High-temperature alloy part reinforced by prefabricated superlattice layer staggering in ordered phase as well as preparation method and application of high-temperature alloy part

Abstract

The invention belongs to the technical field of high-temperature metal material processing, and particularly discloses a high-temperature alloy workpiece reinforced by prefabricated superlattice stacking in an ordered phase and a preparation method and application thereof.The preparation method comprises the steps that 1, according to the design size of the high-temperature alloy workpiece, size information of a blank A is determined through finite element simulation iterative calculation; 2) preparing a blank A; (3) the blank A is subjected to heat treatment; (4) the blank A is subjected to surface machining, and a blank B is obtained; (5) the blank B is subjected to pressure maintaining forging in an isothermal forging press, so that the blank B is subjected to pre-creep deformation to form a gamma'phase internal superlattice layer fault, and a blank C is obtained; and (6) the blank C is subjected to annealing treatment and then machined to the designed size, and the target high-temperature alloy workpiece is obtained. By means of the technology, the discontinuous superlattice layer fault in the ordered strengthening phase of the high-temperature alloy can be obtained, and the structure formed by the structure has higher tensile strength and creep / endurance strength and can meet the strict requirements of aerospace for mechanical properties.

Description

Technical Field

[0001] This invention belongs to the field of high-temperature metal material processing technology, specifically relating to a high-temperature alloy part reinforced by pre-fabricated superlattice stacking faults in an ordered phase, its preparation method, and its application. Background Technology

[0002] High-temperature alloys are key materials for core components in the aerospace field, and their mechanical properties under extreme high-temperature and high-stress environments are a major research focus. In precipitation-strengthened high-temperature alloys, the γ′ phase (Ni3(Al, Ti)) becomes the main strengthening phase due to its L12-type ordered crystal structure. In this structure, Al atoms occupy the vertices of the face-centered cubic lattice, and Ni atoms occupy the face-centered positions. This ordered occupancy endows the γ′ phase with unique mechanical properties, giving it excellent thermodynamic stability and strengthening effect.

[0003] Studies have shown that dislocation slip is the main mechanism of plastic deformation in high-temperature alloys, while stacking faults, as planar defects in crystal structures, can effectively hinder dislocation movement, thereby improving material strength. Superlattice stacking faults (SSFs) formed in ordered phases exhibit higher stability and more significant strengthening effects due to their synergistic effect with the ordered structure. However, in traditional high-temperature alloy manufacturing processes, the formation of superlattice stacking faults often depends on dynamic deformation during service, making it difficult to controllably introduce them during the manufacturing stage, thus limiting the improvement of tensile strength and creep / endurance strength.

[0004] Currently, the technology for controlling γ′ phase precipitation through heat treatment is relatively mature, but there is still a lack of effective methods for pre-fabricating superlattice stacking faults within ordered phases. Some studies have attempted to induce stacking faults through cold deformation or thermomechanical treatment, but cold deformation easily introduces residual stress, and thermomechanical treatment has a narrow process window, making it difficult to accurately control the stacking fault density and distribution.

[0005] To overcome the aforementioned bottlenecks, it is urgent to develop a process that introduces superlattice stacking faults during the preparation stage to achieve the synergistic effect of γ′ phase strengthening and stacking fault strengthening, thereby further improving the tensile strength and creep / endurance strength of high-temperature alloys to meet the stringent mechanical performance requirements of aerospace. Summary of the Invention

[0006] The purpose of this invention is to overcome the shortcomings of the prior art and provide a high-temperature alloy part with pre-invented superlattice stacking faults in an ordered phase, its preparation method and application. It is mainly used to solve the problem that it is difficult to controllably introduce superlattice stacking faults in an ordered phase in the traditional high-temperature alloy preparation process, resulting in insufficient tensile strength and creep / endurance strength of the material. This invention optimizes the blank size through finite element simulation, induces pre-creep deformation through isothermal forging, and controls the stacking fault structure by combining annealing treatment, thereby improving the tensile strength and creep / endurance strength of the high-temperature alloy material.

[0007] The objective of this invention is achieved through the following technical solution: In a first aspect, the present invention provides a method for preparing a high-temperature alloy component strengthened by pre-fabricated superlattice stacking faults within an ordered phase, comprising the following steps: Step 1: Based on the design dimensions of the high-temperature alloy part, determine the dimensional information of blank A through finite element simulation iterative calculation; Step 2: Prepare blank A as determined in Step 1 using nickel-based superalloy as raw material; Step 3: Perform standard heat treatment on the blank A prepared in Step 2 (this step requires ensuring that the properties of the alloy itself reach the current technical level before pressure forging deformation, and the strengthening effect of subsequent steps will be superimposed on this basis). Step 4: Perform surface machining on blank A after standard heat treatment in Step 3 until the roughness Ra ≤ 3.2 μm to obtain blank B; Step 5: The blank B obtained in Step 4 is subjected to pressure forging in an isothermal forging press to cause pre-creep deformation of blank B to form superlattice stacking faults in the γ′ phase, thereby obtaining blank C. Step 6: Anneal the blank C obtained in Step 5, and then process it to the design size to obtain the target high-temperature alloy part.

[0008] Furthermore, in step 1, the specific process of determining the dimensional information of blank A through finite element simulation iterative calculation is as follows: Step 1.1: Import the design dimensions of the high-temperature alloy part into the finite element simulation software; Step 1.2: Set the mold temperature to 650℃~850℃ (the billet temperature is set to 650℃~850℃ simultaneously), and set the initial holding pressure according to the cross-sectional area of ​​the high-temperature alloy part in contact with the mold × stress of 600MPa~1035MPa; Step 1.3: Simulate the pressure holding forging process, requiring the stress at all locations inside the high-temperature alloy part to reach 600MPa to 1035MPa within 0.5h to 1h, and the pressure holding time to be set to 50h to 200h; Step 1.4: Record the vertical compression Y and lateral elongation X during the simulated pressure holding forging process; Step 1.5: Add compensation amounts Y and X to the design dimensions, and iterate and correct until the simulation results meet the design dimension requirements, to obtain the compensation dimensions Yn and Xn, and finally obtain the dimension information of the blank A.

[0009] Furthermore, in step 2, the mass fraction of the γ′ phase in the nickel-based superalloy is ≥35%.

[0010] Furthermore, in step 2, the method for preparing the blank A includes powder metallurgy, casting, and forging.

[0011] Furthermore, in step 3, the standard heat treatment is performed according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook".

[0012] Further, in step 5, the pressure holding forging process is as follows: the blank B obtained in step 4 is placed in the isothermal forging press mold, and pressure holding forging is carried out under the conditions of mold temperature of 650℃~850℃ and blank B temperature of 650℃~850℃. The pressure holding is calculated according to the cross-sectional area of ​​blank B in contact with the mold × stress of 600MPa~1035MPa. During the pressure-holding forging process, the mold temperature is monitored in real time. When the mold temperature drops by more than 50°C, the forging is interrupted, the mold is reheated to the set temperature, and the blank B is returned to the furnace to 650°C to 850°C and held for 1 to 5 hours before forging continues. This is to ensure that there is no excessive temperature loss during the pressure-holding forging process.

[0013] Preferably, it should be set to 850MPa~1035MPa.

[0014] Furthermore, in step 5, during the pressure holding forging, the pressure holding time is the sum of the time required for all positions inside the high-temperature alloy part to reach the set stress in step 1 and the pressure holding time.

[0015] Furthermore, in step 6, the annealing temperature is 100℃~200℃ lower than the aging temperature of the high-temperature alloy, and the annealing time is ≥6h.

[0016] Secondly, the present invention provides a high-temperature alloy component reinforced by pre-fabricated superlattice stacking faults within an ordered phase, wherein the high-temperature alloy component is prepared by the above-described preparation method.

[0017] Thirdly, the present invention also provides an application of the above-mentioned ordered phase prefabricated superlattice stacking fault strengthened high-temperature alloy parts, which are used in scenarios where higher requirements are placed on tensile strength and creep / endurance strength, such as high-temperature load-bearing components for aero-engines, rocket engines or power plants.

[0018] Compared with the prior art, the present invention has the following beneficial effects: The preparation method provided by this invention strengthens high-temperature alloys by pre-forming superlattice stacking faults within the γ′ phase. Its core lies in utilizing the synergistic effect of the ordered phase crystal structure and stacking fault defects to hinder dislocation movement. Based on existing methods such as powder metallurgy, casting, and forging, this invention adds an isothermal pressure forging process to the heat treatment of high-temperature alloy parts. This allows nickel-based high-temperature alloy billets with a γ′ phase mass fraction ≥35% to undergo pre-creep deformation under specific conditions (by controlling the temperature, stress, and time of the mold and billet, avoiding insufficient stacking fault formation due to excessively low temperature or stress, or the formation of microtwins detrimental to creep performance due to excessively high temperature or stress) to form superlattice stacking faults within the γ′ phase. Specifically, the dislocations are represented by a Burgers vector of "a / 6". <112> or a / 3 <112> "When a superlattice partial dislocation slips into the γ′ phase, it leaves a superlattice stacking fault in the crystal lattice. This stacking fault disrupts the ordered atomic arrangement of the L12 structure, forming a local atomic fault plane. The ordered lattice on both sides of the stacking fault generates a reverse stress field due to the energy difference, forming an 'energy barrier' for subsequent dislocation slip. After annealing, the additional dislocations in the matrix are basically eliminated, and the interface energy between the stacking fault and the γ′ phase is reduced, improving structural stability. The interaction between the dislocation and newly generated dislocations during subsequent service is further enhanced, requiring the dislocation to overcome the stacking fault energy barrier." Only by traversing or bypassing stacking faults can the resistance to plastic deformation of the alloy be significantly increased, thereby improving the tensile strength and creep / endurance strength of the material. In addition, by iteratively compensating for the blank size through finite element simulation, the final part shape is ensured to remain unchanged, while ensuring uniform stress distribution during deformation. This results in a high-density and uniform distribution of stacking faults within the γ′ phase, avoiding the problem of discrete strengthening effects caused by uneven deformation in traditional processes. Ultimately, this achieves a synergistic effect of precipitation strengthening (γ′ phase) and stacking fault strengthening, meeting the service requirements of aerospace components for high performance (tensile strength and creep / endurance strength). Attached Figure Description

[0019] The accompanying drawings are incorporated in and form part of this specification, and together with the description serve to explain the principles of the invention.

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a flowchart of the preparation method of the high-temperature alloy part with pre-fabricated superlattice stacking faults in the ordered phase according to the present invention; Figure 2 This is a transmission electron microscope image of a high-temperature alloy part according to Embodiment 1 of the present invention; Figure 3 This is a transmission electron microscope image of a high-temperature alloy part, which is Comparative Example 1 of this invention. Figure 4 This is a transmission electron microscope image of a high-temperature alloy component, which is Comparative Example 2 of this invention. Detailed Implementation

[0022] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples consistent with some aspects of the invention as detailed in the appended claims.

[0023] To enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0024] Example 1 This embodiment produces a certain type of FGH4096 part for an aero-engine. The part has a design dimension of φ650×40mm. Figure 1 As shown, the specific preparation process is as follows: 1) The design dimensions of the FGH4096 part, φ650×40mm, were imported into finite element simulation software to simulate and analyze the stress transfer within the billet during the pressure-holding forging process. The die temperature was set to 750℃, and the initial holding pressure was set. The initial holding pressure was calculated based on the product of the cross-sectional area of ​​the part and the die contact area and the stress. The stress was set to 850MPa. Calculations showed that the forging pressure applied was approximately 282MN. The upper die was input as the holding pressure in the finite element simulation software, and the pressure was set to 282MN for simulation. After simulation, the stress at all locations inside the part reached 850MPa after 0.7h. The holding time was 120h. Simultaneously, the downward pressure in the height direction (10mm) and the lateral elongation (13mm) were recorded. Because deformation occurs during pressure holding, the final part will be augmented with a height of Y1=10mm and a lateral elongation of X1=13mm, and the above process will be repeated. After three iterations: the first compensation of Y1=10mm and X1=13mm resulted in bulging at the outer edge of the part, and the diameter could not be guaranteed; the second correction of Y2=16.5mm and X2=20.3mm satisfied the part design dimensions after pressure holding, thus obtaining the final dimensions of blank A. 2) Blank A (γ′ phase mass fraction ≥36%) was prepared using powder metallurgy. 3) Perform standard heat treatment on blank A, specifically according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook", specifically using solution treatment: (1140~1170)℃×2~4h / oil quenching + aging: (740~770)℃×(10~20h) / air cooling; 4) Perform surface machining on blank A after standard heat treatment in step 3), and the surface roughness after machining is 3.2μm to obtain blank B; 5) Place the blank B obtained in step 4) into an isothermal forging press for pressure holding forging to achieve pre-creep deformation of the blank. The specific process parameters are set as follows: the temperature of both the isothermal forging die and blank B is set to 750℃; during the forging process, when the die and blank B begin to contact, the holding pressure is controlled at 282MN, corresponding to a stress of 850MPa, and the holding time is set to 120.7h.

[0025] During the pressure holding period, the mold needs to be continuously heated, and the temperature change of the mold needs to be monitored in real time. When the temperature drop of the mold exceeds 50°C, the mold needs to be reheated. At the same time, the blank B is returned to the furnace for reheating. The reheating temperature is 750°C, the original blank temperature, and the reheating process lasts for 2 hours. After the above operations, blank C is finally obtained.

[0026] 6) Anneal the blank C after pressure forging in step 5). Specifically, place the blank C in a heat treatment equipment, set the annealing temperature to 600℃, and the holding time to 8h. After the holding time is over, use furnace cooling to slowly lower the blank C to room temperature. Finally, process it to the design size to obtain the FGH4096 part with specifications of φ650×40mm.

[0027] Performance testing Tensile properties and creep properties were tested at different locations of the blank A after standard heat treatment in step 3) of Example 1, and the corresponding test results are shown in Tables 1 and 2 below. Simultaneously, tensile properties and creep properties were tested at different locations of the final FGH4096 part prepared in this example, and the corresponding test results are shown in Tables 3 and 4 below. Table 1. Tensile properties of blank A at different locations after standard heat treatment in step 3) of Example 1. Table 2 Creep properties of blank A after standard heat treatment in step 3) of Example 1 Table 3 Tensile properties of the final part at different locations in Example 1 Table 4 Creep properties of the final part at different locations in Example 1 Example 2 This embodiment produces a certain type of FGH4096 component for an aero-engine. The component has a design size of φ350×40mm, and the specific manufacturing process is as follows: 1) The design dimensions of the FGH4096 part, φ350×40mm, were imported into finite element simulation software to simulate and analyze the stress transfer within the billet during the pressure-holding forging process. The die temperature was set to 650℃, and the initial holding pressure was calculated based on the product of the cross-sectional area of ​​the part and the die and the stress. The stress was set to 1035MPa. Calculations showed that the forging pressure applied was approximately 100MN. The upper die was input as the holding pressure in the finite element simulation software, and the pressure was set to 100MN for simulation. After simulation, the stress at all locations inside the part reached 1035MPa after 0.52 hours. The holding time was 120 hours. Simultaneously, the downward pressure in the height direction (12.8mm) and the lateral elongation (11.2mm) were recorded. Because deformation occurs during pressure holding, the height Y1=12.8mm and the lateral elongation X1=11.2mm will be added to the final part, and the above process will be repeated; the process will be continuously corrected and iterated to obtain Y3=13.2mm and X3=12.9mm, which will meet the part design size requirements after pressure holding, thus obtaining the final size of blank A. 2) Blank A (γ′ phase mass fraction ≥36%) was prepared using powder metallurgy. 3) Perform standard heat treatment on blank A, specifically according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook", specifically using solution treatment: (1140~1170)℃×2~4h / oil quenching + aging: (740~770)℃×(10~20h) / air cooling; 4) Perform surface machining on blank A after standard heat treatment in step 3), and the surface roughness after machining is 3.2μm to obtain blank B; 5) Place the blank B obtained in step 4) into an isothermal forging press for pressure holding forging to achieve pre-creep deformation of the blank. The specific process parameters are set as follows: the temperature of both the isothermal forging die and blank B is set to 650℃; during the forging process, when the die and blank B begin to contact, the holding pressure is controlled at 100MN, corresponding to a stress of 1035MPa, and the holding time is set to 120.52h. During the pressure holding period, the mold needs to be continuously heated, and the temperature change of the mold needs to be monitored in real time. When the temperature drop of the mold exceeds 50°C, the mold needs to be reheated. At the same time, the blank B is returned to the furnace for reheating. The reheating temperature is 650°C, the original blank temperature, and the reheating process lasts for 2 hours. After the above operations, blank C is finally obtained.

[0028] 6) Anneal the blank C after pressure forging in step 5). Specifically, place the blank C in a heat treatment equipment, set the annealing temperature to 600℃, and the holding time to 8h. After the holding time is over, use furnace cooling to slowly lower the blank C to room temperature. Finally, process it to the design size to obtain the FGH4096 part with specifications of φ350×40mm.

[0029] Performance testing Tensile and creep properties were tested at different locations of the blank A after standard heat treatment in step 3) of Example 2. The corresponding test results were at the same level as those in Tables 1 and 2. Meanwhile, tensile and creep properties were tested at different locations of the final FGH4096 part prepared in this comparative example. The corresponding test results are shown in Tables 5 and 6 below. Table 5 Tensile properties of the final part at different locations in Example 2 Table 6 Creep properties of the final part at different locations in Example 2 Example 3 This embodiment produces a GH4079 part for an aero-engine, with design dimensions of φ410×60mm. Figure 1 As shown, the specific preparation process is as follows: 1) The design dimensions of the GH4079 part, φ410×60mm, were imported into finite element simulation software to simulate and analyze the stress transfer within the billet during the pressure holding forging process. The die temperature was set to 850℃, and the initial holding pressure was calculated based on the product of the cross-sectional area of ​​the part and the die contact area and the stress. The stress was set to 900MPa, and the calculated forging pressure was approximately 119 MN. The upper die was input as the holding pressure in the finite element simulation software, and the pressure was set to 119 MN for simulation. After simulation, the stress at each location inside the part reached 900MPa after 0.8h, and the holding time was 130h. The downward pressure in the height direction was recorded as 13mm, and the lateral elongation was recorded as 16mm. Due to deformation caused by pressure holding, the height direction Y1=13mm and the lateral elongation X1=16mm were added to the final part, and the above process was repeated. It was verified that after the first correction, the part design dimensions were met after the pressure holding was completed, thus obtaining the final dimensions of the blank A. 2) The blank A (γ′ phase mass fraction ≥42%) is prepared by a combination of single casting, free forging for initial blanking, and final forging. 3) Perform standard heat treatment on blank A, specifically according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook". Specifically, the process is as follows: annealing: 1040℃×4h / air cooling, solution treatment: (1130~1150)℃×8h / air cooling, aging: 850℃×6h / air cooling + 780℃×(10~16)h / air cooling. 4) Perform surface machining on blank A after standard heat treatment in step 3), and the surface roughness after machining is 3.2μm to obtain blank B; 5) Place the blank B obtained in step 4) into an isothermal forging press for pressure holding forging to achieve pre-creep deformation of the blank. The specific process parameters are set as follows: the temperature of both the isothermal forging die and blank B is set to 850℃; during the forging process, when the die and blank B begin to contact, the holding pressure is controlled at 119 MN, corresponding to a stress of 900MPa, and the holding time is set to 130.8h. During the pressure holding period, the mold needs to be continuously heated, and the temperature change of the mold needs to be monitored in real time. When the temperature drop of the mold exceeds 50°C, the mold needs to be reheated. At the same time, the blank B is returned to the furnace for reheating. The reheating temperature is 850°C, the original blank temperature, and the reheating process lasts for 2 hours. After the above operations, blank C is finally obtained.

[0030] 6) Anneal the blank C after pressure forging in step 5). Specifically, place the blank C in a heat treatment equipment, set the annealing temperature to 680℃, and hold it for 7 hours. After the holding time is over, use furnace cooling to slowly lower the blank C to room temperature. Finally, process it to the designed size to obtain the GH4079 part with specifications of φ410×60mm.

[0031] Performance testing Tensile properties and creep properties were tested at different locations of the blank A after standard heat treatment in step 3) of Example 3, and the corresponding test results are shown in Tables 7 and 8 below. Simultaneously, tensile properties and creep properties were tested at different locations of the final GH4079 part prepared in this example, and the corresponding test results are shown in Tables 9 and 10 below. Table 7 Tensile properties of blank A at different locations after standard heat treatment in step 3) of Example 3 Table 8 Creep properties of blank A after standard heat treatment in step 3) of Example 3 Table 9 Tensile properties of the final part at different locations in Example 3 Table 10 Creep properties of the final part at different locations in Example 3 Comparative Example 1 (This comparative example is a comparative test conducted with Example 1 using a low stress of 590 MPa, which is 600 MPa to 1035 MPa lower than the range defined in this invention) This comparative example shows the fabrication of a certain type of FGH4096 aero-engine component. The component has a design size of φ650×40mm, and the specific fabrication process is as follows: 1) The design dimensions of the FGH4096 part, φ650×40mm, were imported into finite element simulation software to simulate and analyze the stress transfer within the billet during the pressure holding forging process. The die temperature was set to 750℃, and the initial holding pressure was calculated based on the product of the cross-sectional area of ​​the part and the die and the stress. The stress was set to 590MPa, and the calculated forging pressure was approximately 196MN. The upper die was input as the holding pressure in the finite element simulation software, and the pressure was set to 196MN for simulation. After simulation, the stress at each location inside the part reached 590MPa after 0.6h, and the holding time was 120h. The downward pressure in the height direction was recorded as 9mm, and the lateral elongation as 11mm was recorded. Due to deformation caused by pressure holding, the height direction Y1=9mm and the lateral elongation X1=11mm were added to the final part, and the above process was repeated. It was verified that after the first correction, the part design dimensions were met after the pressure holding was completed, thus obtaining the final dimensions of the blank A. 2) Blank A (γ′ phase mass fraction ≥36%) was prepared using powder metallurgy. 3) Perform standard heat treatment on blank A, specifically according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook", specifically (1140~1170)℃×2~4h / oil quenching + aging: (740~770)℃×(10~20h) / air cooling; 4) Perform surface machining on blank A after standard heat treatment in step 3), and the surface roughness after machining is 3.2μm to obtain blank B; 5) Place the blank B obtained in step 4) into an isothermal forging press for pressure holding forging to achieve pre-creep deformation of the blank. The specific process parameters are set as follows: the temperature of both the isothermal forging die and blank B is set to 750℃; during the forging process, when the die and blank B begin to contact, the holding pressure is controlled at 196MN, corresponding to a stress of 590MPa, and the holding time is set to 120.6h. During the pressure holding period, the mold needs to be continuously heated, and the temperature change of the mold needs to be monitored in real time. When the temperature drop of the mold exceeds 50°C, the mold needs to be reheated. At the same time, the blank B is returned to the furnace for reheating. The reheating temperature is 750°C, the original blank temperature, and the reheating process lasts for 2 hours. After the above operations, blank C is finally obtained.

[0032] 6) Anneal the blank C after pressure forging in step 5). Specifically, place the blank C in a heat treatment equipment, set the annealing temperature to 600℃, and the holding time to 8h. After the holding time is over, use furnace cooling to slowly lower the blank C to room temperature. Finally, process it to the design size to obtain the FGH4096 part with specifications of φ650×40mm.

[0033] Performance testing Tensile and creep properties were tested at different locations of the blank A after standard heat treatment in step 3) of Comparative Example 1. The corresponding test results were at the same level as those in Tables 1 and 2. At the same time, tensile and creep properties were tested at different locations of the final FGH4096 part prepared in this comparative example. The corresponding test results are shown in Tables 11 and 12 below: Table 11 Tensile properties of the final part at different locations in Comparative Example 1 Table 12 Creep properties of the final part at different locations in Comparative Example 1 Comparative Example 2 (This comparative example is a comparative test conducted with Example 2 using a high stress of 1100 MPa, which exceeds the range of 600 MPa to 1035 MPa beyond the limits of this invention) This comparative example shows the fabrication of a certain type of FGH4096 aero-engine component. The component has a design size of φ350×40mm, and the specific fabrication process is as follows: 1) The design dimensions of the FGH4096 part (φ350×40mm) were imported into finite element simulation software to simulate and analyze the stress transfer within the billet during the pressure-holding forging process. The die temperature was set to 650℃, and the initial holding pressure was calculated based on the product of the cross-sectional area of ​​the part and the die contact area and the stress. The stress was set to 1100MPa. Calculations showed that the forging pressure applied was approximately 10⁶MN. The upper die was input as the holding pressure in the finite element simulation software, and the pressure was set to 10⁶MN for simulation. After simulation, the stress at all locations inside the part reached 1100MPa after 0.41 hours. The holding time was 120 hours. The downward pressure in the height direction (13mm) and the lateral elongation (12mm) were recorded simultaneously. Because deformation occurs during pressure holding, the height Y1=13mm and the lateral elongation X1=12mm will be added to the final part, and the above process will be repeated; the process will be continuously corrected and iterated to obtain Y3=13.8mm and X3=14.3mm, which will meet the part design size requirements after pressure holding, thus obtaining the final size of blank A. 2) Blank A (γ′ phase mass fraction ≥36%) was prepared using powder metallurgy. 3) Perform standard heat treatment on blank A, specifically according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook", specifically (1140~1170)℃×2~4h / oil quenching + aging: (740~770)℃×(10~20h) / air cooling; 4) Perform surface machining on blank A after standard heat treatment in step 3), and the surface roughness after machining is 3.2μm to obtain blank B; 5) Place the blank B obtained in step 4) into an isothermal forging press for pressure holding forging to achieve pre-creep deformation of the blank. The specific process parameters are set as follows: the temperature of both the isothermal forging die and blank B is set to 650℃; during the forging process, when the die and blank B begin to contact, the holding pressure is controlled at 106MN, corresponding to a stress of 1100MPa, and the holding time is set to 120.41h. During the pressure holding period, the mold needs to be continuously heated, and the temperature change of the mold needs to be monitored in real time. When the temperature drop of the mold exceeds 50°C, the mold needs to be reheated. At the same time, the blank B is returned to the furnace for reheating. The reheating temperature is 650°C, the original blank temperature, and the reheating process lasts for 2 hours. After the above operations, blank C is finally obtained.

[0034] 6) Anneal the blank C after pressure forging in step 5). Specifically, place the blank C in a heat treatment equipment, set the annealing temperature to 600℃, and the holding time to 8h. After the holding time is over, use furnace cooling to slowly lower the blank C to room temperature. Finally, process it to the design size to obtain the FGH4096 part with specifications of φ350×40mm.

[0035] Performance testing Tensile and creep properties were tested at different locations of the blank A after standard heat treatment in step 3) of Comparative Example 2. The corresponding test results were at the same level as those in Tables 1 and 2. At the same time, tensile and creep properties were tested at different locations of the final FGH4096 part prepared in this comparative example. The corresponding test results are shown in Tables 13 and 14 below: Table 13 Tensile properties of the final part at different locations in Comparative Example 2 Table 14 Creep properties of the final part at different locations in Comparative Example 2 The test results of Examples 1-3 and Comparative Examples 1-2 show that the high-temperature alloy parts finally prepared by the method of the present invention have improved tensile strength and creep / rupture strength compared with the material properties after standard heat treatment. Furthermore, the comparative examples show that even with the addition of isothermal pressure forging, the superlattice stacking fault structure, where the faults exist only in the γ′ phase, can only be achieved within a specific temperature and stress range (650-850℃ / 600-1035MPa). Figure 2 As shown, this is because: (1) if the temperature is below 650℃, higher stress is required to provide higher energy for the decomposition of full dislocations, and the pressure may exceed hundreds of thousands of tons, which is not in line with the actual engineering for existing press equipment; for high-temperature alloys, dislocation climb is likely to occur above 850℃, and it is difficult for dislocation decomposition to occur, making it difficult to control the process window; (2) when the stress is less than 600MPa (comparative example 1 stress 590MPa), due to insufficient driving force for dislocation activation by the load, no full dislocation decomposition will occur in the alloy, making it difficult to form partial dislocations, and therefore it is impossible to form stacking faults, forming a large number of full dislocations in the matrix, such as Figure 3 As shown; if the stress exceeds 1035 MPa (comparative Example 2 stress 1100 MPa), stacking faults will extend through the γ′ phase and the matrix, reaching the grain boundaries and continuously thickening to form microtwins tens of nanometers in size, such as... Figure 4 As shown, although microtwins hinder dislocations and increase tensile strength, they significantly reduce the creep properties of the alloy because the twins will continuously thicken during creep, leading to deformation.

[0036] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention.

[0037] It should be understood that the present invention is not limited to the content already described above, and various modifications and changes can be made without departing from its scope. The scope of the present invention is limited only by the appended claims.

Claims

1. A method for preparing a high-temperature alloy component reinforced with pre-existing superlattice stacking faults within an ordered phase, characterized in that, Includes the following steps: Step 1: Based on the design dimensions of the high-temperature alloy part, determine the dimensional information of blank A through finite element simulation iterative calculation; Step 2: Prepare blank A as determined in Step 1 using nickel-based superalloy as raw material; Step 3: Perform standard heat treatment on the blank A prepared in step 2; Step 4: Perform surface machining on blank A after standard heat treatment in Step 3 until the roughness Ra ≤ 3.2 μm to obtain blank B; Step 5: The blank B obtained in Step 4 is subjected to pressure forging in an isothermal forging press to cause pre-creep deformation of blank B to form superlattice stacking faults in the γ′ phase, thereby obtaining blank C. Step 6: Anneal the blank C obtained in Step 5, and then process it to the design size to obtain the target high-temperature alloy part.

2. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 1, the specific process of determining the dimensional information of blank A through finite element simulation iterative calculation is as follows: Step 1.1: Import the design dimensions of the high-temperature alloy part into the finite element simulation software; Step 1.2: Set the mold temperature to 650℃~850℃, and set the initial holding pressure according to the cross-sectional area of ​​the high-temperature alloy part in contact with the mold × stress of 600MPa~1035MPa; Step 1.3: Simulate the pressure holding forging process, requiring the stress at all locations inside the high-temperature alloy part to reach 600MPa to 1035MPa within 0.5h to 1h, and the pressure holding time to be set to 50h to 200h; Step 1.4: Record the vertical compression Y and lateral elongation X during the simulated pressure holding forging process; Step 1.5: Add compensation amounts Y and X to the design dimensions, and iterate and correct until the simulation results meet the design dimension requirements, to obtain the compensation dimensions Yn and Xn, and finally obtain the dimension information of the blank A.

3. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 2, the mass fraction of the γ′ phase in the nickel-based superalloy is ≥35%.

4. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 2, the methods for preparing the blank A include powder metallurgy, casting, and forging.

5. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 3, the standard heat treatment is performed according to the process of the corresponding high-temperature alloy grade in the "Chinese High-Temperature Alloy Handbook".

6. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 5, the pressure holding forging process is as follows: the blank B obtained in step 4 is placed in the isothermal forging press mold, and pressure holding forging is carried out under the conditions of mold temperature of 650℃~850℃ and blank B temperature of 650℃~850℃. The pressure holding is calculated according to the cross-sectional area of ​​blank B in contact with the mold × stress of 600MPa~1035MPa. During the pressure-holding forging process, the mold temperature is monitored in real time. When the mold temperature drops by more than 50°C, the forging is interrupted, the mold is reheated to the set temperature, and the blank B is returned to the furnace to 650°C to 850°C and held for 1 to 5 hours before forging continues.

7. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 5, during the pressure holding forging, the pressure holding time is the sum of the time required for all positions inside the high-temperature alloy part to reach the set stress in step 1 and the pressure holding time.

8. The method for preparing high-temperature alloy parts with pre-fabricated superlattice stacking faults in ordered phases according to claim 1, characterized in that, In step 6, the annealing temperature is 100℃~200℃ lower than the aging temperature of the high-temperature alloy, and the annealing time is ≥6h.

9. A high-temperature alloy component reinforced with pre-existing superlattice stacking faults within an ordered phase, characterized in that, The high-temperature alloy component is prepared by the preparation method described in any one of claims 1 to 8.

10. An application of a high-temperature alloy component reinforced with pre-fabricated superlattice stacking faults within an ordered phase as described in claim 9, characterized in that, The high-temperature alloy components are used as high-temperature load-bearing components in aero-engines, rocket engines, or power plants.

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