of 8mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 240 ℃ for 40 hours, and then cooling to room temperature in air. The scanning electron microscope microstructure of the obtained cabin die forging piece is shown in figure 7. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Comparative example 3: smelting and casting a cylindrical ingot blank of the Mg-Y-Zn alloy, wherein the mass percentage content of the alloy is Mg-3.5Y-0.5Zn. The homogenizing annealing process of the ingot blank is carried out at 495 ℃ for 80 hours. And extruding and forming the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder. Before extrusion, the ingot blank and the mould are heated to 360 ℃ and kept for 3.5 hours. During extrusion, the extrusion rod advancing speed was 1mm/s, the extrusion ratio was 9, the diameter of the extruded rod was 160mm, and the initial extrusion direction was defined as I-ED. Cutting an extrusion rod into ingot blanks with the length of 200mm, heating the ingot blanks to 420 ℃, preserving heat for 3 hours, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 5mm/s, and the pressing height is 110mm. And (5) after upsetting, machining into a forging stock with the diameter of 200mm and the height of 105mm, wherein the height direction of the forging stock is consistent with the upsetting direction. And (3) performing die forging forming on the forging stock to prepare a cabin body, heating the die and the forging stock to 380 ℃ and preserving heat for 3 hours before die forging, and then performing die forging at a pressing speed of 2mm/s, wherein the die forging direction is consistent with the upsetting direction. And (3) aging the cabin body after die forging, preserving heat at 190 ℃ for 100h, and then cooling to room temperature in air. The scanning electron microscope microstructure of the obtained cabin die forging piece is shown in figure 8. The mechanical properties of the obtained cabin die forging piece in the axial direction and the circumferential direction are shown in table 1.
Table 1: room temperature mechanical properties of magnesium alloy cabin members in examples and comparative examples
It can be seen from FIG. 2 that after the homogenizing annealing and extrusion treatment of the Mg-Y-Zn alloy according to the process of the present invention, a large number of inter-crystalline bulk and intra-crystalline needle LPSO phases arranged in the extrusion direction appear. As can be seen from fig. 3 and 4, example 1 significantly increased the recrystallized volume fraction and decreased the average grain size after upsetting and swaging in the direction perpendicular to the initial extrusion direction I-ED; the ordered degree of the LPSO phases arranged along the direction perpendicular to the upsetting direction after upsetting is enhanced; the LPSO phase alignment direction after swaging is slightly inclined toward the swaging direction but is generally aligned along the I-ED. Meanwhile, as can be seen from Table 1, the Mg-Y-Zn magnesium alloy cabins of examples 1 to 3 are smaller in difference in axial and circumferential mechanical properties and more excellent in comprehensive mechanical properties than those of comparative examples 1 to 3.
Referring to fig. 4 and 6, it was found from comparative example 1 and comparative example 1 that the annealing and heat-preserving time of the ingot blank was insufficient without using the homogenizing annealing process of the present invention, and the LPSO phase generated was significantly reduced, particularly, the needle-like LPSO phase in the crystal was almost lost, and the alloy strength was significantly reduced due to the reduction of the strengthening phase of the LPSO phase; wherein, the loss of the circumferential strength of the cabin die forging is more serious, so that the mechanical property difference of the cabin in different directions is increased. With reference to fig. 4 and 7, in comparative examples 1 and 2, since the forging temperature is too high, the metal flows more actively during forging in comparative example 2, and the rapidly flowing metal drives the LPSO phase to move and deflect in the flowing direction when filling the cavity, so that the LPSO phase originally perpendicular to the forging direction tends to be parallel to the forging direction, while the axial strength of the cabin die forging is further improved, the circumferential strength is sacrificed, and the mechanical property anisotropy becomes more obvious in different directions. With reference to fig. 5 and 8, in comparative examples 2 and 3, since the preheating temperature before extrusion is low, the directional arrangement order of LPSO phases during extrusion is high and the recrystallization degree is low, sufficient dynamic recrystallization cannot be achieved in the subsequent upsetting and swaging processes, and the arrangement order of LPSO phases along each direction is balanced, resulting in higher circumferential strength of the capsule, lower elongation, and serious component anisotropy. Obviously, by adopting the process provided by the invention, the volume fraction of the LPSO phase, the recrystallization degree, the arrangement order degree of the LPSO phase and the metal streamline are scientifically regulated and controlled, and the influence factors of the directional strong plasticity are reasonably preset, so that the quasi-isotropic magnesium alloy cabin body can be prepared.
The embodiments of the present invention have been described above with reference to the accompanying drawings, and the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict. The present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those of ordinary skill in the art without departing from the spirit of the invention and the scope of the appended claims, which are all within the scope of the invention.
Claims (5)
1. A preparation method of a magnesium alloy cabin is characterized by comprising the following steps:
A. smelting and casting a cylindrical Mg-Y-Zn alloy ingot blank, wherein the alloy comprises the following components in percentage by mass: 3.5-9.5%, zn:0.5-2.5%, the balance being Mg and non-removable impurity elements;
B. homogenizing and annealing the ingot blank;
C. and extruding the ingot blank subjected to the homogenizing annealing treatment in an extrusion cylinder to form, wherein the extrusion rod has an extrusion speed of 1-5mm/s and an extrusion ratio of 4-9, and the diameter of the extruded bar is 160-200mm. Defining the initial extrusion direction as I-ED;
D. cutting the extrusion rod into sections, heating the ingot blank to 420-460 ℃, preserving heat for 1.5-3 hours, upsetting and deforming on a hydraulic press, wherein the upsetting direction is vertical to the I-ED, the pressing speed of the pressing head is 5-20mm/s, and the pressing height is 90-110mm; machining into forging stock with diameter of 200-230mm and height of 85-105mm after upsetting, wherein the height direction of the forging stock is consistent with the upsetting direction;
E. performing die forging forming on the forging stock to prepare a cabin; before die forging, heating the die and the forging stock to 380-430 ℃ and preserving heat for 1.5-3 hours, and then die forging is carried out at a pressing speed of 2-8 mm/s; the die forging direction is consistent with the upsetting direction;
F. and (5) aging the cabin body after die forging.
2. The method for preparing a magnesium alloy cabin according to claim 1, wherein in the step B, the annealing process is as follows: preserving the temperature at 495-525 ℃ for 30-80h.
3. The method for preparing a magnesium alloy cabin according to claim 1, wherein in the step C, the ingot blank and the mold are preheated before extrusion, and the ingot blank and the mold are heated to 380-440 ℃ and kept for 0.5-3.5h.
4. The method for preparing a magnesium alloy cabin according to claim 1, wherein in the step F, the aging process is to keep the temperature at 190-240 ℃ for 40-100h, and air-cool to room temperature.
5. The method for preparing a magnesium alloy cabin according to claim 1, wherein the room temperature yield strength of the die forging cabin member after aging treatment in the step F is not less than 240MPa, the tensile strength is not less than 300MPa, the elongation after forging is not less than 8.0, the absolute value of the strength difference between the member in the axial direction and the circumferential direction is less than 15MPa, and the absolute value of the elongation difference after forging is less than 2%.
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