CN111235502A - Production method of large-size nickel-based high-temperature alloy forging - Google Patents
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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
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
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- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
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Abstract
A production method of a large-size nickel-based superalloy forging piece comprises the steps of preparing a blank, grinding and blanking, heating and preserving heat, isothermal forging and machining, wherein an isothermal forging technology is adopted, technological parameters such as the height-diameter ratio of the blank, the forging temperature, the deformation rate and the like are controlled, the temperature of a die is controlled within a certain range, the temperature drop of the blank is effectively reduced, excessive delta phase precipitation is further avoided, and meanwhile, the grain structure can be effectively refined under the condition of large deformation; the produced product meets the specification of a turbine for an aerospace engine and a ship
The GH4169 alloy (In 718) forging has excellent strength, durability and good toughness.
Description
Technical Field
The invention belongs to the field of forging of nickel-based alloys, and particularly relates to a production method of a large-size nickel-based high-temperature alloy forging.
Background
The high-temperature alloy is a key metal structure material required in the fields of modern aerospace engines, ship gas turbines and the like, can bear large stress and can be used for a long time under the conditions of high-temperature environment (generally 600-1100 ℃), oxidation and gas corrosion. Due to different use conditions, the performance requirements of different parts are greatly different, wherein the service environment of the engine rotating parts is the most severe and the performance requirements are the most strict.
Taking the current high-thrust space engine as an example, the GH4169 alloy is selected as the material of the turbine disk. Considering the aspects of design and use conditions, the engine turbine disc forging is required to have high strength, high durability and good impact toughness. Although the GH4169 alloy is widely applied to the fields of aircraft engines, gas turbines and the like, the indexes of the performance such as the heavy strength, the durability, the creep deformation and the like are mainly considered, and the comprehensive assessment strength and the toughness index are few. Therefore, how to balance and solve the two indexes of "strength" and "toughness" is one of the challenges in developing and developing the forging.
In addition, with the continuous development of the aerospace engine technology, the thrust is continuously improved, and the size of engine parts is required to be continuously increased and is developed to be large. The size of the new generation of engine disc forging is increased by more than 1 time than that of the prior engine disc forging, the diameter of the new generation of engine disc forging reaches phi 300mm, and the thickness of the new generation of engine disc forging is about 130 mm. With the increase of the size of the forging, higher requirements are provided for the control of the structure and the performance, and the manufacturing difficulty is multiplied, so that how to solve the manufacturing problem caused by the size effect, and the preparation of the forging with the structure and the performance meeting the requirements becomes one of the bottlenecks restricting the development of the aerospace engine in China.
Studies have shown that GH4169 alloys achieve high strength, high durability and good impact toughness, and are generally controlled primarily from two aspects: 1) fine crystal structure: the grain refinement is an effective means for improving the room temperature and high temperature strength of the material and improving the toughness of the material, and is especially important for the GH4169 alloy with high strength and high toughness; 2) controlling the delta phase: a certain amount of delta phase is precipitated in the alloy structure, so that the notch sensitivity of the alloy can be improved, and the endurance quality of the alloy can be improved. However, the δ -phase precipitation content is too large, and is not favorable for the impact properties of the alloy. Therefore, in actual production, it is necessary to control the finish forging temperature so as to avoid excessive or insufficient precipitation of the δ phase. At present, the traditional process route for producing the alloy forging is free forging or air hammer forging. The production process parameters are as follows: heating temperature of the blank: 1040-1060 ℃, the reduction of 30-40 mm and the finish forging temperature of more than or equal to 900 ℃.
During production, firstly, a fast forging machine is adopted to forge a blank with a certain specification, then, the blank is blanked in a fixed length mode, the blank is forged and pressed into a blank forging piece with a specification close to a finished product specification through an air hammer, and then, the blank is machined to the finished product specification. By adopting the process route, the production efficiency is often lower, the material yield is low, and due to the longer forging time and the low finish forging temperature (the finish forging temperature is often lower than 900 ℃), the problem that the impact property of the forged piece is not satisfactory often occurs. In addition, the limit specification of the forging manufacturing is still small at present due to the limitation of the production mode. Therefore, it is very important to design and develop a process route capable of producing large-specification forgings meeting performance requirements.
The Chinese invention patent CN101153360A introduces a preparation method of a large-size high-temperature alloy round cake. The method directly carries out upset cake on the homogenized alloy steel ingot after fixed-length blanking. However, the patent only aims at the alloy which is difficult to deform, such as GH105, and does not relate to the requirements of the performance of the cake, so the patent has no reference significance.
The Chinese invention patent CN1165204A describes a method for obtaining uniform ultrafine grain by nickel-based superalloy forgings and bars. The method is characterized in that a certain amount of delta phase is precipitated in advance, and then the delta phase is spheroidized through hot working, so that an ultra-fine grain structure is obtained. If the method is adopted to prepare the disc, the impact property of the disc cannot meet the requirement, so the method still has no reference significance.
Disclosure of Invention
The invention aims to provide a production method of a large-specification nickel-based high-temperature alloy forging piece, which is suitable for GH4169 alloy (In 718 abroad), adopts an isothermal forging technology, and produces the large-specification high-performance forging piece with high strength, high durability and good impact toughness by controlling the technological parameters such as the height-diameter ratio of a blank, the forging temperature, the deformation rate and the like, and is mainly applied to the aerospace field, large-scale ship engine rotating parts and the like, and relates to the key fields of national defense, civil use and the like.
In order to achieve the purpose, the invention provides the following technical scheme:
a production method of a large-specification nickel-based superalloy forging comprises the following steps:
1) preparation of the blanks
Preparing a blank with a required specification by adopting a quick forging or radial forging process, wherein the grain size of the blank tissue is 4-6 grades;
2) grinding and blanking
Polishing the surface of the blank, and blanking according to the requirement of the deformation ratio, wherein the height-diameter ratio of the blank is controlled to be 2.2-2.5;
3) heating and heat preservation
Putting the blank into a heating furnace with the temperature less than or equal to 600 ℃, starting to heat up, and at least 5 hours are needed for heating up from 600 ℃ to 950 +/-10 ℃; keeping the furnace temperature for at least more than 2 hours after the furnace temperature reaches 950 +/-10 ℃; then heating to 990-1050 ℃ for at least 1h, and keeping for at least 3h after the temperature is reached;
4) isothermal forging
Transferring the blank onto a press, adjusting the position, then starting pressing, pressing the blank into a disc forging piece, controlling the deformation rate at 20-30 mm/s, forming the blank by one fire, and cooling the blank by air after forging;
5) machining
And 4) machining the disc forging obtained in the step 4) to obtain the nickel-based high-temperature alloy forging with the surface state and the dimensional specification meeting the requirements.
Preferably, the blank in step 1) is a GH4169 alloy.
Further, in the step 1), the size specification of the blank is phi 200 x (440-480) mm, and the specification of the nickel-based superalloy forging is phi 200 x (440-480) mm
Preferably, the nickel-based high temperatureThe room-temperature tensile strength Rm of the alloy forging is more than or equal to 1360MPa, Rp0.2 is more than or equal to 1120MPa, and the room-temperature impact energy AKU2Not less than 42J; the tensile strength Rm at 600 ℃ is more than or equal to 1140MPa, and Rp0.2 is more than or equal to 945 MPa; the structure is uniform and fine, and the grain size is 6-8 grade.
When the blank is prepared, the blank with the required specification is prepared by adopting a conventional quick forging or radial forging process, and the requirements on the blank structure are as follows: the grain size is ensured to reach 4-6 levels, the requirement on the grain size of the blank is necessary, and if the grain structure of the blank is uneven or coarse, the grain of a subsequent forge piece is coarse or residual coarse grains exist, so that the mechanical property of the forge piece is influenced.
According to the invention, the height-diameter ratio of the blank is controlled to be 2.2-2.5, so that the blank has enough deformation ratio, and the sufficient refinement of the forging structure is realized; according to the invention, the surface of the intermediate blank is ground to remove the defects of surface cracks and the like, and then the fixed-length blanking is carried out according to the requirement of the deformation ratio, so that the problem of surface cracking in the die forging process can be effectively avoided.
When the disc is pressed by isothermal forging, the deformation rate is controlled to be 20-30 mm/s, if the pressing is too fast, the temperature rise in the blank is easy to be high, and the fine grain structure is not easy to obtain; if the pressing is too slow, the tissue recrystallization is not easy to complete, which is not favorable for tissue refinement.
According to the invention, a set of stable, efficient and feasible large-size forge piece production process flow is created by optimally controlling three aspects of blank organization, height-diameter ratio design and deformation rate and combining an isothermal forging technology. In the actual production process, the uniformity of the temperature from the center of the blank to the edge can be ensured by the isothermal forging technology, and particularly, the loss of the temperature at the edge is reduced; in addition, the deformation rate in the whole forging process is controllable, and the internal structure of the forging is fully recrystallized by combining with the design of larger deformation, so that the purpose of refining crystal grains is realized, and simultaneously, a proper amount of delta phase is ensured to be precipitated in the structure. Finally, the maximum specification of the produced forging reaches phi 300 multiplied by 130mm, and the structure performance completely meets the requirements.
Compared with the prior art, the invention has the following beneficial effects:
the invention adopts the isothermal forging technology, controls the temperature of the die within a certain range by controlling the technological parameters of the blank such as the height-diameter ratio, the forging temperature, the deformation rate and the like, can effectively reduce the temperature drop of the blank, further avoid excessive separation of delta phase, and can effectively refine the grain structure under larger deformation; the produced GH4169 alloy forging piece for the aerospace engine and the ship steam turbine has excellent strength, durability and toughness.
The forging obtained by the method has high strength, long service life and excellent impact toughness, and solves the problem that the GH4169 alloy high-strength forging has low impact toughness; moreover, the size of the developed forging reaches phi 300 multiplied by 130mm, the maximum specification in the domestic aerospace field is reached, and the development of the aerospace engine technology in China is powerfully supported.
Drawings
FIG. 1 is a view showing the grain structure of an intermediate ingot in an embodiment 1 of the present invention at 100 times.
FIG. 2 is a 500-fold view of the grain structure of the intermediate ingot in example 1 of the present invention.
Fig. 3 is a graph of a heating process of the ingot in examples 1-4 of the present invention.
FIG. 4 is a schematic drawing of a longitudinal section sample of 1/4 from example 2 of the invention and a forging of a comparative example.
FIG. 5 is a photograph of the center structure of a forging of example 2 of the present invention.
FIG. 6 is an R/2 structure photograph of a forging of example 2 of the present invention.
FIG. 7 is a photograph of the edge structure of a forging of example 2 of the present invention.
FIG. 8 is a photograph of the center structure of a comparative example forging.
FIG. 9 is a photograph of the R/2 texture of a comparative example forging.
FIG. 10 is a photograph of the edge structure of a comparative example forging.
Detailed Description
The present invention is further illustrated by the following specific examples.
Embodiment 1 the invention relates to a production method of a large-size nickel-based superalloy forging, which comprises the following steps:
the GH4169 alloy blank is prepared by adopting a conventional rapid forging process, the grain structure of the blank reaches 5 grades or finer, and the grain structure photos of the intermediate blank are shown in figures 1-2.
Grinding the surface of the blank, then cutting to length, wherein the size of the blank is phi 200 multiplied by 440mm, and the height-diameter ratio is 2.2.
The blank is put into a heating furnace for heating, the heating process is shown in figure 3, and the heat preservation temperature is 1040 ℃.
After the blank is heated, the blank is quickly transferred to a press, and the position of the blank is adjusted to ensure that the upper end surface and the lower end surface of the blank are parallel; and pressing the disc piece at the deformation rate of 20mm/s, controlling the deformation according to the height, and immediately taking out the deformed forging piece for air cooling.
The forged blank has poor surface state and size specification which can not meet the use requirement, the surface of the blank is machined, and the finished product size after polishing is as follows: phi 300X 130 mm.
the GH4169 alloy blank is prepared by adopting a radial forging process, and the grain structure of the blank reaches 5 grades or finer.
Grinding the surface of the blank, then cutting to length, wherein the size of the blank is phi 200 multiplied by 480mm, and the height-diameter ratio is 2.4.
The blank is put into a heating furnace for heating, the heating process is shown in figure 3, and the heat preservation temperature is 1000 ℃.
After the blank is heated, the blank is quickly transferred to a press, and the position of the blank is adjusted to ensure that the upper end surface and the lower end surface of the blank are parallel; the disk was pressed at a deformation rate of 20mm/s, and the amount of deformation was controlled in accordance with the height. And (5) taking out the deformed forge piece immediately, and air-cooling.
The forged blank has poor surface state and size specification which can not meet the use requirement, the surface of the blank is machined, and the finished product size after polishing is as follows: phi 300X 130 mm.
Embodiment 3 the production method of the large-size nickel-based superalloy forging comprises the following steps:
the GH4169 alloy blank is prepared by adopting a rapid forging process, and the grain structure of the intermediate blank reaches 5 grades or finer.
Grinding the surface of the blank, then cutting to length, wherein the size of the blank is phi 200 multiplied by 440mm, and the height-diameter ratio is 2.2.
The blank is put into a heating furnace for heating, the heating process is shown in figure 3, and the heat preservation temperature is 1000 ℃.
After the blank is heated, the blank is quickly transferred to a press, and the position of the blank is adjusted to ensure that the upper end face and the lower end face of the blank are parallel. The disk was pressed at a deformation rate of 30mm/s, and the amount of deformation was controlled in accordance with the height. And (5) taking out the deformed forge piece immediately, and air-cooling.
The forged blank has poor surface state and size specification which can not meet the use requirement, the surface of the blank is machined, and the finished product size after polishing is as follows: phi 300X 130 mm.
Embodiment 4 the invention relates to a method for producing a large-size nickel-based superalloy forging, which comprises the following steps:
the GH4169 alloy blank is prepared by adopting a quick forging or radial forging process, the grain structure of the intermediate blank reaches 5 grades or finer, the surface of the blank is ground, and then the blank is blanked in a fixed length, wherein the size of the blank is phi 200 multiplied by 480mm, and the height-diameter ratio is 2.4.
The blank is put into a heating furnace for heating, the heating process is shown in figure 3, and the heat preservation temperature is 1020 ℃.
After the blank is heated, the blank is quickly transferred to a press, the position of the blank is adjusted, the upper end surface and the lower end surface of the blank are ensured to be parallel, the disc is pressed at the deformation rate of 20mm/s, and the deformation is controlled according to the height. And (5) taking out the deformed forge piece immediately, and air-cooling.
The forged blank has poor surface state and size specification which can not meet the use requirement, the surface of the blank is machined, and the finished product size after polishing is as follows: phi 300X 130 mm.
Comparative example
GH4169 alloy forging is produced according to the traditional process route,
the traditional process route is free forging or air hammer forging, during production, firstly a blank with a certain specification is forged by a quick forging machine, then blanking is carried out in a fixed length, the blank is forged into a blank forging piece with a specification close to a finished product specification through an air hammer, and then machining is carried out until the finished product specification is reached.
The production process parameters are as follows: heating temperature of the blank: 1040-1060 ℃, the reduction of 30-40 mm and the finish forging temperature of more than or equal to 900 ℃.
The forging pieces produced by the embodiment 2 and the comparative example are subjected to structure analysis according to the positions shown in FIG. 4, and the results of the embodiment 2 are shown in FIGS. 5-7, so that the forging pieces pressed by the process route have uniform and fine structures and the grain sizes of the forging pieces reach 6-8 levels; the structure condition of the forge piece produced according to the traditional process is shown in figures 8-10, and as can be seen from figures 8-10, the grain size of the forge piece is coarse, about 4-5 grades, and a large amount of unrecrystallized structures exist near the edge.
After the forgings produced according to the traditional process in the embodiments 1 to 4 of the invention and the comparative example are subjected to heat treatment according to the standard, the performance comparison result is shown in the table 1, wherein the conditions of the endurance test are as follows: 600 ℃/883MPa, and when the test time reaches 26h (more than 25h), the test is stopped by directly unloading.
As can be seen from Table 1, the strength and plasticity indexes of the forged piece produced by the traditional process are lower than those of the forged piece produced by the new process, and the impact property is poorer, the performance of the forged piece prepared by the process route of the invention meets the requirements, and the alloy forged piece has high strength, long service life and good impact toughness.
Claims (5)
1. A production method of a large-specification nickel-based superalloy forging comprises the following steps:
1) preparation of the blanks
Preparing a blank with a required specification by adopting a quick forging or radial forging process, wherein the grain size of the blank tissue is 4-6 grades;
2) grinding and blanking
Polishing the surface of the blank, and blanking according to the requirement of the deformation ratio, wherein the height-diameter ratio of the blank is controlled to be 2.2-2.5;
3) heating and heat preservation
Putting the blank into a heating furnace with the temperature less than or equal to 600 ℃, starting to heat up, and at least 5 hours are needed for heating up from 600 ℃ to 950 +/-10 ℃; keeping the furnace temperature for at least more than 2 hours after the furnace temperature reaches 950 +/-10 ℃; then heating to 990-1050 ℃ for at least 1h, and keeping for at least 3h after the temperature is reached;
4) isothermal forging
Transferring the blank onto a press, adjusting the position, then starting pressing, pressing the blank into a disc forging piece, controlling the deformation rate at 20-30 mm/s, forming the blank by one fire, and cooling the blank by air after forging;
5) machining
And 4) machining the disc forging obtained in the step 4) to obtain the nickel-based high-temperature alloy forging with the surface state and the dimensional specification meeting the requirements.
2. The method for producing large format nickel-base superalloy forgings according to claim 1, wherein the blank in step 1) is a GH4169 alloy.
3. The production method of the large-specification nickel-base superalloy forging according to claim 1, wherein in the step 1), the blank is 200 mm (440-480) mm in size.
4. The production method of the large-specification nickel-based superalloy forging according to claim 1, wherein the room-temperature tensile strength Rm of the nickel-based superalloy forging is equal to or more than 1360MPa, Rp0.2 of the nickel-based superalloy forging is equal to or more than 1120MPa, and the room-temperature impact energy A is equal to or more than 1120MPaKU2Not less than 42J; the tensile strength Rm at 600 ℃ is more than or equal to 1140MPa, and Rp0.2 is more than or equal to 945 MPa; the structure is uniform and fine, and the grain size is 6-8 grade.
5. The method of producing a large gauge nickel-base superalloy forging of claim 1, wherein the gauge of the nickel-base superalloy forging is 300 x 130 mm.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112139415A (en) * | 2020-09-16 | 2020-12-29 | 江苏隆达超合金航材有限公司 | Method for producing difficult-to-deform nickel-based high-temperature alloy through compensation heating assisted free forging |
| CN114378234A (en) * | 2021-09-07 | 2022-04-22 | 江西宝顺昌特种合金制造有限公司 | NS3303 corrosion-resistant alloy and forging method thereof |
| CN117161298A (en) * | 2023-11-02 | 2023-12-05 | 莱州市莱索制品有限公司 | Manufacturing method of thrust wheel for engineering machinery |
| WO2024138420A1 (en) * | 2022-12-26 | 2024-07-04 | 无锡透平叶片有限公司 | Machining method for in718 axial flow blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112139415A (en) * | 2020-09-16 | 2020-12-29 | 江苏隆达超合金航材有限公司 | Method for producing difficult-to-deform nickel-based high-temperature alloy through compensation heating assisted free forging |
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| WO2024138420A1 (en) * | 2022-12-26 | 2024-07-04 | 无锡透平叶片有限公司 | Machining method for in718 axial flow blade |
| CN117161298A (en) * | 2023-11-02 | 2023-12-05 | 莱州市莱索制品有限公司 | Manufacturing method of thrust wheel for engineering machinery |
| CN117161298B (en) * | 2023-11-02 | 2024-02-09 | 莱州市莱索制品有限公司 | Manufacturing method of thrust wheel for engineering machinery |
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