CN116005088B - Method for cooperatively regulating and controlling tissue performance and residual stress of high-temperature alloy disc forging - Google Patents
Method for cooperatively regulating and controlling tissue performance and residual stress of high-temperature alloy disc forging Download PDFInfo
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- CN116005088B CN116005088B CN202211718357.4A CN202211718357A CN116005088B CN 116005088 B CN116005088 B CN 116005088B CN 202211718357 A CN202211718357 A CN 202211718357A CN 116005088 B CN116005088 B CN 116005088B
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- 238000005242 forging Methods 0.000 title claims abstract description 93
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 72
- 239000000956 alloy Substances 0.000 title claims abstract description 72
- 238000000034 method Methods 0.000 title claims abstract description 71
- 230000001276 controlling effect Effects 0.000 title claims abstract description 15
- 230000001105 regulatory effect Effects 0.000 title claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 119
- 238000010438 heat treatment Methods 0.000 claims abstract description 19
- 239000007789 gas Substances 0.000 claims description 65
- 230000035882 stress Effects 0.000 claims description 56
- 239000003570 air Substances 0.000 claims description 44
- 229910000601 superalloy Inorganic materials 0.000 claims description 35
- 230000032683 aging Effects 0.000 claims description 14
- 238000005192 partition Methods 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 230000033228 biological regulation Effects 0.000 claims description 6
- 239000003595 mist Substances 0.000 claims description 5
- 239000002826 coolant Substances 0.000 claims description 4
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 238000012545 processing Methods 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 17
- 238000010791 quenching Methods 0.000 description 17
- 230000000171 quenching effect Effects 0.000 description 16
- 238000012360 testing method Methods 0.000 description 11
- 239000000243 solution Substances 0.000 description 10
- 238000009826 distribution Methods 0.000 description 6
- 230000008646 thermal stress Effects 0.000 description 6
- 238000005336 cracking Methods 0.000 description 5
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000006104 solid solution Substances 0.000 description 4
- 238000005728 strengthening Methods 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
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- 230000007704 transition Effects 0.000 description 2
- 208000012868 Overgrowth Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002902 bimodal effect Effects 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000000635 electron micrograph Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
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- 150000003839 salts Chemical class 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
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- 238000004781 supercooling Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
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Abstract
The invention relates to the technical field of high-temperature alloy processing, in particular to a method for cooperatively regulating and controlling tissue performance and residual stress of a high-temperature alloy disc forging. The method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging comprises the following steps: carrying out solution heat treatment on the high-temperature alloy disc forging, and then carrying out air cooling; in the air cooling process, the cooling rate is controlled to be 5-50 ℃/min in the process of changing from TS to (TS-20 ℃) to (TS-100 ℃); the cooling rate is controlled at 50-250 ℃/min in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃); the cooling rate is controlled to be 20-100 ℃/min in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature. The invention reduces the residual stress in the high-temperature alloy disc forging piece by adopting a mode of temperature division interval and regional control while taking the tissue performance into consideration.
Description
Technical Field
The invention relates to the technical field of high-temperature alloy processing, in particular to a method for cooperatively regulating and controlling tissue performance and residual stress of a high-temperature alloy disc forging.
Background
The disk forgings such as turbine disks, compressor disks and the like are important hot end bearing components in gas turbine aeroengines, and are generally prepared from aging strengthening type nickel-based superalloy, such as GH4169 alloy, GH4738 alloy, GH4720Li, FGH96 alloy, FGH98 alloy and the like.
In order to obtain a sufficient strengthening level, after forging and forming, a superalloy disc forging generally needs to be rapidly cooled at a certain rate after solution treatment at a temperature exceeding or approaching the total dissolution temperature of a strengthening phase, so as to ensure that the gamma 'or gamma' strengthening phase is not coarsened in the process, and oil quenching, salt quenching, water quenching and other modes are often adopted in the preparation process of the current technology, and thus the following steps are adopted: (1) In the quenching beginning stage, the cooling speed of the surface is higher, so that higher-value tensile stress is generated on the surface, the cracking problem of a workpiece is caused, and cracks are often generated at concave corners of an inner hole and upper and lower end surfaces of a disc piece; (2) In the cooling process, the hub with larger thickness of the turbine disc and the rim area with smaller thickness of the thick bottom are easy to generate higher temperature gradient, and the thermal stress formed by the temperature difference can cause uneven plastic deformation, so that residual stress with higher value and unreasonable distribution form is formed in the cooled disc. Proved by actual measurement, the residual stress of the GH4169 alloy disc after quenching can reach about 400MPa, and the residual stress of the GH4738 alloy, GH4720Li, FGH4096, FGH4095 and other high-alloy superalloy discs can reach 800MPa or even higher; (3) Because of adopting uniform quenching medium (quenching oil, water and the like), the cooling speed of the workpiece in a high-temperature section is high, but the cooling speed in a medium-temperature section is insufficient, and the tissue performance cannot meet the use requirement.
For the high-temperature alloy turbine disc forging, due to the characteristics of the high-temperature alloy turbine disc forging, the stacking fault energy is low, so that the residual stress is easy to accumulate and difficult to release, and the numerical value is large. The methods of natural aging, pre-stretching, cryogenic, and vibration, which are successfully applied in the preparation of other materials or components, are very limited in effect for high temperature alloy disc forgings which are heavy and have extremely high stress relief thresholds. Conventional aging heat treatments also only remove about 1/3 of the residual quench stresses.
In view of this, the present invention has been made.
Disclosure of Invention
The invention aims to provide a method for cooperatively regulating and controlling the tissue performance and residual stress of a high-temperature alloy disc forging, which aims to solve the technical problem of high residual stress of the high-temperature alloy disc forging in the prior art.
In order to achieve the above object of the present invention, the following technical solutions are specifically adopted:
the method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging comprises the following steps:
carrying out solution heat treatment on the high-temperature alloy disc forging, and then carrying out air cooling;
in the air cooling process, the cooling rate is controlled to be 5-50 ℃/min in the process of changing from TS to (TS-20 ℃) to (TS-100 ℃);
the cooling rate is controlled at 50-250 ℃/min in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃);
the cooling rate is controlled to be 20-100 ℃/min in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature.
In a specific embodiment of the invention, the corresponding cooling rate is achieved by adjusting the gas flow rate in the gas cooling. Further, the temperature of the gas is 10 to 30 ℃.
In a specific embodiment of the present invention, the air cooling adopts a partition control cooling mode. Further, in the zone control cooling, the flow rate of the air cooling air gradually decreases from the hub center of the disc forging to the rim direction of the disc forging.
In a specific embodiment of the invention, in the zone control cooling, the gas flow rate at the hub center of the disc forging is 2-4 times that at the rim of the disc forging.
In a specific embodiment of the present invention, in the zone control cooling, a gas flow rate adopted by a portion between a hub and a rim of the disc forging is greater than or equal to a gas flow rate at the rim and less than or equal to a gas flow rate at a center of the hub.
In the embodiment of the invention, in the zone control cooling, the disc forging is partitioned according to the size of the section thickness along the axial direction, and the gas flow velocity between each two areas is proportional to the section thickness.
In a specific embodiment of the present invention, the time of the partition controlled cooling is 10 to 30 minutes.
In a specific embodiment of the present invention, in the air cooling, the flow rate of the air is 0 to 150m/s.
In a specific embodiment of the invention, in the air cooling process, the flow rate of the air is 0-60 m/s in the process of changing from Ts to (Ts-20 ℃) to (Ts-100 ℃); the flow rate of the gas is 20-150 m/s in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃); the gas flow rate is 5-50 m/s in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature.
In a specific embodiment of the present invention, further comprising: and carrying out aging heat treatment on the high-temperature alloy disc forging subjected to air cooling.
In specific embodiments of the present invention, the superalloy comprises any of a GH4169 alloy, a GH4720Li alloy, a GH4738 alloy, a FGH95 alloy, a FGH96 alloy, and a FGH97 alloy.
In a specific embodiment of the present invention, in the air cooling, the cooling medium includes any one or more of air, helium and water mist. Wherein, the water mist is the mixture of air and water drops.
Compared with the prior art, the invention has the beneficial effects that:
the residual quenching stress of the superalloy mainly originates from thermal stress formed by asynchronous cooling of different areas during cooling and volume shrinkage effect caused by reinforced phase transformation. According to the invention, by adopting an air cooling mode, the temperature gradient in the quenching process is controlled, so that the generation of thermal stress is avoided; on the premise of ensuring that the cooling speed of each area of the section of the high-temperature alloy forging is larger than the critical cooling speed, the cooling speed difference of different areas is reduced, so that the residual stress is reduced; meanwhile, the high-temperature alloy forging piece is cooled rapidly at the part with thick section and cooled slowly at the part with thin section; the cooling speed difference of different areas is reduced by the zonal regulation and control of the heat exchange coefficient of the cooling section, so that quenching stress caused by temperature gradient and residual stress value left after cooling are reduced, the problem of limitation of the prior art on the control of the residual stress in the high-temperature alloy forging is solved, and meanwhile, the tissue performance is guaranteed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a partition control cooling device according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the cross-sectional structure and partition of a superalloy disc forging of embodiment 1 of the present invention;
FIG. 3 is a residual stress test result of a superalloy disc forging processed in example 1 of the present invention;
FIG. 4 is a residual stress test result of a superalloy disc forging processed in example 2 of the present invention;
FIG. 5 is a residual stress test result of the superalloy disc forging processed in comparative example 1;
FIG. 6 is a residual stress test result of the superalloy disc forging processed in comparative example 2;
FIG. 7 is a metallographic photograph of the grain size of a superalloy disc forging processed in example 1 of the present invention;
FIG. 8 is a photograph of a precipitated phase electron microscope of a superalloy disc forging treated in example 1 of the present invention;
FIG. 9 is a grain size metallographic photograph of a superalloy disc forging treated in comparative example 1;
FIG. 10 is a precipitated phase electron micrograph of a superalloy disc forging treated in comparative example 1;
fig. 11 is a photograph of a superalloy disc forging treated in comparative example 2.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings and detailed description, but it will be understood by those skilled in the art that the examples described below are some, but not all, examples of the present invention, and are intended to be illustrative of the present invention only and should not be construed as limiting the scope of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. The specific conditions are not noted in the examples and are carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or apparatus used were conventional products commercially available without the manufacturer's attention.
The method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging comprises the following steps:
carrying out solution heat treatment on the high-temperature alloy disc forging, and then carrying out air cooling;
in the air cooling process, the cooling rate is controlled to be 5-50 ℃/min in the process of changing from TS to (TS-20 ℃) to (TS-100 ℃);
the cooling rate is controlled at 50-250 ℃/min in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃);
the cooling rate is controlled to be 20-100 ℃/min in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature.
The excellent high temperature performance of nickel-base superalloys results from the ideal microstructure, while the inclusion of a bimodal distribution of the gamma' phase on the gamma matrix is a guarantee that the alloy has excellent overall properties, which are closely related to the supersaturation of solid solution during cooling. In the initial stage of cooling the superalloy, after the secondary gamma '-phase is precipitated by the first burst nucleation, the supersaturation degree of the matrix is rapidly reduced, so that the cooling speed is increased at the moment, the supersaturation degree of the alloy is increased, and a microstructure with double/multimode gamma' -phase size distribution is formed.
In the process of changing Ts to (Ts-20 ℃) to (Ts-100 ℃), the cooling rate is controlled to be 5-50 ℃/min, so that the surface tensile stress value in the quenching process of the workpiece is reduced, and the workpiece is prevented from cracking; on the other hand, sufficient time and temperature conditions are provided for secondary gamma' -phase precipitation; in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃), the cooling rate is controlled to be 50-250 ℃/min, the supercooling degree of the alloy and the supersaturation degree of the solid solution are improved, conditions are created for forming a microstructure with double/multimode gamma ' phase size distribution, and overgrowth and coarsening of gamma ' or gamma ' phases are avoided. In the rapid cooling process, regional control should be performed so as to avoid residual generation of residual stress; in the process of changing the temperature from (Ts-200 ℃) to (Ts-500 ℃) to room temperature, the cooling rate is controlled to be 20-100 ℃/min, so that the value of the shearing stress of the wheel hub and the spoke part is reduced, and microscopic cracking near the inclusion at the part is avoided.
As in the various embodiments, the cooling rate may be illustratively controlled at 5℃/min, 10℃/min, 15℃/min, 20℃/min, 25℃/min, 30℃/min, 35℃/min, 40℃/min, 45℃/min, 50℃/min, etc. during the transition from Ts to (Ts-20deg.C) to (Ts-100deg.C); in the process of changing from (TS-20deg.C) to (TS-100deg.C) to (TS-200deg.C) to (TS-500deg.C), the cooling rate can be controlled at 50deg.C/min, 80deg.C/min, 100deg.C/min, 120deg.C/min, 150deg.C/min, 180deg.C/min, 200deg.C/min, 220deg.C/min, 250deg.C/min, etc., by way of example; in the process of changing from (Ts-200deg.C) to (Ts-500deg.C) to room temperature, the cooling rate can be controlled at 20deg.C/min, 30deg.C/min, 40deg.C/min, 50deg.C/min, 60deg.C/min, 70deg.C/min, 80deg.C/min, 90deg.C/min, 100deg.C/min, etc., as examples.
In a specific embodiment of the invention, the corresponding cooling rate is achieved by adjusting the gas flow rate in the gas cooling. Further, the temperature of the gas is 10 to 30 ℃.
As in the various embodiments, the temperature of the gas may be illustratively 10 ℃, 12 ℃, 15 ℃, 18 ℃, 20 ℃, 22 ℃, 25 ℃, 28 ℃, 30 ℃, and the like.
In a specific embodiment of the present invention, the air cooling adopts a partition control cooling mode. Further, in the zone control cooling, the flow rate of the air cooling air gradually decreases from the hub center of the disc forging to the rim direction of the disc forging.
In a specific embodiment of the invention, in the zone control cooling, the gas flow rate at the hub center of the disc forging is 2-4 times that at the rim of the disc forging.
As in the various embodiments, in the zone control cooling, the gas flow rate at the hub center of the disc forging may be illustratively 2 times, 2.5 times, 3 times, 3.5 times, 4 times, etc. the gas flow rate at the rim of the disc forging. The ratio of the gas flow rate at the hub center to the gas flow rate at the rim of a specific disc forging is equivalent to the ratio of the thickness of the hub center to the gas flow rate at the rim.
In a specific embodiment of the present invention, in the zone control cooling, a gas flow rate adopted by a portion between a hub and a rim of the disc forging is greater than or equal to a gas flow rate at the rim and less than or equal to a gas flow rate at a center of the hub.
In the embodiment of the invention, in the zone control cooling, the disc forging is partitioned according to the size of the section thickness along the axial direction, and the gas flow velocity between each two areas is proportional to the section thickness.
In actual operation, the partition control cooling can be performed by adopting a structural schematic diagram of a partition control cooling device shown in fig. 1, the surface of the superalloy disc forging is divided into a plurality of areas, and gas nozzles are respectively arranged for cooling. The cooling rate of the corresponding position of the disc is controlled by adjusting the quenching gas flow rate and the medium type, so that the zonal control of the disc cooling process is realized.
For high-temperature alloy disc forgings with heavy weight and large section difference, a large temperature gradient can be formed by adopting traditional cooling means such as water cooling and the like, so that a high-magnitude residual stress gradient is caused. Controlling the temperature gradient in the quenching process and avoiding the generation of thermal stress is the key for realizing the control of thermal stress and residual stress in the quenching process. On the premise of ensuring that the cooling speed of each area of the section of the high-temperature alloy forging is larger than the critical cooling speed, the cooling speed difference of different areas is reduced, so that the residual stress is reduced; the high-temperature alloy forging piece is cooled rapidly at the part with thick section and cooled slowly at the part with thin section; the cooling speed difference of different areas is reduced by the zonal regulation and control of the heat exchange coefficient of the cooling section, so that the quenching stress caused by temperature gradient and the residual stress value left after cooling are reduced, and the problem of limitation of the prior art on the control of the residual stress in the high-temperature alloy forging is solved.
In a specific embodiment of the present invention, the time of the partition controlled cooling is 10 to 30 minutes.
As in the various embodiments, the time of the zone control cooling may be exemplified by 10min, 12min, 15min, 18min, 20min, 22min, 25min, 28min, 30min, etc.
In a specific embodiment of the present invention, in the air cooling, the flow rate of the air is 0 to 150m/s.
As in the various embodiments, the gas flow rate in the gas cooling may be exemplified by 0m/s, 10m/s, 20m/s, 30m/s, 40m/s, 50m/s, 60m/s, 70m/s, 80m/s, 90m/s, 100m/s, 110m/s, 120m/s, 130m/s, 140m/s, 150m/s, etc.
In a specific embodiment of the invention, in the air cooling process, the flow rate of the air is 0-60 m/s in the process of changing from Ts to (Ts-20 ℃) to (Ts-100 ℃); the flow rate of the gas is 20-150 m/s in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃); the gas flow rate is 5-50 m/s in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature.
When the gas flow rate is 0, air cooling is correspondingly adopted. As in the various embodiments, in the gas cooling, the gas flow rate may be exemplified by 0m/s, 10m/s, 20m/s, 30m/s, 40m/s, 50m/s, 60m/s, etc. in the course of changing from Ts to (Ts-20deg.C) to (Ts-100deg.C); the gas flow rate in the process from (Ts-20deg.C) to (Ts-100deg.C) to (Ts-200deg.C) to (Ts-500deg.C) may be exemplified by 20m/s, 30m/s, 40m/s, 50m/s, 60m/s, 70m/s, 80m/s, 90m/s, 100m/s, 110m/s, 120m/s, 130m/s, 140m/s, 150m/s, etc.; the gas flow rate during the transition from (Ts-200deg.C) to (Ts-500deg.C) to room temperature may be exemplified by 5m/s, 10m/s, 15m/s, 20m/s, 25m/s, 30m/s, 35m/s, 40m/s, 45m/s, 50m/s, etc.
In a specific embodiment of the present invention, further comprising: and carrying out aging heat treatment on the high-temperature alloy disc forging subjected to air cooling.
In actual operation, the aging heat treatment is carried out by adopting a conventional aging heat treatment system according to the type of the high-temperature alloy.
In specific embodiments of the present invention, the superalloy comprises any of a GH4169 alloy, a GH4720Li alloy, a GH4738 alloy, a FGH95 alloy, a FGH96 alloy, and a FGH97 alloy.
In a specific embodiment of the present invention, in the air cooling, the cooling medium includes any one or more of air, helium and water mist. Wherein, the water mist is the mixture of air and water drops. The cooling medium used in the following embodiment is air, but is not limited thereto.
Example 1
The embodiment provides a GH4169 high-temperature alloy disk forging tissue performance and residual stress cooperative regulation method, which comprises the following steps:
(1) Forming or solutionizing the GH4169 high-temperature alloy plate forging at 990-1020 ℃ for 4 hours, and then carrying out zone control air cooling;
specifically, the schematic sectional structure and the partition diagram of the GH4169 superalloy disc forging are shown in FIG. 2, wherein the gas flow rate in a A, B, I, J area is set to be 15m/s, the gas flow rate in a C area is set to be 8.75m/s, and the gas flow rate in a D, E, F, G, H area is set to be 5m/s from the solid solution temperature to 950 ℃; the corresponding cooling rate is about 10-20 ℃/min;
the gas flow rate in the A, B, I, J area is set to be 60m/s, the gas flow rate in the C area is set to be 35m/s and the gas flow rate in the D, E, F, G, H area is set to be 20m/s in the same proportion from 950 ℃ to 600 ℃; the corresponding cooling rate is about 50-60 ℃/min;
the gas flow rate in the A, B, I, J area is set to be 30m/s, the gas flow rate in the C area is set to be 17.5m/s and the gas flow rate in the D, E, F, G, H area is set to be 10m/s in the same proportion from 600 ℃ to room temperature; the corresponding cooling rate is about 20-40 deg.c/min.
(2) And (3) carrying out aging heat treatment on the disc forging processed in the step (1), wherein the aging heat treatment system is 720 ℃/8h+620 ℃/8h, furnace cooling is carried out when the temperature is reduced from 720 ℃ to 620 ℃, the cooling rate is 100 ℃/min, and the disc forging is air-cooled from 620 ℃ to room temperature. .
Example 2
The embodiment provides a method for synergistically regulating and controlling the tissue performance and residual stress of a FGH96 high-temperature alloy disk forging, which comprises the following steps:
(1) Carrying out solution heat treatment on the FGH96 high-temperature alloy disk forging at 1150 ℃ for 4 hours, and then carrying out zone control air cooling;
specifically, the hub thickness of the FGH96 superalloy disc forging is about 2.5 times the rim thickness;
in the process of changing the temperature from 1150 ℃ to 1080 ℃, the gas flow rate of the rim area is 10m/s, the gas flow rate of the hub area is 25m/s, the gas temperature is 10-30 ℃, and the cooling rate is controlled to be 20-50 ℃/min (the rim area is about 40-50 ℃/min and the hub area is about 30-40 ℃/min);
in the process of changing from 1080 ℃ to 700 ℃, the gas flow rate of the rim area is 40m/s, the gas flow rate of the hub area is 100m/s, the gas temperature is 10-30 ℃, and the cooling rate is controlled to be 50-150 ℃/min (the rim area is about 90-150 ℃/min and the hub area is about 60-100 ℃/min);
the gas flow rate of the rim area is 20m/s, the gas flow rate of the hub area is 50m/s, the gas temperature is 10-30 ℃, and the cooling rate is controlled to be 10-50 ℃/min (the rim area is about 40-50 ℃/min and the hub area is about 30-40 ℃/min) in the process of changing from 700 ℃ to room temperature.
(2) And (3) carrying out aging heat treatment on the disc forging processed in the step (1), wherein the aging heat treatment system is 760 ℃/16h, and air cooling is carried out.
Comparative example 1
Comparative example 1 reference example 1, except that: and (3) directly performing oil cooling after the solution heat treatment in the step (1), and directly performing corresponding aging heat treatment after the oil cooling.
Comparative example 2
Comparative example 2 reference example 2, except that: and (3) directly performing oil cooling after the solution heat treatment in the step (1), and directly performing corresponding aging heat treatment after the oil cooling.
Experimental example 1
The residual stress of the inner chord direction is measured by adopting a < TCSTM 00347-2020 metal material disc annular forging residual stress measuring contour method >, and FIG. 3 is a residual stress test result of the high-temperature alloy disc forging processed by the embodiment 1 of the invention; FIG. 4 is a residual stress test result of a superalloy disc forging processed in example 2 of the present invention; FIG. 5 is a residual stress test result of the superalloy disc forging processed in comparative example 1; FIG. 6 is a residual stress test result of the superalloy disc forging processed in comparative example 2.
The GH4169 superalloy disc forging prepared in comparative example 1 has a residual stress distribution characteristic of "external tensile internal pressure", and a maximum residual tensile stress value of about 300MPa.
The GH4169 high-temperature alloy disc forging prepared by the method of the embodiment 1 of the invention has obviously reduced residual stress value and the maximum chord stress value is lower than 100MPa.
The FGH96 alloy disk forging produced in comparative example 2 has a residual stress distribution characterized by "external tension internal pressure" and a maximum residual tensile stress value of about 650MPa.
The FGH96 alloy disk forging prepared by the method of the embodiment 2 of the invention has obviously reduced residual stress value and the maximum chord stress value is lower than 200MPa.
Fig. 7 to 8 and fig. 9 to 10 are respectively a metallographic photograph and a precipitated phase electron microscope photograph of the grain size of the superalloy disc forging processed in example 1 and comparative example 1 according to the present invention, and it is apparent from the drawings that the superalloy disc forging obtained by the method of the present invention has no obvious difference in terms of structural performance from comparative example 1, and residual stress is effectively controlled on the premise of ensuring the structural performance.
Fig. 11 is a photograph of a superalloy disc forging treated in comparative example 2. From the graph, higher numerical thermal stress is generated in the oil quenching process after solid solution, and the cracking problem of the inner hole of the workpiece is caused. After the cooling mode of the invention is adopted, the problems of cracking and the like are solved.
Experimental example 2
Tensile properties at room temperature of high-temperature alloy disk forgings worth different examples and comparative examples were tested, and the test results are shown in table 1.
Table 1 results of room temperature tensile properties testing of different superalloy disc forgings
From the test results, the tensile strength and the yield strength of the GH4169 superalloy disc forge piece and the FGH96 superalloy disc forge piece prepared by the method are improved.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (9)
1. The method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging is characterized by comprising the following steps of:
carrying out solution heat treatment on the high-temperature alloy disc forging, and then carrying out air cooling;
in the air cooling process, the cooling rate is controlled to be 5-50 ℃/min in the process of changing from TS to (TS-20 ℃);
the cooling rate is controlled to be 50-250 ℃/min in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃);
the cooling rate is controlled to be 20-100 ℃/min in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature;
in the air cooling, a partition control cooling mode is adopted;
in the zone control cooling, the center of the hub of the disc forging starts to face the rim direction of the disc forging, and the air cooling air flow rate is gradually reduced;
in the zone control cooling, the disc forging is partitioned according to the thickness of the section along the axial direction, and the gas flow velocity among the areas is in direct proportion to the thickness of the section;
the corresponding cooling rate is achieved by adjusting the flow rate of the gas in the gas cooling;
the superalloy includes any of a GH4169 alloy, a GH4720Li alloy, a GH4738 alloy, a FGH95 alloy, a FGH96 alloy, and a FGH97 alloy.
2. The method for synergistically regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging according to claim 1, wherein the temperature of the gas is 10-30 ℃.
3. The method for collaborative regulation and control of structural performance and residual stress of a superalloy disc forging according to claim 1, wherein in the zone control cooling, the gas flow rate at the hub center of the disc forging is 2-4 times the gas flow rate at the rim of the disc forging.
4. The method of claim 1, wherein the portion of the disc forging between the hub center and the rim is at a gas flow rate greater than or equal to the gas flow rate at the rim and less than or equal to the gas flow rate at the hub center.
5. The method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging according to claim 1, wherein the time for the zone control cooling is 10-30 min.
6. The method for synergistically regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging according to claim 1, wherein in the air cooling, the air flow rate is 0-150 m/s.
7. The method for cooperatively regulating and controlling the tissue performance and the residual stress of the high-temperature alloy disc forging piece according to claim 6, wherein in the air cooling process, the air flow rate is 0-60 m/s in the process of changing from Ts to (Ts-20 ℃) to (Ts-100 ℃); the flow rate of the gas is 20-150 m/s in the process of changing from (TS-20 ℃) to (TS-100 ℃) to (TS-200 ℃) to (TS-500 ℃); in the process of changing from (Ts-200 ℃) to (Ts-500 ℃) to room temperature, the gas flow rate is 5-50 m/s.
8. The method for collaborative regulation of superalloy disc forging tissue properties and residual stress according to claim 1, further comprising: and carrying out aging heat treatment on the high-temperature alloy disc forging subjected to air cooling.
9. The method for collaborative regulation of superalloy disc forging tissue properties and residual stress according to claim 1, wherein the cooling medium in the air cooling comprises any one or more of air, helium and water mist.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4685978A (en) * | 1982-08-20 | 1987-08-11 | Huntington Alloys Inc. | Heat treatments of controlled expansion alloy |
| CN114107852A (en) * | 2021-11-25 | 2022-03-01 | 北京钢研高纳科技股份有限公司 | Heat treatment method of GH4096 alloy forging, forging prepared by same and application thereof |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4685978A (en) * | 1982-08-20 | 1987-08-11 | Huntington Alloys Inc. | Heat treatments of controlled expansion alloy |
| CN114107852A (en) * | 2021-11-25 | 2022-03-01 | 北京钢研高纳科技股份有限公司 | Heat treatment method of GH4096 alloy forging, forging prepared by same and application thereof |
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