CN111644548A - Forging-modifying technology for high-strength homogeneous aluminum alloy forging for spaceflight - Google Patents
Forging-modifying technology for high-strength homogeneous aluminum alloy forging for spaceflight Download PDFInfo
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- CN111644548A CN111644548A CN202010534021.7A CN202010534021A CN111644548A CN 111644548 A CN111644548 A CN 111644548A CN 202010534021 A CN202010534021 A CN 202010534021A CN 111644548 A CN111644548 A CN 111644548A
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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
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/06—Heating or cooling methods or arrangements specially adapted for performing forging or pressing operations
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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
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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
- B21J5/06—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
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
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Abstract
The invention discloses a forging-modifying technology of a high-strength homogeneous aluminum alloy forging for spaceflight, belonging to the technical field of aluminum alloy forging technology, and the technical scheme is characterized by comprising the following steps: the method comprises the following steps: heating; forging: s1, upsetting the blank along the axial direction; s2, upsetting the blank along the rolling direction; s3, upsetting the blank along the axial direction; s4, axially drawing the blank; s5, upsetting the blank along the axial direction; s6, axially drawing the blank; s7, upsetting the blank along the axial direction; s8, axially drawing the blank; s9, upsetting the blank along the axial direction; step two: s1, heating: heating the blank and then preserving heat; s2, ejection: performing rounding upsetting, punching and expanding; step three: s1, heating: heating the blank and then preserving heat; s2, ring rolling: rolling the blank to form a ring; step four: s1, solid solution: keeping the temperature after heating, and quickly cooling the forging by water; s2, artificial aging, and the method has the advantages that the existing forging and cogging method is improved, the generation of cracks in the forging process is reduced, and the physical and chemical properties of the forge piece are improved.
Description
Technical Field
The invention relates to the technical field of aluminum alloy forging processes, in particular to a forging-modifying technology of a high-strength homogeneous aluminum alloy forging for spaceflight.
Background
Along with the rapid development of the aerospace industry, the modern national defense industry and the transportation industry in China, the light weight of important stressed parts and structural parts promotes the increasing of the call for aluminum strip steel, and the usage amount and demand amount of aluminum alloy forgings are gradually increased.
The aluminum alloy for forging adopts the rod to be mostly extrusion rod, and there are casting defects such as gas pocket, loose, segregation in the material itself, and forging defects such as crackle easily produce in the forging process, and the forging performance is lower. At present, the cogging is carried out by adopting a direct upsetting mode, and cracks are easily generated on the surface of a forged blank due to the casting defects of raw materials in the forging and cogging processes; the mechanical property of the forged piece is poor, and the requirement of acceptance standard cannot be met.
Disclosure of Invention
The invention aims to provide a forging technology for a high-strength homogeneous aluminum alloy forging for aerospace, which has the advantages that the existing forging cogging method is improved, the generation of cracks in the forging process is reduced, and the physical and chemical properties of the forging are improved.
The technical purpose of the invention is realized by the following technical scheme:
a forging-modifying technology for a high-strength homogeneous aluminum alloy forging for aerospace comprises the following steps:
the method comprises the following steps: comprises heating and forging, wherein the heating: preparing a raw material, placing the raw material in an aluminum alloy heating furnace, heating the raw material to 440 ℃, and then preserving heat to obtain a blank;
forging: s1, upsetting the blank in the axial direction; s2, upsetting the blank along the rolling direction; s3, upsetting the blank in the axial direction; s4, drawing the blank along the axial direction; s5, upsetting the blank in the axial direction; s6, drawing the blank along the axial direction; s7, upsetting the blank in the axial direction; s8, drawing the blank along the axial direction; s9, upsetting the blank in the axial direction;
step two: s1, heating: returning the hot blank processed in the first step to the furnace, and keeping the temperature of the blank after the temperature of the blank is raised to 440 ℃; s2, ejection: sequentially carrying out rounding upsetting, punching and expanding on the blank;
step three: s1, heating: returning the blank hot material processed in the step two to the furnace, and keeping the temperature after the blank is heated to 440 ℃; s2, ring rolling: rolling the blank to obtain a forged piece;
step four: s1, solid solution: firstly, heating, charging the forge piece processed in the second step at room temperature, heating to 470 ℃, preserving heat, then cooling, and rapidly cooling the forge piece by water at the temperature of 65-75 ℃; s2, artificial aging: firstly, heating, charging the forge piece at room temperature, heating to 120 ℃, preserving heat for 24 hours, heating to 160 ℃, preserving heat for 4 hours, and finally cooling the forge piece in an air cooling mode.
Furthermore, in the heating process of the first step, the heat preservation time is 12 hours.
Further, in the forging modification process of the step one, the integral forging ratio of the blank is 6.3.
Furthermore, in the heating process of the second step, the heat preservation time is 4 hours.
Further, in the blank ejection process of the second process step, the overall deformation of the blank is 21.2%.
Furthermore, in the heating process of the third step, the heat preservation time is 4 hours.
Further, in the ring rolling process of the third step, the overall deformation of the blank is 50%.
Furthermore, in the solid solution process of the fourth step, the time from the discharging of the forge piece to the water entering is less than or equal to 15S.
In conclusion, the invention has the following beneficial effects:
1. through multiple small-deformation upsetting and upsetting-drawing, the generation of cracks in the forging process is reduced, and the physical and chemical properties of the forging are improved;
2. through solid solution and aging strengthening, the physical and chemical properties of the forging are further improved, and the generation of forging cracks is reduced.
Drawings
FIG. 1 is a schematic diagram of a forging-modifying technique for a high-strength homogeneous aluminum alloy forging for aerospace;
fig. 2 is a schematic view of the variation of the shape of the blank.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Example (b): a forging-modifying technology for a high-strength homogeneous aluminum alloy forging for aerospace is shown in figure 1 and comprises the following steps:
an aluminum alloy raw material is prepared, the weight of which is 215kg, and the specification of the aluminum alloy raw material is as follows: 510mm flow lines 420mm 356 mm.
The method comprises the following steps: the forging apparatus used was a 1250T rapid forging machine comprising the following procedures:
heating: preparing raw materials, placing the raw materials in an aluminum alloy heating furnace, heating the raw materials to 440 ℃, and then preserving heat for 12 hours to obtain a blank.
Forging: the shape of the blank was changed as shown in fig. 2, and the blank was axially elongated to 400mm flow lines 480mm 400mm, S1.
S2, upsetting the billet in the rolling direction with dimensions 460mm flow lines 530mm 320 mm.
And S3, upsetting the blank in the axial direction, wherein the size is 350mm streamline 610mm 360 mm.
And S4, axially stretching the blank to a size of 810mm streamline 305 mm.
And S5, upsetting the blank in the axial direction, wherein the size is 480mm streamline 400 mm.
And S6, axially stretching the blank to a size of 810mm streamline 305 mm.
And S7, upsetting the blank in the axial direction, wherein the size is 480mm streamline 400 mm.
And S8, axially stretching the blank to a size of 810mm streamline 305 mm.
And S9, upsetting the blank in the axial direction, wherein the size is 380mm streamline and 445 mm.
The forging ratio of the billet was 6.3.
Step two: s1, heating: and (4) returning the hot blank processed in the step one to the furnace, heating the blank to 440 ℃, and then preserving heat for 4 hours.
S2, ejection: carrying out rolling upsetting on the blank, wherein the size of the blank is as follows: phi 860mm 130mm flow line.
Punching a blank, wherein the size of the blank is as follows: phi 860mm phi 280mm (inner bore) 130mm flow line.
And (3) carrying out horse expanding on the blank, wherein the size of the blank is as follows: phi 965mm phi 500mm (inner bore) 130mm flow line.
The overall deformation of the blank was 21.2%.
Step three: s1, heating: and (4) returning the blank hot material processed in the step two to the furnace, heating the blank to 440 ℃, and then preserving heat for 4 hours.
S2, ring rolling: and (3) rolling the blank to obtain a forged piece, wherein the shape of the forged piece is changed as shown in figure 2, and the size of the forged piece is phi 2010mm phi 780mm (inner hole) 95 mm. The overall deformation of the blank was 50%.
Step four: s1, solid solution: firstly, heating, charging the forge piece processed in the second step at room temperature, then heating to 470 ℃, preserving heat, then cooling, rapidly cooling the forge piece by water, wherein the water temperature is 65-75 ℃, and the time from the forge piece discharging to the water entering is less than or equal to 15S.
S2, artificial aging: firstly, heating, charging the forge piece at room temperature, heating to 120 ℃, preserving heat for 24 hours, heating to 160 ℃, preserving heat for 4 hours, and finally cooling the forge piece in an air cooling mode.
Comprehensive detection experiment of forgings:
preparation of the experiment: two forgings were randomly drawn from different batches of product as test specimen SL1 and test specimen SL 2.
Experiment temperature: keeping the temperature at 25 ℃.
Experiment humidity: 75% rh.
Supplementary description of the experiment: and sampling after the forging is cooled for 24 h.
Table 1.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment without inventive contribution as needed after reading the present specification, but all of them are protected by patent law within the scope of the claims of the present invention.
Claims (8)
1. The forging-modifying technology for the high-strength homogeneous aluminum alloy forging for spaceflight is characterized by comprising the following steps of:
the method comprises the following steps: comprises heating and forging, wherein the heating: preparing a raw material, placing the raw material in an aluminum alloy heating furnace, heating the raw material to 440 ℃, and then preserving heat to obtain a blank;
forging: s1, upsetting the blank in the axial direction; s2, upsetting the blank along the rolling direction; s3, upsetting the blank in the axial direction; s4, drawing the blank along the axial direction; s5, upsetting the blank in the axial direction; s6, drawing the blank along the axial direction; s7, upsetting the blank in the axial direction; s8, drawing the blank along the axial direction; s9, upsetting the blank in the axial direction;
step two: s1, heating: returning the hot blank processed in the first step to the furnace, and keeping the temperature of the blank after the temperature of the blank is raised to 440 ℃; s2, ejection: sequentially carrying out rounding upsetting, punching and expanding on the blank;
step three: s1, heating: returning the blank hot material processed in the step two to the furnace, and keeping the temperature after the blank is heated to 440 ℃; s2, ring rolling: rolling the blank to obtain a forged piece;
step four: s1, solid solution: firstly, heating, charging the forge piece processed in the second step at room temperature, heating to 470 ℃, preserving heat, then cooling, and rapidly cooling the forge piece by water at the temperature of 65-75 ℃; s2, artificial aging: firstly, heating, charging the forge piece at room temperature, heating to 120 ℃, preserving heat for 24 hours, heating to 160 ℃, preserving heat for 4 hours, and finally cooling the forge piece in an air cooling mode.
2. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: in the heating process of the first step, the heat preservation time is 12 hours.
3. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: in the forging modification process of the step one, the integral forging ratio of the blank is 6.3.
4. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: and in the heating process of the second step, the heat preservation time is 4 hours.
5. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: and in the blank ejection process of the second step, the overall deformation of the blank is 21.2 percent.
6. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: and in the heating process of the third step, the heat preservation time is 4 hours.
7. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: in the ring rolling process of the third step, the overall deformation of the blank is 50%.
8. The forging improvement technology for the high-strength homogeneous aluminum alloy forging for spaceflight as claimed in claim 1, wherein: in the solid solution process of the fourth step, the time from the discharging of the forge piece to the water inlet is less than or equal to 15S.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112317662A (en) * | 2020-10-09 | 2021-02-05 | 中国航发北京航空材料研究院 | Extrusion-upsetting-drawing composite cogging method for high-temperature alloy difficult to deform |
| CN112808910A (en) * | 2020-12-31 | 2021-05-18 | 无锡派克新材料科技股份有限公司 | Forging method for improving percent of pass of large-wall-thickness 5754 aluminum alloy forge piece |
| CN112828218A (en) * | 2020-12-31 | 2021-05-25 | 无锡派克新材料科技股份有限公司 | Method for forming large-size thick-section ultrahigh-strength aluminum alloy cylindrical part |
| CN112893727A (en) * | 2021-02-26 | 2021-06-04 | 陕西长羽航空装备有限公司 | Forging process of magnesium-lithium alloy |
| CN114309411A (en) * | 2022-01-20 | 2022-04-12 | 中聚信海洋工程装备有限公司 | Crank prefabricated part forging process |
| CN114505429A (en) * | 2021-12-15 | 2022-05-17 | 陕西宏远航空锻造有限责任公司 | Forging method of 7050 aluminum alloy forging |
| CN117259630A (en) * | 2023-09-28 | 2023-12-22 | 太仓申星锻造有限公司 | Forming process of membrane water-cooled wall sealing forging |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112317662A (en) * | 2020-10-09 | 2021-02-05 | 中国航发北京航空材料研究院 | Extrusion-upsetting-drawing composite cogging method for high-temperature alloy difficult to deform |
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| CN112828218A (en) * | 2020-12-31 | 2021-05-25 | 无锡派克新材料科技股份有限公司 | Method for forming large-size thick-section ultrahigh-strength aluminum alloy cylindrical part |
| CN112893727A (en) * | 2021-02-26 | 2021-06-04 | 陕西长羽航空装备有限公司 | Forging process of magnesium-lithium alloy |
| CN114505429A (en) * | 2021-12-15 | 2022-05-17 | 陕西宏远航空锻造有限责任公司 | Forging method of 7050 aluminum alloy forging |
| CN114309411A (en) * | 2022-01-20 | 2022-04-12 | 中聚信海洋工程装备有限公司 | Crank prefabricated part forging process |
| CN117259630A (en) * | 2023-09-28 | 2023-12-22 | 太仓申星锻造有限公司 | Forming process of membrane water-cooled wall sealing forging |
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