CN115138799A - Homogenization forging-modifying method for large-sized easy-cracking high-temperature alloy for aviation - Google Patents
Homogenization forging-modifying method for large-sized easy-cracking high-temperature alloy for aviation Download PDFInfo
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- CN115138799A CN115138799A CN202211067087.5A CN202211067087A CN115138799A CN 115138799 A CN115138799 A CN 115138799A CN 202211067087 A CN202211067087 A CN 202211067087A CN 115138799 A CN115138799 A CN 115138799A
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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
- 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
- B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular 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
- B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular operations
- B21J5/08—Upsetting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K29/00—Arrangements for heating or cooling during processing
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Abstract
The invention discloses a homogenizing forging-modifying method for a large-scale easy-cracking high-temperature alloy for aviation, which belongs to the technical field of forging processes and comprises the steps of S1 heating a blank; s2, carrying out quick pressing treatment along the Z-axis direction of the blank; s3, drawing out the blank along the Z-axis direction; s4, upsetting along the Z-axis direction of the blank; s5, drawing out the blank along the X axial direction; s6, upsetting along the X axial direction of the blank; s7, drawing out along the Y-axis direction of the blank; s8, upsetting along the Y-axis direction of the blank; s9, drawing out the blank along the Z-axis direction; s10, upsetting along the Z-axis direction of the blank; s11, drawing out the blank in the Z-axis direction in eight directions; s12, rolling and drawing the blank to a forming size by adopting a V-shaped anvil. The invention carries out re-forging on the large-scale easy-cracking high-temperature alloy bar material for aviation, improves the mechanical property and the microstructure of the forged piece, and avoids the problem of easy cracking of the forged piece in the re-forging process.
Description
Technical Field
The invention belongs to the technical field of forging processes, and particularly relates to a homogenization forging-modifying method for a large-scale easy-cracking high-temperature alloy for aviation.
Background
The large-scale high-temperature alloy material has good fuel gas corrosion resistance, higher yield strength and fatigue performance. With the rapid development of the aerospace industry, the modern national defense industry and the transportation industry at home and abroad, the requirement of large-sized high-temperature alloy forgings for aerospace is more and more vigorous, and the high-temperature alloy forgings are developed from the original segmented welding to integration and large-scale. However, the large-scale high-temperature alloy material is easy to generate ductile cracks in the processing process, and the product quality is seriously influenced. Therefore, in order to obtain a high-temperature alloy with qualified and uniform mechanical properties and microstructure, the quality of a product needs to be improved by a forging modification method, and meanwhile, the problem that a forging piece is cracked in the forging modification process is reduced.
The mechanical properties of the existing nickel-based high-temperature alloy, such as GH738, are very sensitive to the control of the processing technology, and phenomena of coarse grains, mixed grains and the like can be generated when the processing process is controlled improperly, so that the fatigue property, the durability, the notch sensitivity, the impact toughness and the like of an alloy product are influenced.
The traditional forging method has the following technical defects:
(1) After the forge piece is discharged from the furnace, the initial forging temperature is reduced quickly due to the limitation of transfer time, and in addition, the forge piece specification is larger, the deformation amount of single-fire forging change is less, and the forging fire number needs to be increased.
(2) Because the actual forging temperature range is narrow, the deformation of each fire time of forging modification is small, and crystal grains cannot be effectively crushed, the effect of the forging modification mode of reducing the temperature piece by using the small deformation of multiple fire times on the thinning of the crystal grains is small, and the improvement on the mechanical property and the microstructure of a forged piece is small.
(3) Because the finish forging temperature is lower, ductile cracks are easy to appear on the forged piece when the pressing is too large, and the product quality and the production progress are seriously influenced.
(4) At present, large-sized bars provided by raw material manufacturers only guarantee chemical components of raw materials, mechanical properties and flaw detection are not guaranteed, and great risks are brought to the final mechanical properties and flaw detection of forgings.
For the technical defects, forging manufacturers and raw material manufacturers at home and abroad do not have good solutions at present.
Disclosure of Invention
Aiming at the problems in the prior art, the invention discloses a large easy-cracking high-temperature alloy homogenization forging-modifying method for aviation, which is used for modifying and forging large easy-cracking high-temperature alloy bars for aviation, improving the mechanical property and microstructure of forgings and avoiding the problem of easy cracking of the forgings in the forging-modifying process.
The technical purpose of the invention is realized by the following technical scheme:
a large-scale easy-cracking high-temperature alloy homogenization forging-modifying method for aviation comprises the following specific steps:
s1, heating a blank: heating the blank to 200 ℃, coating a heat-preservation coating on the surface of the blank, putting the blank into a furnace, heating the blank to 1150-1200 ℃, preserving heat for 12-15h, and discharging the blank out of the furnace for hot-covering treatment;
s2, carrying out quick pressing treatment along the Z-axis direction of the blank, controlling the Z-axis deformation of the blank within the range of 35-40%, returning to the furnace to heat the blank to 1120-1150 ℃, preserving heat for 8-6h, and then discharging from the furnace to carry out hot covering treatment;
s3, drawing out the blank along the Z-axis direction, controlling the Z-axis deformation of the blank within the range of 30% -35%, returning to the furnace, heating the blank to 1120-1150 ℃, preserving heat for 4-6h, and then discharging from the furnace for hot covering treatment;
s4, upsetting along the Z-axis direction of the blank, controlling the X-axis deformation of the blank within the range of 35-40%, returning to the furnace to heat the blank to 1080-1110 ℃, preserving heat for 6-8 hours, and then discharging from the furnace to perform hot covering treatment;
s5, drawing out the blank along the X axial direction, controlling the X axial deformation of the blank within the range of 35-40%, returning to the furnace, heating the blank to 1080-1110 ℃, preserving heat for 4-6 hours, and then discharging from the furnace for hot covering treatment;
s6, upsetting along the X axial direction of the blank, controlling the Y axial deformation of the blank to be within the range of 35-40%, returning to the furnace to heat the blank to 1050-1080 ℃, preserving heat for 6-8 hours, and then discharging from the furnace to perform hot covering treatment;
s7, drawing out the blank along the Y-axis direction, controlling the Y-axis deformation of the blank within the range of 35% -40%, returning to the furnace to heat the blank to 1050-1080 ℃, keeping the temperature for 4-6h, and then discharging from the furnace to perform hot covering treatment;
s8, upsetting along the Y axial direction of the blank, controlling the Z axial deformation of the blank within the range of 35-40%, returning to the furnace, heating the blank to 1020-1050 ℃, keeping the temperature for 6-8h, and then discharging from the furnace for hot-covering treatment;
s9, drawing out the blank along the Z-axis direction, controlling the Z-axis deformation of the blank within the range of 35% -40%, returning to the furnace, heating the blank to 1020 ℃ -1050 ℃, preserving heat for 4-6h, and then discharging from the furnace for hot covering treatment;
s10, upsetting along the Z-axis direction of the blank, controlling the Z-axis deformation of the blank within the range of 35-40%, returning to the furnace to heat the blank to 1000-1030 ℃, preserving heat for 6-8 hours, and then discharging from the furnace to perform hot covering treatment;
s11, drawing out the blank in the Z-axis direction in eight directions, controlling the Z-axis deformation of the blank within the range of 30% -35%, upsetting along the Z-axis, controlling the deformation within the range of 35% -40%, returning the blank to the furnace, heating the blank to 1000-1030 ℃, keeping the temperature for 6-8h, then discharging the blank out of the furnace, performing hot covering treatment, and repeating the step S11 once;
s12, rolling and drawing the blank to a forming size by adopting a V-shaped anvil.
Preferably, the thermal wrap treatment is specifically operated as follows: and (4) after the blank is discharged from the furnace, wrapping heat preservation cotton on the surface of the blank for hot covering, and then returning the blank to the furnace for heat preservation for 1-2 hours.
Preferably, the transfer time from tapping to forging in each step is less than or equal to 15s.
Preferably, the finish forging temperature in each step is greater than or equal to 930 ℃.
Has the beneficial effects that: the invention discloses a large-scale easy-cracking high-temperature alloy homogenizing forging-modifying method for aviation, which has the following advantages:
(1) According to the invention, the problem of low initial forging temperature caused in the transfer process is compensated by increasing the charging temperature and performing hot-pack sleeve treatment, the required capacity of equipment is reduced, larger deformation can be obtained, and the possibility of crack occurrence is greatly reduced.
(2) Three-direction upsetting and drawing are adopted, upsetting and drawing times are increased, forging crystal grains can be fully crushed, finer forging crystal grains are obtained, and the mechanical property and the microstructure of the forging are improved.
(3) The invention is beneficial to finishing dynamic recrystallization by controlling the finish forging temperature to be stable at a certain temperature, thereby controlling the grain size and the tissue uniformity.
(4) The invention can control the forging deformation amount to be 35-40% in each forging step, improves the deformation amount of each heating time, is beneficial to effectively crushing crystal grains, and improves the mechanical property and the microstructure of the forged piece.
Drawings
FIG. 1 is a schematic view of the grain size at 1/2 radius of a bar before swaging in example 1;
FIG. 2 is a schematic view of the grain size at 1/2 radius of a bar after being forged in example 1;
FIG. 3 is a schematic diagram showing the grain size at the center of the bar after the forging of example 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. The following description of the embodiments is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses.
Example 1
The blank I is a high-temperature alloy GH738, the initial size of the blank I before forging is phi 600 multiplied by 800, and the size units mentioned in the embodiment are all mm.
The specific forging method of the blank I is as follows:
s1, heating a blank I to 200 ℃, coating a heat preservation coating on the surface of the blank I, putting the blank I into a furnace, heating to 1200 ℃, preserving heat for 14 hours, taking the blank out of the furnace, wrapping heat preservation cotton on the surface of the blank I after the blank is taken out of the furnace, carrying out hot sheathing, returning the blank to the furnace, preserving heat for 1 hour, and transferring and forging the blank, wherein the transfer time is less than or equal to 15S;
s2, performing rapid pressing treatment along an IZ axis of the blank until the size of the blank I is phi 725 multiplied by 550, returning to the furnace to heat the blank I to 1120-1150 ℃, preserving heat for 7 hours, then discharging from the furnace to perform hot sheathing, returning to the furnace to preserve heat for 1 hour;
s3, drawing out along an IZ axis of the blank until the size of the blank I is 500 multiplied by 900, returning to the furnace to heat the blank I to 1150 ℃, keeping the temperature for 5 hours, discharging from the furnace to perform hot covering treatment, and returning to the furnace to keep the temperature for 1 hour;
s4, upsetting along an IZ axis of the blank until the size of the blank I is 615 multiplied by 600, returning to the furnace to heat the blank I to 1110 ℃, keeping the temperature for 7 hours, then taking out of the furnace to carry out hot sheathing, and returning to the furnace to keep the temperature for 1 hour;
s5, drawing the blank IX along the axis until the size of the blank I is 900 multiplied by 500, returning to the furnace to heat the blank I to 1110 ℃, keeping the temperature for 5 hours, then taking the blank out of the furnace to carry out hot sheathing, and returning to the furnace to keep the temperature for 1 hour;
s6, upsetting along the stock IX shaft until the size of the stock I is 600 multiplied by 615, returning to the furnace to heat the stock I to 1080 ℃, keeping the temperature for 7 hours, taking out of the furnace to carry out hot sheathing, and returning to the furnace to keep the temperature for 1 hour;
s7, drawing the blank along an IY axis of the blank until the size of the blank I is 500 multiplied by 900 multiplied by 500, returning to the furnace to heat the blank I to 1080 ℃, keeping the temperature for 5 hours, then taking the blank out of the furnace to carry out hot sheathing, and returning to the furnace to keep the temperature for 1 hour;
s8, upsetting along an IY axis of the blank until the size of the blank I is 615 multiplied by 600 multiplied by 615, returning to the furnace to heat the blank I to 1050 ℃, keeping the temperature for 7 hours, then discharging from the furnace to perform hot covering treatment, and returning to the furnace to keep the temperature for 1 hour;
s9, drawing along an IZ axis of the blank until the size of the blank I is 500 multiplied by 900, returning to the furnace to heat the blank I to 1050 ℃, keeping the temperature for 5 hours, discharging from the furnace to perform hot covering treatment, and returning to the furnace to keep the temperature for 1 hour;
s10, upsetting along an IZ axis of the blank until the size of the blank I is 615 multiplied by 600, returning to the furnace to heat the blank I to 1030 ℃, keeping the temperature for 7 hours, discharging from the furnace to perform hot covering treatment, and returning to the furnace to keep the temperature for 1 hour;
s11, drawing out the blank I in the axial direction of the blank IZ in eight directions until the size of the blank I is \9633, 580X 900 and the deformation amount is 35 percent, upsetting the blank I in the axial direction of Z until the size of the blank I is \9633, 650X 600 and the deformation amount is 35 percent, returning the blank I to 1030 ℃, keeping the temperature for 7 hours, then taking out the blank, covering the blank, returning the blank to the furnace, keeping the temperature for 1 hour, and then repeating the step once;
s13, rolling and drawing the blank I to a forming size phi of 600 multiplied by 800 by adopting a V-shaped anvil.
(1) Mechanical Property test
The bar before and after re-forging of example 1 was subjected to mechanical tests by taking samples at two different positions, sample number 1 (end) and sample number 2 (1/2 radius), and room temperature stretching and high temperature stretching (540 ℃) were carried out, and the specific test results are shown in table 1.
TABLE 1 results of mechanical testing of the samples
As shown in Table 1, the tensile strength of the material after the hot forging was superior to that before the hot forging, particularly the elongation at break and the end face shrinkage after the hot forging, both at room temperature and at high temperature (540 ℃).
(2) Grain size test
As shown in FIG. 1, the grain size of the blank I at 1/2 of the radius before forging is larger, the grain size is not uniform, and the grain size is only 2 grade.
As shown in FIG. 2, the grain size of the billet I at the radius of 1/2 after forging is shown, and the original cast grain structure is fully crushed, the grain refining effect is remarkable, and the grain size reaches 5 grades. This is because the embodiment 1 improves the deformation amount of each firing, and adopts three-way alternating upsetting to make the blank deformation direction change vertically and alternately, thereby avoiding the formation of linearly distributed carbides, causing the carbides to be distributed dispersedly, promoting the grain refinement, and improving the fatigue resistance of the alloy.
As shown in fig. 3, which is a schematic diagram of the grain size at the center of the billet I after the forging process is performed, it can be found from the diagram that the grain structure at the center of the billet I is sufficiently crushed, the shape of the grain is uniform, and the grain size reaches 6 levels, which indicates that the forging process of example 1 can ensure that the grain structures at different positions of the billet can be uniformly and sufficiently crushed, uniform grain fineness can be obtained, and the uniformity of the mechanical properties of the billet can be ensured.
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 (4)
1. A large-scale easy-cracking high-temperature alloy homogenization forging-modifying method for aviation is characterized by comprising the following specific steps:
s1, heating a blank: heating the blank to 200 ℃, coating a heat-preservation coating on the surface of the blank, putting the blank into a furnace, heating the blank to 1150-1200 ℃, preserving heat for 12-15h, and taking the blank out of the furnace to perform hot covering treatment;
s2, carrying out rapid pressing treatment along the Z-axial direction of the blank, controlling the Z-axial deformation of the blank within the range of 35-40%, returning to the furnace, heating the blank to 1120-1150 ℃, keeping the temperature for 6-8h, and then discharging from the furnace for hot covering treatment;
s3, drawing out the blank along the Z-axis direction, controlling the Z-axis deformation of the blank within the range of 30% -35%, returning to the furnace, heating the blank to 1120-1150 ℃, preserving heat for 4-6h, and then discharging from the furnace for hot covering treatment;
s4, upsetting along the Z-axis direction of the blank, controlling the X-axis deformation of the blank within the range of 35-40%, returning to the furnace to heat the blank to 1080-1110 ℃, preserving heat for 6-8 hours, and then discharging from the furnace to perform hot covering treatment;
s5, drawing out the blank along the X axial direction, controlling the X axial deformation of the blank within the range of 35-40%, returning to the furnace, heating the blank to 1080-1110 ℃, preserving heat for 4-6 hours, and then discharging from the furnace for hot covering treatment;
s6, upsetting along the X axial direction of the blank, controlling the Y axial deformation of the blank to be within the range of 35-40%, returning to the furnace to heat the blank to 1050-1080 ℃, preserving heat for 6-8 hours, and then discharging from the furnace to perform hot covering treatment;
s7, drawing out the blank along the Y-axis direction, controlling the Y-axis deformation of the blank within the range of 35% -40%, returning to the furnace, heating the blank to 1050-1080 ℃, keeping the temperature for 4-6h, and then discharging from the furnace for hot covering treatment;
s8, upsetting along the Y axis of the blank, controlling the Z axis deformation of the blank within the range of 35-40%, returning to the furnace to heat the blank to 1020-1050 ℃, preserving heat for 6-8h, and then discharging from the furnace to perform hot covering treatment;
s9, drawing out the blank along the Z-axis direction, controlling the Z-axis deformation of the blank within the range of 35% -40%, returning to the furnace, heating the blank to 1020 ℃ -1050 ℃, preserving heat for 4-6h, and then discharging from the furnace for hot covering treatment;
s10, upsetting along the Z-axis direction of the blank, controlling the Z-axis deformation of the blank within the range of 35-40%, returning to the furnace, heating the blank to 1000-1030 ℃, keeping the temperature for 6-8 hours, and discharging from the furnace for hot-covering treatment;
s11, drawing out the blank in the Z-axis direction in eight directions, controlling the Z-axis deformation of the blank within the range of 30% -35%, upsetting along the Z-axis, controlling the deformation within the range of 35% -40%, returning the blank to the furnace, heating the blank to 1000-1030 ℃, keeping the temperature for 6-8h, then discharging the blank out of the furnace, performing hot covering treatment, and repeating the step S11 once;
s12, rolling and drawing the blank to a forming size by adopting a V-shaped anvil.
2. The large-scale easy-cracking superalloy homogenization forging method for aviation according to claim 1, wherein the method comprises the following steps: the thermal sheathing treatment specifically operates as follows: and (4) after the blank is discharged from the furnace, wrapping heat preservation cotton on the surface of the blank for thermal sheathing, and then returning the blank to the furnace for heat preservation for 1-2 hours.
3. The large-scale easy-cracking superalloy homogenizing and forging method for aviation according to any one of claims 1-2, wherein: the transfer time from discharging to forging in each step is less than or equal to 15s.
4. The large easy-cracking superalloy homogenizing and forging method for aviation according to claim 1, wherein the method comprises the following steps: the finish forging temperature in each step is more than or equal to 930 ℃.
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| CN202211067087.5A CN115138799A (en) | 2022-09-01 | 2022-09-01 | Homogenization forging-modifying method for large-sized easy-cracking high-temperature alloy for aviation |
| CN202211307794.7A CN115971384A (en) | 2022-09-01 | 2022-10-24 | Large-scale easy-cracking high-temperature alloy homogenizing forging-modifying method for aviation |
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| CN202211307794.7A Pending CN115971384A (en) | 2022-09-01 | 2022-10-24 | Large-scale easy-cracking high-temperature alloy homogenizing forging-modifying method for aviation |
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| CN116603963A (en) * | 2023-05-24 | 2023-08-18 | 陕西长羽航空装备股份有限公司 | Upsetting method for high-temperature alloy with large height-diameter ratio |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116603963A (en) * | 2023-05-24 | 2023-08-18 | 陕西长羽航空装备股份有限公司 | Upsetting method for high-temperature alloy with large height-diameter ratio |
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Application publication date: 20221004 |