CN112264565A - Manufacturing method of high-performance aluminum alloy cylindrical forging for spaceflight - Google Patents
Manufacturing method of high-performance aluminum alloy cylindrical forging for spaceflight Download PDFInfo
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- CN112264565A CN112264565A CN202010519097.2A CN202010519097A CN112264565A CN 112264565 A CN112264565 A CN 112264565A CN 202010519097 A CN202010519097 A CN 202010519097A CN 112264565 A CN112264565 A CN 112264565A
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- blank
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- aluminum alloy
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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
- B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
- B21H1/00—Making articles shaped as bodies of revolution
- B21H1/06—Making articles shaped as bodies of revolution rings of restricted axial length
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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
- B21J5/10—Piercing billets
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/08—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for tubular bodies or pipes
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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
Abstract
The invention discloses a method for manufacturing a high-performance aluminum alloy cylindrical forging for spaceflight, which belongs to the technical field of aluminum alloy forging and heat treatment, and the technical scheme is characterized by comprising the following steps of: s1, blanking; s2, forging and heating: heating the blank to 440-470 ℃, and preserving the heat for 20-25 h; s3, blank making: upsetting and drawing twice along the axial direction of the blank to form a round cake piece; s4, returning: returning the blank to the furnace, heating to 420-440 ℃, and preserving heat for 4-7 h; s5, backward extrusion: punching the blank, then carrying out backward extrusion on the blank, and then air-cooling the blank to room temperature; s6, cleaning: cleaning an inner hole and a bottom plate of the blank; s7, returning and heating: heating the blank to 420-440 ℃, and preserving heat for 4-8 h; s8, ring rolling: rolling the blank into a ring; s9, solution treatment: heating the blank to 500-530 ℃, then preserving heat, and discharging the blank from a furnace and cooling by water; s10, aging treatment: the blank is heated to 140-175 ℃ and then is subjected to heat preservation, and the method has the advantages of greatly improving the axial performance and improving the structure uniformity of the forge piece.
Description
Technical Field
The invention relates to the technical field of aluminum alloy forging and heat treatment, in particular to a manufacturing method of a high-performance aluminum alloy cylindrical forging for spaceflight.
Background
Along with the rapid development of the domestic and overseas aerospace industry, the modern national defense industry and the transportation industry, the high-performance cylindrical aluminum alloy for aerospace has attracted attention in the domestic and overseas aerospace field, the integral high-cylindrical ring forging of the aluminum alloy can only be cast in the prior art due to the restriction of process equipment and the like, but the casting has the problems of high product rejection rate, low reliability and the like due to the defects of air holes, looseness, segregation and the like, at present, the integral aluminum alloy ring is adopted to replace a casting, and the improvement of the product performance and the reliability is the development trend of manufacturing high-cylinder aluminum alloy components.
The existing treatment technology of the cylindrical aluminum alloy forging comprises the following steps: and (3) punching after multidirectional forging of the cast ingot, drawing out the mandrel, reaming the trestle, grinding the ring, and performing heat treatment and rough machining. On one hand, the radial mechanical property is low due to the deformation mode of mandrel drawing and trestle reaming; meanwhile, the deformation mode does not restrict the axial direction of the blank, so that the axial flow line is not obvious, and the axial mechanical property is low; on the other hand, as the hot working procedures involved in the production process are more, the hot working belongs to the process of thermal coupling alternation, the mandrel drawing and the saddle reaming are non-continuous thermal deformation processes, the deformation mode has no constraint on the axial direction of the blank, the axial flow line is not obvious, the process of thermal coupling alternation repeatedly can cause that the quality of the forged piece is difficult to control, and the nonuniformity of the forged piece structure can be increased.
Disclosure of Invention
The invention aims to provide a method for manufacturing a high-performance aluminum alloy cylindrical forging for spaceflight, which has the advantages that the axial performance can be greatly improved and the structure uniformity of the forging is improved by carrying out multidirectional forging and backward extrusion treatment on a blank.
The technical purpose of the invention is realized by the following technical scheme:
a manufacturing method of a high-performance aluminum alloy cylindrical forging for spaceflight comprises the following steps:
s1, blanking: blanking on the aluminum alloy ingot according to the size specification to obtain a blank;
s2, forging and heating: placing the blank in a heating furnace, heating to 440-470 ℃, and preserving heat for 20-25 h;
s3, blank making: upsetting and drawing twice along the axial direction of the blank to form a round cake piece;
s4, returning: returning the blank to the furnace for heating, raising the temperature to 420-440 ℃, and preserving the heat for 4-7 hours;
s5, backward extrusion: punching the blank, increasing the axial height of the blank, then carrying out backward extrusion on the blank, and then air-cooling the blank to room temperature;
s6, cleaning: cleaning an inner hole and a bottom plate of the blank;
s7, returning and heating: placing the blank cleaned in the step S6 in a heating furnace, heating to 420-440 ℃, and preserving heat for 4-8 h;
s8, ring rolling: rolling the blank into a ring;
s9, solution treatment: heating the blank to 500-530 ℃, then preserving heat, taking the blank out of a furnace, cooling by water, keeping the water temperature at 40-65 ℃, and keeping the water in for 20-40 min;
s10, aging treatment: heating the blank to 140-175 ℃, then preserving heat, discharging the blank out of the furnace, and air-cooling to room temperature.
Further, in step S3, the deformation amount of each single upsetting of the billet is more than or equal to 65%.
Further, in step S3, the blank is formed to a size of Φ 705 × 900 mm.
Further, in step S5, the dimensions of the billet are back-extruded to Φ 705 × Φ 360 × 1200 mm.
Further, in step S8, the billet ring is sized to Φ 1040 × Φ 860 × 1200 mm.
Further, in step S9, the heat preservation time is 6-10 h.
Further, in step S10, the heat preservation time is 5-12 h.
In conclusion, the invention has the following beneficial effects:
1. the axial streamline of the blank is changed into the direction of the forced streamline through backward extrusion, the axial performance can be greatly improved, the deformation mode does not cause forging compression damage to the radial direction, the radial performance is improved to the maximum extent, meanwhile, the overall deformation of the blank is uniform and consistent in the deformation process, the organization is guaranteed to be uniform and consistent, and the final mechanical performance of the blank in all directions is guaranteed to be uniform and consistent.
2. The reverse extrusion deformation forces the three-way compression deformation, and in the reverse extrusion process, the blank is subjected to the action of three-way pressure stress, so that the residual crystalline phase in the aluminum alloy can be forcedly crushed, the second phase can be fully dissolved and aged in the subsequent heat treatment process, and the mechanical property of the product is greatly improved.
Drawings
FIG. 1 is a schematic step diagram of a method for manufacturing a high-performance aluminum alloy cylindrical forging for aerospace;
FIG. 2 is a schematic view of the structure of the billet prior to the backward extrusion process;
FIG. 3 is a schematic view of the structure of the billet after the backward extrusion process;
FIG. 4 is a metallographic micrograph of sample 1;
fig. 5 is a metallographic micrograph of sample 2.
In the figure 1, an upper die; 2. and (5) a lower die.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Example (b): a manufacturing method of a high-performance aluminum alloy cylindrical forging for aerospace comprises the following steps as shown in figure 1:
s1, blanking: blanking on the aluminum alloy cast ingot according to the size specification to obtain a blank, wherein the size of the blank is phi 600 multiplied by 1240 mm.
S2, forging and heating: and (3) putting the blank into a heating furnace for heating by a worker, heating the blank to 440-470 ℃, and then preserving the heat of the blank for 20-25 h.
S3, blank making: upsetting and drawing twice by a wide anvil strong pressing forging method along the axial direction of the blank, forming the blank into a round cake piece, wherein the deformation of the blank in single upsetting and drawing is more than or equal to 65 percent and the forming size of the blank is phi 705 multiplied by 900 mm.
S4, returning: and returning the blank to the furnace and heating to 420-440 ℃, and preserving the heat of the blank for 4-7 h after the blank reaches the specified temperature.
S5, backward extrusion: preparing a special die, wherein the special die comprises an upper die 1 and a lower die 2, the upper die 1 is arranged on a punch head of a punching machine, as shown in figure 2, the lower die 2 is arranged on an anvil of the punching machine, a blank is put into the lower die 2, then as shown in figure 3, the upper die 1 is pressed downwards on the blank to punch a hole, the height of the blank is increased, the back extrusion of the blank is completed, and the forming size of the blank is to phi 705 x phi 360 x 1200 mm.
The axial streamline of the blank is changed into the direction of the forced streamline by the backward extrusion of the blank, the axial performance can be greatly improved, the deformation mode does not cause forging compression damage to the radial direction, the radial performance is improved to the maximum extent, meanwhile, the overall deformation of the blank is uniform and consistent in the deformation process, the organization is guaranteed to be uniform and consistent, and the final mechanical performance of the blank in all directions is guaranteed to be uniform and consistent.
S6, cleaning: cleaning an inner hole and a bottom plate of the blank, and sizing the blank: phi 705 x phi 380 x 1200 mm.
S7, returning and heating: and (3) placing the blank cleaned in the step (S6) in a heating furnace, heating to 420-440 ℃, and then preserving heat for 4-8 h. The heating increases the plasticity of the blank, and facilitates the subsequent processing deformation.
S8, ring rolling: and (4) rolling the blank into a ring, wherein the size of the blank is phi 1040 multiplied by phi 860 multiplied by 1200mm, and the blank is in a high cylinder shape.
S9, solution treatment: and heating the blank to 500-530 ℃, then preserving heat for 6-10 h, discharging the blank from a furnace, cooling by water, keeping the water at 40-65 ℃, and keeping the water in for 20-40 min.
S10, aging treatment: and heating the blank to 140-175 ℃, then preserving heat for 5-12 h, and after preserving heat, discharging the blank out of the furnace and air-cooling to room temperature.
S11, sampling and detecting: the blank is sampled to be 100mm high along the axial direction, and the performance is carried out on the ring piece in three directions. And (6) detecting.
S12, machining: the blank was machined to dimensions phi 1020 x phi 880 x 1050 mm.
S13, ultrasonic flaw detection: and carrying out ultrasonic flaw detection on the blank.
Aluminum alloy detection: the detection results of the aluminum alloy forging are shown in table 1.
| Item | Sample No. 1 | Sample No. 2 | Standard of merit |
| Tensile strength (Mpa) | 486 | 511 | ≥450Mpa |
| Yield strength (Mpa) | 433 | 455 | ≥380Mpa |
| Elongation (%) | 8 | 8 | 6～14％ |
| Ultrasonic flaw detection | Class A | Class A | GJB1580A-2004 |
Table 1.
And (3) metallographic detection: the microscopic gold phase diagram of sample 1 is shown in FIG. 4, and the microscopic gold phase diagram of sample 2 is shown in FIG. 5.
And (4) conclusion: the alloy structure has no fracture defects, and the grain structure is fine and dense.
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 (7)
1. The manufacturing method of the high-performance aluminum alloy cylindrical forging for aerospace is characterized by comprising the following steps:
s1, blanking: blanking on the aluminum alloy ingot according to the size specification to obtain a blank;
s2, forging and heating: placing the blank in a heating furnace, heating to 440-470 ℃, and preserving heat for 20-25 h;
s3, blank making: upsetting and drawing twice along the axial direction of the blank to form a round cake piece;
s4, returning: returning the blank to the furnace for heating, raising the temperature to 420-440 ℃, and preserving the heat for 4-7 hours;
s5, backward extrusion: punching the blank, increasing the axial height of the blank, then carrying out backward extrusion on the blank, and then air-cooling the blank to room temperature;
s6, cleaning: cleaning an inner hole and a bottom plate of the blank;
s7, returning and heating: placing the blank cleaned in the step S6 in a heating furnace, heating to 420-440 ℃, and preserving heat for 4-8 h;
s8, ring rolling: rolling the blank into a ring;
s9, solution treatment: heating the blank to 500-530 ℃, then preserving heat, taking the blank out of a furnace, cooling by water, keeping the water temperature at 40-65 ℃, and keeping the water in for 20-40 min;
s10, aging treatment: heating the blank to 140-175 ℃, then preserving heat, discharging the blank out of the furnace, and air-cooling to room temperature.
2. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight according to claim 1, wherein the method comprises the following steps: in step S3, the deformation of each single upsetting of the billet is more than or equal to 65 percent.
3. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight as claimed in claim 2, wherein the method comprises the following steps: in step S3, the blank is formed to a size Φ 705 × 900 mm.
4. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight according to claim 1, wherein the method comprises the following steps: in step S5, the dimensions of the billet are back-extruded to Φ 705 × Φ 360 × 1200 mm.
5. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight according to claim 1, wherein the method comprises the following steps: in step S8, the billet is ring sized to Φ 1040 × Φ 860 × 1200 mm.
6. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight according to claim 1, is characterized in that: in step S9, the temperature is maintained for 6-10 h.
7. The method for manufacturing the high-performance aluminum alloy cylindrical forging for spaceflight according to claim 1, is characterized in that: in step S10, the temperature is maintained for 5-12 h.
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| CN202010519097.2A CN112264565A (en) | 2020-06-09 | 2020-06-09 | Manufacturing method of high-performance aluminum alloy cylindrical forging for spaceflight |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113635000A (en) * | 2021-08-27 | 2021-11-12 | 中国兵器工业第五九研究所 | Extrusion-rolling composite forming method for magnesium alloy ring piece |
| CN114393160A (en) * | 2021-12-02 | 2022-04-26 | 北京航空航天大学 | Preparation method of aluminum alloy extruded material |
| CN115106396A (en) * | 2022-07-20 | 2022-09-27 | 陕西长羽航空装备股份有限公司 | Blank making device of titanium alloy deep cylinder and extrusion-rolling forming method using same |
| CN115608891A (en) * | 2022-09-30 | 2023-01-17 | 中南大学 | Method and device for manufacturing special-shaped section transition ring of rocket tank |
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| CN115608891A (en) * | 2022-09-30 | 2023-01-17 | 中南大学 | Method and device for manufacturing special-shaped section transition ring of rocket tank |
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Application publication date: 20210126 |