CN112122398A - Thermal sizing process of nickel-based superalloy thin-wall casting and nickel-based superalloy thin-wall casting - Google Patents
Thermal sizing process of nickel-based superalloy thin-wall casting and nickel-based superalloy thin-wall casting Download PDFInfo
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 256
- 238000005266 casting Methods 0.000 title claims abstract description 253
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 172
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 121
- 238000000034 method Methods 0.000 title claims abstract description 112
- 238000004513 sizing Methods 0.000 title claims abstract description 102
- 238000012937 correction Methods 0.000 claims abstract description 116
- 238000010438 heat treatment Methods 0.000 claims abstract description 26
- 230000007613 environmental effect Effects 0.000 claims abstract description 4
- 238000001816 cooling Methods 0.000 claims description 15
- 239000002994 raw material Substances 0.000 claims description 11
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 8
- 239000011261 inert gas Substances 0.000 claims description 8
- 229910052786 argon Inorganic materials 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 abstract description 27
- 239000000956 alloy Substances 0.000 abstract description 27
- 238000013461 design Methods 0.000 abstract description 6
- 230000000052 comparative effect Effects 0.000 description 24
- 230000000694 effects Effects 0.000 description 9
- 238000004321 preservation Methods 0.000 description 7
- 238000005495 investment casting Methods 0.000 description 6
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000002045 lasting effect Effects 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 239000002699 waste material Substances 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 230000000875 corresponding effect Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- AFCARXCZXQIEQB-UHFFFAOYSA-N N-[3-oxo-3-(2,4,6,7-tetrahydrotriazolo[4,5-c]pyridin-5-yl)propyl]-2-[[3-(trifluoromethoxy)phenyl]methylamino]pyrimidine-5-carboxamide Chemical compound O=C(CCNC(=O)C=1C=NC(=NC=1)NCC1=CC(=CC=C1)OC(F)(F)F)N1CC2=C(CC1)NN=N2 AFCARXCZXQIEQB-UHFFFAOYSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- 238000001000 micrograph Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D1/00—Straightening, restoring form or removing local distortions of sheet metal or specific articles made therefrom; Stretching sheet metal combined with rolling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/84—Making other particular articles other parts for engines, e.g. connecting-rods
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
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- Engineering & Computer Science (AREA)
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- Chemical & Material Sciences (AREA)
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- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application relates to the technical field of alloy castings, in particular to a thermal sizing process of a nickel-based superalloy thin-wall casting and the nickel-based superalloy thin-wall casting, wherein the thermal sizing process specifically comprises the following steps: placing the thin-wall nickel-based superalloy casting in an air-isolated environment, heating the environment to 1160-1200 ℃, and heating the thin-wall nickel-based superalloy casting along with the environment; preserving the heat of the nickel-based superalloy thin-wall casting under the environmental condition for 4-6 h; the nickel-based superalloy thin-wall casting is cooled along with the environment; when the environment is cooled to 800 ℃ of 600-; and the nickel-based superalloy thin-wall casting is corrected by the thermal correction process. The casting size can meet the design requirement to the maximum extent, and the high-temperature mechanical property of the casting is improved.
Description
Technical Field
The application relates to the technical field of alloy castings, in particular to a thermal sizing process of a nickel-based superalloy thin-wall casting and the nickel-based superalloy thin-wall casting.
Background
Castings, such as a sealing sheet and an adjusting sheet, at the closing-in nozzle part of the aero-engine need to bear the high temperature and the tensile stress of more than 1000 ℃ in the working process of the aero-engine, so that the castings are required to have high temperature resistance and corrosion resistance, and high dimensional accuracy, so that when the aero-engine is accelerated and lifted or lowered in an operation state and a cruise state, the stability and the safety of an engine adjusting system are ensured.
The structure characteristics of the casting at the closing-up nozzle part of the aero-engine are mainly represented by a large plane, a thin wall, a complex structure and no allowance. The casting is cast through a precision casting process, the cast casting is easy to deform, and the size of the casting hardly meets the design requirement. Therefore, there is a need for a hot-forming process for hot-forming a casting obtained by precision casting to maximize the design of the casting.
Disclosure of Invention
In order to enable the size of the casting to meet the design requirement to the maximum extent and improve the high-temperature mechanical property of the casting, the application provides a thermal sizing process of a nickel-based superalloy thin-wall casting and the nickel-based superalloy thin-wall casting.
In a first aspect, the application provides a thermal sizing process for a nickel-based superalloy thin-wall casting, which adopts the following technical scheme:
a hot sizing process of a nickel-based superalloy thin-wall casting specifically comprises the following steps:
step (1): placing the thin-wall nickel-based superalloy casting in an air-isolated environment, heating the environment to 1160-1200 ℃, and heating the thin-wall nickel-based superalloy casting along with the environment;
step (2): preserving the heat of the nickel-based superalloy thin-wall casting under the environmental condition in the step (1) for 4-6 hours;
and (3): and (3) cooling the nickel-based superalloy thin-wall casting treated in the step (2) along with the environment to obtain the nickel-based superalloy thin-wall casting subjected to thermal shape correction.
By adopting the technical scheme, in the hot sizing process of the nickel-based high-temperature alloy thin-wall casting, the control of the hot sizing temperature and the hot sizing time plays a crucial role in the hot sizing result. According to the method, the temperature of the environment for isolating air in the thermal sizing process of the nickel-based high-temperature alloy thin-wall casting is controlled within the range of 1160-1200 ℃, namely the thermal sizing temperature is controlled within the range of 1160-1200 ℃, and the thermal sizing time is controlled within the range of 4-6h, so that the size precision and the mechanical property of the nickel-based high-temperature alloy thin-wall casting can meet the design requirements of the closing nozzle part of an aero-engine on the casting to the greatest extent.
According to the test result analysis, the thermal sizing process of the nickel-based superalloy thin-wall casting provided by the application can cause poor thermal sizing result or reduced mechanical property of the nickel-based superalloy thin-wall casting when the thermal sizing temperature is lower than 1160 ℃ or higher than 1200 ℃. Therefore, the thermal sizing temperature parameter in the thermal sizing process of the nickel-based superalloy thin-wall casting is controlled within the range of 1160-1200 ℃; when the hot shape correction time is less than 4h, the hot shape correction effect of the nickel-based superalloy thin-wall casting is poor, and the mechanical property is reduced; meanwhile, the hot-sizing time is too long, unnecessary consumption of time and resources is caused, resource waste is caused, the production cost of the casting is improved, and when the hot-sizing time is 6 hours, the hot-sizing effect of the nickel-based high-temperature alloy thin-wall casting after sizing is good and the nickel-based high-temperature mechanical property is high. Therefore, the hot-forming time parameter in the hot-forming process of the nickel-base superalloy thin-wall casting is controlled within the range of 4-6 h. Within the parameter range of the thermal sizing process, the tensile property and the durability of the nickel-based superalloy thin-wall casting are both obviously improved, the tensile strength of the nickel-based superalloy thin-wall casting can maximally reach 320.0MPa, the yield strength of the nickel-based superalloy thin-wall casting can maximally reach 231.7MPa, the elongation of the nickel-based superalloy thin-wall casting can maximally reach 21.7% under the condition that the temperature is 1100 ℃, meanwhile, the lasting time can reach 86.1h under the condition that the durability is 60MPa, and the high-temperature mechanical property of the nickel-based superalloy thin-wall casting can be obviously improved under the thermal sizing process condition by combining an electron microscope image of the nickel-based superalloy structure morphology after sizing of different thermal sizing temperature parameters and different thermal sizing time parameters.
In conclusion, the control of the thermal sizing temperature and the thermal sizing time in the thermal sizing process can not only enable the dimensional accuracy of the nickel-based superalloy thin-wall casting to meet the requirement of the closing-up nozzle part of the aircraft engine on the size of the casting to the maximum extent, but also can obviously improve the high-temperature mechanical property of the nickel-based superalloy thin-wall component.
Preferably, the air-insulated environment in step (1) is heated to 1160-1200 ℃ within 2-5 h.
By adopting the technical scheme, the nickel-based superalloy thin-wall casting to be subjected to thermal straightening is placed in an air-isolated environment, and the heating time of the environment temperature of the air-isolated environment is controlled within 2-5h, so that on one hand, the temperature in the environment is ensured to be slowly changed, and the nickel-based superalloy thin-wall casting is prevented from being greatly deformed in the environment with sudden temperature change, so that the nickel-based superalloy thin-wall casting is prevented from cracking; on the other hand, when the environment is heated, the nickel-based high-temperature alloy thin-wall casting changes along with the change of the environment temperature, so that the temperature of the nickel-based high-temperature alloy thin-wall casting is ensured to change uniformly and slowly, and the thermal sizing of the nickel-based high-temperature alloy thin-wall casting is laid for the subsequent thermal sizing of the nickel-based high-temperature alloy thin-wall casting through continuous heat preservation, so that the thermal sizing effect of the nickel-based high-temperature alloy thin-wall casting is improved, and the dimensional precision of the nickel-based high-temperature alloy thin-wall casting can meet the.
Preferably, the air-insulated environment is a vacuum environment.
By adopting the technical scheme, in order to prevent the contact and oxidation of the casting and air, the thermal sizing process of the nickel-based superalloy thin-wall casting is carried out in a vacuum environment.
Preferably, when the environment is cooled to 600-800 ℃, filling inert gas of 0.1-0.4MPa into the environment and cooling.
Preferably, the environment is cooled to ambient temperature.
Preferably, the inert gas is argon.
By adopting the technical scheme, in the cooling process, when the ambient temperature of the isolated air is cooled to 600-800 ℃, the inert gas is filled into the environment of the isolated air, on one hand, the inert gas is filled into the environment, which is beneficial to cooling the environment, on the other hand, when the temperature is reduced to normal temperature, the internal and external air pressures of the environment of the isolated air approach, the environment of the isolated air is conveniently opened, and the nickel-based high-temperature alloy after thermal correction is taken out from the environment of the isolated air.
In a second aspect, the application provides a thin-walled nickel-based superalloy casting, which adopts the following technical scheme:
the nickel-based superalloy thin-wall casting is corrected by the thermal correction process.
Preferably, the thin-wall nickel-base superalloy casting comprises the following raw material components in percentage by weight: 0.06-0.20% of C, 7.40-8.20% of Cr, 1.5-2.5% of W, 3.5-5.5% of Mo, 7.6-8.5% of Al, 0.6-1.3% of Ti, 0.3-0.9% of Hf, less than or equal to 0.05% of B, less than or equal to 0.01% of Y and the balance of Ni.
By adopting the technical scheme, the thin-wall casting is subjected to thermal sizing by using the thermal sizing process provided by the application, and tests show that the nickel-based superalloy thin-wall casting subjected to the thermal sizing process can meet the requirement of a closing-in nozzle part of an aircraft engine on the dimensional precision of the casting to the maximum extent, and meanwhile, the high-temperature mechanical property parameters of the nickel-based superalloy thin-wall casting are remarkably improved.
In summary, the present application includes at least one of the following beneficial technical effects:
the application provides a thermal sizing process of a nickel-based superalloy thin-wall component, which can not only enable the size precision of a nickel-based superalloy thin-wall casting to meet the requirement of a closing-in nozzle part of an aircraft engine on the size of the casting to the maximum extent, but also obviously improve the high-temperature mechanical property of the nickel-based superalloy thin-wall component by controlling the thermal sizing temperature and the thermal sizing time in the thermal sizing process.
In addition, the temperature is increased to 1160-1200 ℃ in 2-5h by controlling the environment isolated from air. On one hand, the nickel-based high-temperature alloy thin-wall casting is prevented from generating large deformation and cracking in a temperature shock environment, on the other hand, the temperature change of the nickel-based high-temperature alloy thin-wall casting is ensured to be uniform and slow, and a cushion is laid for performing thermal correction on the nickel-based high-temperature alloy thin-wall casting through continuous heat preservation, so that the thermal correction effect of the nickel-based high-temperature alloy thin-wall casting is improved, and the size precision of the nickel-based high-temperature alloy thin-wall casting can meet the requirement of the closing-in nozzle part of an aircraft engine on the size of the.
The application also provides the nickel-based high-temperature alloy thin-wall casting corrected by the thermal correction process, the nickel-based high-temperature alloy thin-wall casting corrected by the thermal correction process can meet the requirement of the closing-up nozzle part of an aircraft engine on the dimensional precision of the casting to the greatest extent, and meanwhile, the high-temperature mechanical property parameters of the nickel-based high-temperature alloy thin-wall casting are remarkably improved.
Drawings
FIG. 1 is a schematic diagram of a thin-walled nickel-base superalloy casting placed on a mold before hot forming.
FIG. 2 is a schematic diagram of the thin-wall nickel-base superalloy casting in FIG. 1 after being subjected to thermal straightening and placed on a mold.
FIG. 3 is a structural morphology diagram of the nickel-based superalloy thin-wall casting before thermal correction.
FIG. 4 is a structural morphology of a nickel-base superalloy thin-wall casting obtained by the hot-forming process of comparative example 1 of the present application after being cooled to room temperature (the hot-forming temperature is 1140 ℃, and the hot-forming time is 4 h).
FIG. 5 is a structural morphology of a thin-walled Ni-based superalloy casting obtained by the hot-forming process of example 1 of the present application after cooling to room temperature (the hot-forming temperature is 1160 ℃ C., and the hot-forming time is 4 hours).
FIG. 6 is a structural morphology of a thin-walled Ni-based superalloy casting obtained by the hot-forming process of example 2 of the present application after cooling to room temperature (the hot-forming temperature is 1180 ℃ C., and the hot-forming time is 4 hours).
FIG. 7 is a structural morphology of a thin-walled Ni-based superalloy casting obtained by the hot-forming process of example 3 of the present application after cooling to room temperature (the hot-forming temperature is 1200 ℃ C., and the hot-forming time is 4 hours).
FIG. 8 is a structural morphology of a nickel-base superalloy thin-wall casting obtained by the hot-forming process of comparative example 2 of the present application after being cooled to room temperature (the hot-forming temperature is 1220 ℃, and the hot-forming time is 4 h).
FIG. 9 is a structural morphology of a thin-walled Ni-based superalloy casting obtained by the hot-forming process of example 4 of the present application after cooling to room temperature (the hot-forming temperature is 1160 ℃ C., and the hot-forming time is 6 hours).
FIG. 10 is a structural morphology of a thin-walled Ni-based superalloy casting obtained by the hot-forming process of comparative example 3 of the present application after cooling to room temperature (the hot-forming temperature is 1160 ℃ C., and the hot-forming time is 3 hours).
Detailed Description
Because the requirement of the casting at the closing-in nozzle part of the aero-engine on the size of the casting is high, the casting obtained through the precision casting process is easy to deform, and the requirement of the closing-in nozzle part of the aero-engine on the size of the casting is difficult to achieve. Therefore, the finished casting needs to be corrected by a hot-sizing process so that the size of the casting can finally meet the design requirement.
The thermal sizing process of the casting is as follows: the casting obtained through the precision casting process is placed in a hot sizing die, and then the casting and the die corresponding to the casting are placed in an isolated space environment together for heating treatment, and meanwhile, the environment is kept moist. And (5) performing thermal sizing treatment to finally shape the casting.
In the process of hot sizing of the casting, the hot sizing temperature and the hot sizing time have great influence on the hot sizing result of the casting. When the temperature of thermal sizing is lower, the thermal sizing effect of the casting is poorer, and the dimensional precision of the casting hardly meets the requirement of the closing-up nozzle part of the aero-engine on the size of the casting; along with the rise of the temperature of thermal sizing, the thermal sizing effect of the casting is also improved, the size precision of the casting is easier to meet the requirement of the closing-in nozzle part of the aircraft engine on the size of the casting, and the higher the temperature of thermal sizing is, the better the thermal sizing effect of the casting is. However, when the temperature of hot-forming is too high, the hot-forming process has a large influence on the structural change of the casting, resulting in a reduction in the high-temperature mechanical properties of the component. Therefore, in order to enable the size of the casting subjected to the hot sizing treatment to meet the requirement of the closing-in nozzle part of the aero-engine on the size of the casting and not to influence the high-temperature mechanical property of the casting, a proper hot sizing temperature needs to be selected.
When the hot sizing time is short, the hot sizing effect of the casting is poor, and the size precision of the casting hardly meets the requirement of the closing-up nozzle part of the aero-engine on the size of the casting; when the hot-sizing time is long, unnecessary consumption of time and resources is caused to a certain extent, so that the resources are wasted, and the production cost of the casting is increased. Therefore, the size of the casting after the thermal sizing treatment can meet the requirement of the closing-in nozzle part of the aero-engine on the size of the casting, the waste of resources is reduced as much as possible, the production cost is reduced, and the proper thermal sizing time needs to be selected.
In addition, the casting cast by using different raw material components has different requirements on parameters of a hot sizing process, and particularly has larger difference on the requirements on hot sizing temperature and hot sizing time. The research on the hot-forming process of the nickel-base superalloy thin-wall casting provided by the application is still in the initial stage, and the hot-forming temperature and the hot-forming time required by the hot-forming process of the nickel-base superalloy thin-wall casting are in the research stage.
In conclusion, in order to ensure that the size of the nickel-based superalloy thin-wall casting can meet the requirement of the closing-in nozzle part of the aero-engine on the size of the casting, the high-temperature mechanical property of the casting is not influenced, the waste of resources is reduced as much as possible, and the production cost is reduced, the applicant researches the thermal sizing process of the nickel-based superalloy thin-wall casting.
The application provides a thermal sizing process of a nickel-based superalloy thin-wall casting and the nickel-based superalloy thin-wall casting, the nickel-based superalloy thin-wall casting after being sized by the thermal sizing process can meet the requirement of a closed nozzle part of an aircraft engine on the size of the casting to the maximum extent, and meanwhile, the thermal sizing temperature in the thermal sizing process cannot influence the high-temperature mechanical property of the nickel-based superalloy thin-wall casting and can improve the high-temperature mechanical property of the nickel-based superalloy thin-wall casting.
Specifically, the application provides a hot sizing process for a nickel-based superalloy thin-wall casting and the nickel-based superalloy thin-wall casting sized by the hot sizing process, wherein the nickel-based superalloy thin-wall casting comprises the following raw material components in percentage by weight: 0.06-0.20% of C, 7.40-8.20% of Cr, 1.5-2.5% of W, 3.5-5.5% of Mo, 7.6-8.5% of Al, 0.6-1.3% of Ti, 0.3-0.9% of Hf, less than or equal to 0.05% of B, less than or equal to 0.01% of Y and the balance of Ni;
the thermal sizing process specifically comprises the following steps:
step (1): placing the thin-wall nickel-based superalloy casting in an air-isolated environment, heating the environment to 1160-1200 ℃ within 2-5h, and raising the temperature of the thin-wall nickel-based superalloy casting along with the environment; the environment for isolating air is a vacuum environment; furthermore, the air-insulated environment may also be an environment filled with an inert gas;
step (2): preserving the heat of the nickel-based high-temperature alloy thin-wall casting under the environmental condition in the step (1) for 4-6 h;
and (3): cooling the nickel-based high-temperature alloy thin-wall casting treated in the step (2) along with the environment; when the environment is cooled to 800 ℃ of 600-;
the inert gas used in the thermal sizing process may be argon.
The present application is further illustrated below with reference to examples 1-4, comparative examples 1-3, and the associated test data.
Examples
Example 1
The embodiment provides a thermal sizing process for a nickel-based superalloy thin-wall casting, which is used for performing thermal sizing on the nickel-based superalloy thin-wall casting, wherein the nickel-based superalloy thin-wall casting comprises the following raw material components in percentage by weight: 0.07 percent of C, 7.6 percent of Cr, 2.0 percent of W, 4.5 percent of Mo, 8.2 percent of Al, 1.0 percent of Ti, 0.65 percent of Hf, less than or equal to 0.05 percent of B, less than or equal to 0.01 percent of Y and the balance of Ni. The thermal sizing process specifically comprises the following steps:
step (1): placing the nickel-based superalloy thin-wall casting in a vacuum heat treatment furnace, heating the vacuum heat treatment furnace to 1160 ℃ within 4h, and heating the nickel-based superalloy thin-wall casting along with the vacuum heat treatment furnace;
step (2): the nickel-based high-temperature alloy thin-wall casting is subjected to heat preservation in a vacuum heat treatment furnace in the step (1), and the heat preservation time is 4 hours; and (3): cooling the nickel-based high-temperature alloy thin-wall casting treated in the step (2) along with a vacuum heat treatment furnace; and when the vacuum heat treatment furnace is cooled to 760 ℃, filling argon gas into the vacuum heat treatment furnace to 0.2MPa, cooling to room temperature, and taking out the nickel-based superalloy thin-wall casting from the vacuum heat treatment furnace to obtain the hot-corrected nickel-based superalloy thin-wall casting.
Example 2
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the hot shape correction process of the embodiment are the same as those in the embodiment 1, and the difference between the hot shape correction process of the embodiment and the embodiment 1 is that in the hot shape correction process, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1180 ℃ along with a vacuum heat treatment furnace, the heat preservation time is 4 hours, and the rest operation steps and parameters of the hot shape correction process of the embodiment are the same as those in the embodiment 1.
Example 3
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the hot shape correction process of the embodiment are the same as those in the embodiment 1, and the difference between the hot shape correction process of the embodiment and the embodiment 1 is that in the hot shape correction process, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1200 ℃ along with a vacuum heat treatment furnace, the heat preservation time is 4 hours, and the rest operation steps and parameters of the hot shape correction process of the embodiment are the same as those in the embodiment 1.
Example 4
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the hot shape correction process of the embodiment are the same as those in the embodiment 1, and the difference between the hot shape correction process of the embodiment and the embodiment 1 is that in the hot shape correction process step, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1160 ℃ along with a vacuum heat treatment furnace, the heat preservation time is 6 hours, and the rest operation steps and parameters of the hot shape correction process of the embodiment are the same as those in the embodiment 1.
Comparative example
Comparative example 1
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the thermal shape correction process of the comparative example are the same as those in example 1, and the difference between the thermal shape correction process of the comparative example and example 1 is that in the thermal shape correction step, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1140 ℃ along with a vacuum heat treatment furnace, and the thermal shape correction is carried out for 4 hours, and the rest operation steps and parameters of the thermal shape correction process of the comparative example are the same as those in example 1.
Comparative example 2
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the thermal shape correction process of the comparative example are the same as those in example 1, and the difference between the thermal shape correction process of the comparative example and example 1 is that in the thermal shape correction step, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1220 ℃ along with a vacuum heat treatment furnace, and the thermal shape correction is carried out for 4 hours, and the rest operation steps and parameters of the thermal shape correction process of the comparative example are the same as those in example 1.
Comparative example 3
The raw material components of the thin-wall nickel-base superalloy casting subjected to shape correction by the thermal shape correction process of the comparative example are the same as those in example 1, and the difference between the thermal shape correction process of the comparative example and example 1 is that in the thermal shape correction step, the thin-wall nickel-base superalloy casting is heated from room temperature for 4 hours to 1160 ℃ along with a vacuum heat treatment furnace, and the thermal shape correction process is carried out for 3 hours, and the rest operation steps and parameters of the thermal shape correction process of the comparative example are the same as those of example 1.
The result of the detection
FIGS. 1 and 2 are schematic diagrams of a thin-walled nickel-base superalloy casting before and after thermal straightening using the thermal straightening process provided herein, respectively. Referring to fig. 1, it can be clearly seen that the nickel-based superalloy thin-wall casting obtained through the precision casting process has an obvious bending phenomenon, and the casting at the closing-up nozzle of the aero-engine has a high requirement on the dimensional precision of the casting, so that it is obvious that the nickel-based superalloy thin-wall casting only subjected to the precision casting cannot meet the requirement on the dimensional precision of the closing-up nozzle of the aero-engine. Referring to fig. 2, and comparing with fig. 1, it can be seen that the thin-wall casting of the nickel-based superalloy, which is subjected to shape correction by the thermal shape correction process, is flat and has no obvious bending phenomenon, so that the shape correction of the thin-wall casting of the nickel-based superalloy by the thermal shape correction process provided by the present application is performed, and the nickel-based superalloy thin-wall casting after the shape correction can meet the requirement of the closing-up nozzle part of the aircraft engine on the dimensional accuracy of the casting to the greatest extent.
Through the analysis, the size precision of the nickel-based high-temperature alloy thin-wall casting can meet the requirement of the closing-in nozzle part of the aero-engine on the size of the casting to the maximum extent by controlling the thermal sizing temperature and the thermal sizing time in the thermal sizing process.
The high-temperature mechanical properties of the nickel-base superalloy thin-wall castings subjected to the thermal shape correction by the thermal shape correction processes of the above examples 1 to 4 and the comparative examples 1 to 3 and the nickel-base superalloy thin-wall castings not subjected to the thermal shape correction are respectively detected, and are respectively subjected to electron microscope analysis, referring to the attached drawings 2 to 10; the results are shown in Table 1.
TABLE 1 high-temp. mechanical property test results of thin-walled Ni-based superalloy castings before and after thermal straightening
As shown in Table 1, the comparison of the high temperature mechanical property parameters of the thin-walled Ni-based superalloy castings subjected to shape correction by the thermal shape correction process of examples 1-4 with those of the thin-walled Ni-based superalloy castings not subjected to thermal shape correction shows that the high temperature mechanical properties of the thin-walled Ni-based superalloy castings subjected to shape correction by the thermal shape correction process are significantly improved, including tensile properties and durability, wherein the tensile strength, yield strength and elongation of the thin-walled Ni-based superalloy castings are improved. And under the condition that the lasting strength is 60MPa, the lasting time of the nickel-based high-temperature alloy thin-wall casting subjected to shape correction by the hot shape correction process is obviously prolonged. Therefore, the hot sizing process provided by the application is used for sizing the nickel-based superalloy thin-wall casting, the high-temperature mechanical property of the nickel-based superalloy thin-wall casting cannot be influenced, and the high-temperature mechanical property of the nickel-based superalloy thin-wall casting can be obviously improved.
By comparing the high-temperature mechanical property parameters of the nickel-base superalloy thin-wall casting subjected to the shape correction by the thermal shape correction process in the embodiment 1-3 and the nickel-base superalloy thin-wall casting subjected to the shape correction by the thermal shape correction process in the comparative example 1-2, the high-temperature mechanical property of the nickel-base superalloy thin-wall casting subjected to the shape correction by the thermal shape correction process in the embodiment 1-3 is obviously higher than that of the nickel-base superalloy thin-wall casting subjected to the shape correction by the thermal shape correction process in the comparative example 1-2, and it can be known that in the thermal shape correction process provided by the application, when the thermal shape correction temperature is controlled within the range of 1160-1200 ℃, the thermal shape correction process provided by the application is used for the thermal shape correction of the nickel-base superalloy thin-wall casting, and the tensile property and the durability of the nickel-base superalloy thin-wall casting can be obviously improved.
By comparing the high-temperature mechanical property parameters of the nickel-base superalloy thin-wall casting subjected to shape correction by using the thermal shape correction process of the comparative examples 1-2 with those of the nickel-base superalloy thin-wall casting not subjected to thermal shape correction, when the thermal shape correction temperature is lower than 1160 ℃, the tensile strength of the nickel-base superalloy thin-wall casting subjected to shape correction is lower than that of the nickel-base superalloy thin-wall casting not subjected to thermal shape correction under the condition that the temperature is 1100 ℃, the yield strength of the nickel-base superalloy thin-wall casting subjected to shape correction is not greatly different from that of the nickel-base superalloy thin-wall casting not subjected to thermal shape correction, and meanwhile, under the condition that the endurance strength is 60MPa, the endurance time of the nickel-base superalloy thin-wall casting subjected to shape correction is lower than that of the nickel-base superalloy thin-wall casting not subjected to thermal shape correction; when the thermal shape correction temperature is higher than 1220 ℃, under the condition of 1100 ℃, the tensile strength of the nickel-base superalloy thin-wall casting after the shape correction is lower than that of the nickel-base superalloy thin-wall casting before the thermal shape correction, and the lasting time of the nickel-base superalloy thin-wall casting after the shape correction is also lower than that of the nickel-base superalloy thin-wall casting before the thermal shape correction. In summary, the thermal sizing temperature of the thermal sizing process provided by the present application is preferably controlled within the range of 1160-.
As shown in table 1, by comparing the high temperature mechanical property parameters of the thin-walled nickel-base superalloy castings subjected to the hot shape-correcting process in examples 1 and 4 with those of the thin-walled nickel-base superalloy castings subjected to the hot shape-correcting process in comparative example 3, it can be seen that the high temperature mechanical property of the thin-walled nickel-base superalloy castings subjected to the hot shape-correcting process in examples 1 and 4 is significantly higher than that of the thin-walled nickel-base superalloy castings subjected to the hot shape-correcting process in comparative example 3, and it can be seen that in the hot shape-correcting process provided by the present application, when the hot shape-correcting time is controlled within the range of 4 to 6 hours, the tensile property and the durability of the thin-walled nickel-base superalloy castings subjected to the hot shape-correcting process provided by the present application can be significantly improved.
By comparing the high-temperature mechanical property parameters of the nickel-base superalloy thin-wall casting subjected to shape correction by using the thermal shape correction process of the comparative example 3 with those of the nickel-base superalloy thin-wall casting which is not subjected to thermal shape correction, when the thermal shape correction time is less than 4 hours, the tensile strength of the nickel-base superalloy thin-wall casting subjected to shape correction is lower than that of the nickel-base superalloy thin-wall casting not subjected to thermal shape correction under the condition that the temperature is 1100 ℃. In addition, considering that the longer time of the thermal sizing causes unnecessary consumption of time and resources to a certain extent, causes waste of resources and causes increase of production cost of the casting, under the thermal sizing process with the thermal sizing time of 6h, the nickel-based superalloy thin-wall casting after sizing has better high-temperature mechanical property, so that the higher value of the thermal sizing temperature is not deeply researched. In summary, the thermal sizing time of the thermal sizing process provided by the application is preferably controlled within the range of 4-6 h.
Referring to fig. 3 and 4, it can be seen that under the condition that other thermal shape correction parameters are not changed, when the thermal shape correction temperature is 1140 ℃, part of the primary gamma ' phase in the thin-wall nickel-base superalloy casting begins to dissolve and a small amount of fine secondary gamma ' phase is precipitated, so that the total content of the gamma ' phase in the thin-wall nickel-base superalloy casting is reduced, and the tensile property at 1100 ℃ and the endurance quality at 1100 ℃/60MPa of the thin-wall nickel-base superalloy casting after thermal shape correction are lower than those of the thin-wall nickel-base superalloy casting without thermal shape correction.
With continuing reference to fig. 5, it can be seen that, under the condition that other thermal shape correction parameters are not changed, when the thermal shape correction temperature is 1160 ℃, the primary γ 'of the thin-wall ni-based superalloy casting is successively dissolved along with the rise of the thermal shape correction temperature, and the precipitation content of the secondary γ' phase gradually increases and starts to grow up, so that the tensile property at 1100 ℃ and the durability at 1100 ℃/60Mpa of the thin-wall ni-based superalloy casting after thermal shape correction are both superior to those of the thin-wall ni-based superalloy casting without thermal shape correction.
With continuing reference to fig. 6, it can be seen that, under the condition that other thermal shape correction parameters are not changed, when the thermal shape correction temperature is 1180 ℃, with further increase of the thermal shape correction temperature, the primary γ 'of the thin-wall nickel-based superalloy casting is successively dissolved, and a large amount of secondary γ' phase is precipitated and grows, so that the tensile property of the thin-wall thermally-corrected nickel-based superalloy casting at 1100 ℃ and the durability at 1100 ℃/60MPa are maximized, and both of the tensile property and the durability are superior to the corresponding properties of the thin-wall nickel-based superalloy casting without thermal shape correction.
With continuing reference to fig. 7, it can be seen that under the condition that other thermal shape correction parameters are not changed, when the thermal shape correction temperature is 1200 ℃, along with the further increase of the thermal shape correction temperature, a large amount of primary gamma 'phase of the nickel-based superalloy thin-wall casting is dissolved, and a large amount of secondary gamma' phase is precipitated and grows, so that the tensile property and the endurance property at 1100 ℃/60MPa of the thermally-corrected nickel-based superalloy thin-wall casting are superior to those of the nickel-based superalloy thin-wall casting without thermal shape correction at 1100 ℃.
With continuing reference to fig. 8, it can be seen that, under the condition that other thermal shape correction parameters are not changed, when the thermal shape correction temperature is 1220 ℃, along with the continuous increase of the thermal shape correction temperature, the primary γ 'phase of the thin-wall nickel-based superalloy casting is substantially dissolved, and the secondary γ' phase is completely precipitated and grown up, so that the tensile property at 1100 ℃ and the endurance property at 1100 ℃/60MPa of the thin-wall thermally corrected nickel-based superalloy casting are both lower than those of the thin-wall nickel-based superalloy casting which is not subjected to thermal shape correction.
With continuing reference to fig. 9 and comparing with fig. 3 and fig. 5, it can be seen that under the condition that other thermal shape-correcting parameters are not changed, when the thermal shape-correcting temperature is 1160 ℃ and the thermal shape-correcting time is 6 hours, the primary gamma 'phase of the nickel-based superalloy thin-wall casting is partially dissolved, and the secondary gamma' phase is precipitated, so that the tensile property and the endurance property at 1100 ℃ and 1100 ℃/60MPa of the thermally-corrected nickel-based superalloy thin-wall casting are superior to those of the nickel-based superalloy thin-wall casting which is not subjected to thermal shape correction.
With continuing reference to fig. 10 and comparing with fig. 3 and fig. 5, it can be seen that under the condition that other thermal shape-correcting parameters are not changed, when the thermal shape-correcting temperature is 1160 ℃ and the thermal shape-correcting time is 3 hours, the primary γ 'phase of the thin-wall nickel-base superalloy casting is partially dissolved, and the secondary γ' phase is precipitated, so that the tensile property of the thin-wall thermally-corrected nickel-base superalloy casting at 1100 ℃ is lower than the corresponding property of the thin-wall nickel-base superalloy casting which is not subjected to thermal shape correction.
Through the analysis, the control of the thermal sizing temperature and the thermal sizing time in the thermal sizing process can be known, so that the dimensional accuracy of the nickel-based superalloy thin-wall casting can meet the requirement of the closing-in nozzle part of an aircraft engine on the size of the casting to the maximum extent, and the high-temperature mechanical property of the nickel-based superalloy thin-wall component can be obviously improved.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (8)
1. A hot sizing process for a nickel-based superalloy thin-wall casting is characterized by comprising the following steps:
step (1): placing the thin-wall nickel-based superalloy casting in an air-isolated environment, heating the environment to 1160-1200 ℃, and heating the thin-wall nickel-based superalloy casting along with the environment;
step (2): preserving the heat of the nickel-based superalloy thin-wall casting under the environmental condition in the step (1) for 4-6 hours;
and (3): and (3) cooling the nickel-based superalloy thin-wall casting treated in the step (2) along with the environment to obtain the nickel-based superalloy thin-wall casting subjected to thermal shape correction.
2. The hot sizing process of the nickel-base superalloy thin-wall casting according to claim 1, wherein: heating the air-isolated environment in the step (1) to 1160-1200 ℃ within 2-5 h.
3. The hot sizing process of the nickel-base superalloy thin-wall casting according to claim 1, wherein: the air-insulated environment is a vacuum environment.
4. The hot sizing process of the nickel-base superalloy thin-wall casting according to claim 1, wherein: when the environment is cooled to 600-800 ℃, filling inert gas of 0.1-0.4MPa into the environment and cooling.
5. The hot sizing process of the nickel-base superalloy thin-wall casting according to claim 4, wherein: and cooling the environment to the normal temperature.
6. The hot sizing process of the nickel-base superalloy thin-wall casting according to claim 4, wherein: the inert gas is argon.
7. A thin-walled casting of nickel-base superalloy characterized in that it is hot-formed according to any of claims 1 to 6.
8. The thin-walled nickel-base superalloy casting of claim 7, wherein: the nickel-based superalloy thin-wall casting comprises the following raw material components in percentage by weight: 0.06-0.20% of C, 7.40-8.20% of Cr, 1.5-2.5% of W, 3.5-5.5% of Mo, 7.6-8.5% of Al, 0.6-1.3% of Ti, 0.3-0.9% of Hf, less than or equal to 0.05% of B, less than or equal to 0.01% of Y and the balance of Ni.
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