Forging method of high-strain-uniformity powder high-temperature alloy turbine disc

Abstract

The forging method for the high-strain-uniformity powder high-temperature alloy turbine disc comprises the following specific steps that S1, a cavity is measured after an isothermal forging die is closed, and area division is conducted; s2, high-temperature alloy powder is prepared through an ultra-high-speed plasma rotating electrode method or an argon atomization method, and an experimental blank is obtained; s3, a pre-forging rough shape A'meeting the size requirement of the turbine disc part to be machined is obtained; s4, high-temperature alloy powder is prepared through an ultra-high-speed plasma rotating electrode method or an argon atomization method, and a hot isostatic pressing blank before forging is obtained; and S5, the obtained hot isostatic pressing blank before forging is machined, a sheath is removed, then isothermal forging is conducted, and the equal-strain turbine disc piece meeting the size requirement is obtained. According to the turbine disc prepared through the method, all parts of the whole disc are uniform in strain, and the range is smaller than 30%.

Description

Technical Field

[0001] The invention belongs to the technical field of high-temperature metal forging, and in particular relates to a forging method for a high-strain uniform powder high-temperature alloy turbine disk. Background Art

[0002] At present, the fundamental factor that restricts engine efficiency and thrust-to-weight ratio is the development level of high-temperature materials. In my country, the forming of conventional powder high-temperature alloy turbine disks usually undergoes a series of processes such as hot isostatic pressing, hot extrusion blanking, and isothermal die forging of extruded cylindrical billets. However, in this process, the material will be introduced into uneven strain many times, resulting in a huge difference in strain in various parts of the forging (the maximum strain difference may even exceed 100%), which will lead to uneven organization and performance, large internal stress, and easy local cracking during quenching. Microcracks may also exist in some areas with excessive local stress, which seriously affects the service life of the disk and the safety performance of the engine. In view of this, in the process of tackling the reliability project of powder disk alloy, it is urgent to design a new turbine disk forming technology, which should be based on isothermal forging isothermal pressing, and achieve equal strain in various parts of the forging during the forging process, to ensure that the strain difference in various parts of the powder high-temperature alloy turbine disk after forging is less than 30%.

[0003] In view of this, the present invention is proposed. Summary of the invention

[0004] The purpose of the present invention is to overcome the shortcomings of the above-mentioned prior art and provide a forging method for a powder high-temperature alloy turbine disk with high strain uniformity, aiming to solve the problem of uneven deformation strain of the powder high-temperature alloy turbine disk.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] The present invention provides a forging method for a high-strain uniform powder high-temperature alloy turbine disk, and the specific steps are as follows:

[0007] S1. Determine the cavity of the isothermal forging die after mold closing, divide the area, and determine a virtual grid A of 1 to 10% of the maximum diameter × 1 to 20% of the maximum height;

[0008] S2. Prepare high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method. The particle size of high-temperature alloy powder is ≤45μm. The powder is loaded into carbon steel or stainless steel sheath by vacuum degassing method. The sheath is pressed by hot isostatic pressing to obtain the hot isostatic pressing test blank required for the design model. The blank size should be φ120~220×120~300mm;

[0009] S3, taking the hot isostatic pressing test blank obtained in step S2 and making cylindrical and biconical specimens according to the virtual grid size divided in step S1, performing isothermal hot compression test on the specimens and combining with finite element simulation software to obtain the pre-forging rough shape A′ of the turbine disk to be processed with the size requirements;

[0010] S4, preparing high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method, the particle size of high-temperature alloy powder is ≤45 μm, processing powder into powder sleeve according to the rough size before forging obtained in step S3, filling the powder into carbon steel or stainless steel sleeve by vacuum degassing method, and forming the sleeve by hot isostatic pressing to obtain hot isostatic pressed blank before forging;

[0011] S5, machining the hot isostatic pressed blank before forging obtained in step S4 to remove the jacket and then isothermally forging to obtain an isostrain turbine disk that meets the size requirements.

[0012] Furthermore, in step S1, the measurement of the cavity after the isothermal forging die is closed, and the regional division includes: regional division of the longitudinal strain component and regional division of the transverse strain component. The specific steps of the regional division of the longitudinal strain component are: measuring the vertical distance from the upper die to the lower die after the isothermal forging die is closed, and the measuring interval is 1 to 10% of the maximum diameter; the specific steps of the regional division of the transverse strain component are: measuring the radial direction distance of the isothermal forging, and the measuring interval is 1 to 20% of the maximum height.

[0013] Furthermore, in step S2, the proportion of high-temperature alloy powder with a particle size of ≤15μm does not exceed 5%, and the proportion of ultrafine powder with a particle size of ≤5μm does not exceed 3%. When the powder is prepared by the ultra-high-speed plasma rotating electrode method, the rotation speed is 25000-32000r / min, and the rod diameter is not greater than 53mm.

[0014] Furthermore, the size of the sample in the isothermal hot compression test in step S3 should not be less than the size of the virtual grid A in step S1, the maximum effective strain inside the sample in the isothermal hot compression test should be less than 1, and the total compression true strain should not be less than 0.69.

[0015] Furthermore, the isothermal hot compression test parameters in step S3 include the temperature and strain rate of each area during the isothermal forging of the disc: wherein, considering the temperature drop during the transfer and forging process, the temperature range should be 1030°C to 1130°C, and considering the different contact time between each position of the forging and the die, the pressing strain rate range should be 0.1 to 0.0001s -1 .

[0016] Furthermore, during the isothermal hot compression experiment in step S3, the changes in the diameter and height of the sample are monitored by an extensometer, and at least the maximum values ​​of the height and diameter changes when the total true strain of the total downward pressure is 0.1, 0.2, 0.3, 0.4, 0.5, and 0.6 are recorded respectively.

[0017] Furthermore, the diameter and height data of the deformed specimen are refilled into the virtual grid A to form a new grid B, and then the deformed specimen is restored to its pre-deformation size. The restored and displaced specimens form a grid C, and the outer contour of the grid C is recorded as grid A.

[0018] Furthermore, in step S3, the rough type A model is imported using finite element simulation software, and the flownet tracking module is used for simulation and iteration, so that the strain of each part of the disk is greater than 0.6 and less than 0.9, and the strain difference of each part is less than 30%. The final rough type A′ before forging can be obtained through multiple iterations.

[0019] Furthermore, in step S4, the powder-filled sheath is processed according to the rough size before forging obtained in step S3, and the sheath needs to be welded, leak-checked, and annealed at 700-1200° C. in a vacuum heat treatment; then the carbon steel sheath is cleaned, powder-filled, degassed, and sealed, and then hot isostatic pressing is performed at 900-1100° C. and 185-205 MPa for 3-10 hours; after the hot isostatic pressing is completed, the sheath is removed by machining for isothermal forging.

[0020] Furthermore, the isothermal hot compression test using a double-conical specimen in step S3 is to consider the influence of the coordinated deformation between adjacent virtual grids A on the metal flow.

[0021] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects:

[0022] (1) The pre-forging rough shape of the blank is formed by powder metallurgy, without other deformation and blanking, and the pre-forging rough shape is directly obtained;

[0023] (2) The turbine disk obtained by the forging method of the present invention has uniform structure: the stress, strain and structure of the blank before forging are uniform, without macro segregation; stable performance: finite element analysis and practice show that the strain difference of each part inside the powder high-temperature alloy turbine disk forging is less than 30%, and the tensile, creep and fatigue properties of each part are stable and highly consistent.

[0024] (3) The forging method provided by the invention has broad application prospects in the fields of powder high-temperature alloy turbine disk manufacturing, etc. It can improve product quality and performance stability, reduce production costs, and improve production efficiency. At the same time, it is of great significance to promote the application of powder metallurgy technology in the field of high-end manufacturing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings are incorporated in and constitute a part of this specification and, together with the description, serve to explain the principles of the present invention.

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0027] Figure 1 This is a microstructure photograph of the rim A in the embodiment of the present invention;

[0028] Figure 2 This is a microstructure photograph of the rim B in the embodiment of the present invention;

[0029] Figure 3 This is a microstructure photo of the hub A in the embodiment of the present invention;

[0030] Figure 4 This is a microstructure photo of the hub B in the embodiment of the present invention;

[0031] Figure 5 This is a microstructure photo of the hub C in the embodiment of the present invention;

[0032] Figure 6 This is a microstructure photograph of the spoke A in the embodiment of the present invention;

[0033] Figure 7 This is a microstructure photograph of the spoke B in the embodiment of the present invention;

[0034] Figure 8 FIG. 4 is a microstructure photograph of the spoke C in the embodiment of the present invention. DETAILED DESCRIPTION

[0035] Here, exemplary embodiments will be described in detail, and examples thereof are shown in the accompanying drawings. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are only examples consistent with some aspects of the present invention as detailed in the appended claims.

[0036] According to an embodiment of the present invention, the present invention provides a forging method of a high-strain uniform powder high-temperature alloy turbine disk, and the specific steps are as follows:

[0037] Step 1: Determine the cavity of the isothermal forging die after mold closing and divide the area. The measured horizontal and vertical lines can be divided into a virtual grid A of 1 to 10% of the maximum diameter × 1 to 20% of the maximum height.

[0038] The regional division includes: regional division of longitudinal strain components and regional division of transverse strain components. The specific steps of regional division of the longitudinal strain components are: measuring the vertical distance from the upper die to the lower die after the isothermal forging die is closed, and the measuring interval is 1 to 10% of the maximum diameter; the specific steps of regional division of the transverse strain components are: measuring the radial direction distance of the isothermal forging, and the measuring interval is 1 to 20% of the maximum height.

[0039] Step 2: Prepare high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method. The particle size of high-temperature alloy powder is ≤45μm. The powder is loaded into a carbon steel or stainless steel sheath by vacuum degassing. The sheath is formed by hot isostatic pressing to obtain the hot isostatic pressing experimental billet used for the designed rough model. The billet size should be φ120~220×120~300mm.

[0040] Among them, the proportion of high-temperature alloy powder with a particle size of ≤15μm does not exceed 5%, and the proportion of ultrafine powder ≤5μm does not exceed 3%. When the ultra-high-speed plasma rotating electrode method is used to prepare the powder, the rotation speed is 25000~32000r / min, and the rod diameter is not more than 53mm.

[0041] Step 3: Take the hot isostatic pressing test blank obtained in step 2 and make cylindrical and biconical specimens according to the virtual grid size divided in step 1. Perform isothermal hot compression test on the specimens and use finite element simulation software to obtain the pre-forging rough shape A′ that meets the dimensional requirements of the turbine disk to be processed.

[0042] For the isothermal hot compression test, the sample size should not be less than the size of the virtual grid A in step 1. In the isothermal hot compression test, the maximum effective strain inside the sample should be less than 1, and the total pressing true strain should be no less than 0.69. The isothermal hot compression test parameters include the temperature and strain rate of each area during the isothermal forging process of the disk: Among them, considering the temperature drop during the transfer and forging process, the temperature range should be 1030℃~1130℃, considering the different contact time between each position of the forging and the die, the pressing strain rate range should be 0.1~0.0001s -1 .

[0043] During the isothermal hot compression test, the changes in the diameter and height of the specimen are monitored by an extensometer, and at least the maximum values ​​of the height and diameter changes when the total true strain of the total downward pressure is 0.1, 0.2, 0.3, 0.4, 0.5, and 0.6 are recorded respectively. Then, the diameter and height data of the deformed specimen are refilled in the virtual grid A to form a new grid B, and then the deformed specimen is restored to the size before deformation. Since the diameter before deformation is small, each layer of the specimen on the outer ring of the forging will be displaced toward the axis. In addition, the gap between the specimens should be filled, and another displacement toward the axis will be generated. This displacement is obtained in the finite element software according to the principle of volume invariance. The above-mentioned restored and displaced specimens form a grid C, and the outer contour of the grid C is recorded as rough type A. Next, the rough type A model is imported using the finite element simulation software, and the flownet tracking module is used for simulation and iteration, so that the strain of each part of the disk is greater than 0.6 and less than 0.9, and the strain difference of each part is less than 30%. The final rough type A′ before forging can be obtained through multiple iterations.

[0044] The isothermal hot compression test using a double-cone specimen is to consider the influence of the coordinated deformation between adjacent virtual grids A on the metal flow. The maximum diameter of the double-cone specimen should not be less than "1-10% of the maximum diameter" as described in step 2, and the cone height should not be less than "1-20% of the maximum height" as described in step 2. The changes in diameter and height are detected during the experiment, which is the same as the record of the cylindrical specimen.

[0045] Step 4: Prepare high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method. The particle size of high-temperature alloy powder is ≤45μm. Process the powder into powder sleeve according to the rough size before forging obtained in step 3. The powder is loaded into carbon steel or stainless steel sleeve by vacuum degassing. The sleeve is formed by hot isostatic pressing to obtain hot isostatic pressed blank before forging.

[0046] It should be noted that before forging, the powder-filled sheath for rough-size processing needs to be welded, leak-checked, and annealed at 700-1200℃ vacuum heat treatment; then the carbon steel sheath is cleaned, powder-filled, degassed, and sealed, and then hot isostatic pressing is performed at 900-1100℃ and 185-205MPa for 3-10 hours; after the hot isostatic pressing is completed, the sheath is removed by machining for isothermal forging.

[0047] Step 5: The hot isostatic pressed blank obtained in step 4 is machined to remove the jacket and then isothermally forged to obtain an isostrain turbine disk that meets the size requirements.

[0048] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0049] Example 1

[0050] Step 1: According to the measurement of the cavity after the isothermal forging die is closed, the maximum height is 150mm, the maximum diameter is 569mm, the height measurement interval is 7.5mm, and the diameter measurement interval is 5.69mm. The virtual grid is divided according to this Φ5.69×7.5mm size to form grid A.

[0051] Step 2: Prepare FGH4096 high temperature alloy powder by argon atomization method, the powder particle size is 15-45 μm, and the fine powder ≤15 μm accounts for 2%.

[0052] Step 3: Take the hot isostatically pressed blank, process it into a cylindrical specimen with a size of Φ5.69×7.5mm, and perform a constant rate compression test on an isothermal compression testing machine. The compression temperatures are 1030℃, 1040℃, 1050℃, 1055℃, 1060℃, and 1065℃, the pressing amount is 50%, and the pressing strain rates are 0.1, 0.03, 0.01, 0.007, 0.009, and 0.0001s. -1 The maximum values ​​of height and diameter changes when the total compressive true strain is 0.1, 0.2, 0.3, 0.4, 0.5, and 0.6 are recorded respectively.

[0053] The hot isostatically pressed blank was used to produce a double-conical specimen with the size of Φ5.69(8)×7.5mm, and the experimental parameter values ​​were the same as those of the cylindrical specimen.

[0054] The diameter change and height data of the deformed specimen obtained above are redrawn and filled in grid A to form a new grid B. All grid sizes in grid B are selected according to the strain amount at each position of the disk, and lateral deformation needs to be considered. The size state before deformation in all grids B is restored to obtain grid C, and the outer contour of grid C is recorded as rough type A. Next, the rough type A model is imported using finite element simulation software, and the flow net tracking module is used for simulation and iteration, so that the strain of each part of the disk is greater than 0.6 and less than 0.9, and the strain difference of each part is less than 30%, and finally rough type A′ is obtained.

[0055] Step 4: Process the carbon steel sheath according to the rough A′ size designed in step 3, seal the sheath, check for leaks, and anneal the sheath at 700°C vacuum heat treatment; clean, degas, fill with powder, seal the carbon steel sheath, and then perform hot isostatic pressing at 900°C and 185MPa for 5 hours.

[0056] Step 5: After the hot isostatic pressing is completed, the jacket is removed by machining and isothermal forging is performed to obtain the turbine disk.

[0057] The machined turbine disk was dissected to observe the strain of each part, and the real equivalent strain of each position was determined by measuring the curvature of the compressed original grain boundary. The strain of each position of the disk is shown in Table 1. The control group in Table 2 is also given, which is the equivalent strain of each position after forging using only cylindrical rough forging.

[0058] Table 1 Strain values ​​and room temperature tensile properties of different parts of the disc after forging in Example 1

[0059]

[0060]

[0061] Table 2 Strain values ​​and room temperature tensile properties of cylindrical rough forging discs at different positions

[0062]

[0063] From the above, we can see that reference Figure 1-8 Microstructure photos of various parts inside the turbine disk show that the strain difference of various parts inside the turbine disk obtained by the forging method of the present invention is less than 30%, the extreme difference is only 23%, and the tensile, creep and fatigue properties of various parts are stable and highly consistent.

[0064] Example 2

[0065] Step 1: According to the measurement of the cavity after the isothermal forging die is closed, the maximum height is 146mm and the maximum diameter is 513mm. The height measurement interval is 12mm and the diameter measurement interval is 10.3mm. The virtual grid is divided according to the size of Φ10.3×12mm to form grid A.

[0066] Step 2: FGH4097 high-temperature alloy powder is prepared by ultra-high-speed plasma rotating electrode method. The powder particle size is 15-45 μm, fine powder ≤15 μm accounts for 1%, the rod speed is 29000 r / min, and the rod diameter is 50 mm.

[0067] Step 3: Take the hot isostatically pressed blank, process it into a cylindrical specimen with a size of Φ10.3×12mm, and perform a constant rate compression test on an isothermal compression testing machine. The compression temperatures are 1080℃, 1090℃, 1095℃, 1110℃, 1115℃, and 1130℃, the compression amount is 45%, and the compression strain rates are 0.1, 0.03, 0.01, 0.007, 0.009, and 0.0001s -1 The maximum values ​​of height and diameter changes when the total compressive true strain is 0.1, 0.2, 0.3, 0.4, 0.5, and 0.6 are recorded respectively.

[0068] The hot isostatically pressed blank was taken and the processing size was Φ10.3×12mm double-cone specimen, which had the same experimental parameter values ​​as the cylindrical specimen.

[0069] According to the diameter and height data of the deformed specimen obtained above, redraw and fill the grid A to form a new grid B. All grid sizes in grid B are selected according to the strain at each position of the disk, and lateral deformation needs to be considered. Restore the size state before deformation in all grids B to obtain grid C. The outer contour of grid C is recorded as rough type A. Next, the rough type A model is imported using finite element simulation software, and the flow net tracking module is used for simulation and iteration, so that the strain of each part of the disk is greater than 0.6 and less than 0.9, and the strain difference of each part is less than 30%. Finally, rough type A′ can be obtained.

[0070] Step 4: Process the carbon steel sheath according to the rough A′ size designed in step 3, seal the sheath, check for leaks, and anneal the sheath at 1200°C vacuum heat treatment; clean, degas, fill with powder, seal the carbon steel sheath, and then perform hot isostatic pressing at 1100°C and 230MPa for 5 hours.

[0071] Step 5: After the hot isostatic pressing is completed, the jacket is removed by machining and isothermal forging is performed to obtain the turbine disk.

[0072] The machined turbine disk was dissected to observe the strain of each part, and the real equivalent strain of each position was determined by measuring the curvature of the compressed original grain boundary. The strain of each position of the disk is shown in Table 3. At the same time, the control group in Table 4 is given, which is the equivalent strain of each position after forging using only cylindrical rough forging.

[0073] Table 3 Strain values ​​and room temperature tensile properties of different parts of the disc after forging in Example 2

[0074]

[0075] Table 4 Strain values ​​and room temperature tensile properties of cylindrical rough forging discs at different positions

[0076]

[0077]

[0078] From the above, we can see that reference Figure 1-8 Microstructure photos of various parts inside the turbine disk show that the strain difference of various parts inside the turbine disk obtained by the forging method of the present invention is less than 30%, the extreme difference is only 28%, and the tensile, creep and fatigue properties of various parts are stable and highly consistent.

[0079] The high-strain uniformity powder high-temperature alloy turbine disk forging method provided by the present invention can greatly improve the uniformity of the organization and performance of the powder high-temperature alloy turbine disk forgings, reduce the abnormal grain growth caused by the deformation dead zone, and improve the material utilization rate. The turbine disk prepared by the method of the present invention is characterized in that the strain of all parts of the entire disk is uniform, and the extreme difference is less than 30%. This method can make the stress distribution inside the powder high-temperature alloy disk uniform and the mechanical properties uniform. The present invention is not only suitable for the forming of powder high-temperature alloys and high-temperature alloy disks, but can even be extended to forging, rolling and extrusion workpieces of other shapes and sizes such as powder steel and powder titanium alloy. Therefore, all the ideas of the present invention can be used to make any adjustments, improvements, and replacements of powder alloys; all the technologies that can use the ideas of the present invention to forge or extrude near-net forming should still be within the scope of protection of the present invention.

[0080] The above description is only a specific embodiment of the present invention, so that those skilled in the art can understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention.

[0081] It should be understood that the present invention is not limited to what has been described above and that various modifications and changes may be made without departing from its scope. The scope of the present invention is limited only by the appended claims.

Claims

1. A forging method for a high-strain uniform powder high-temperature alloy turbine disk, characterized in that: The specific steps are as follows: S1. Determine the cavity of the isothermal forging die after mold closing, divide the area, and determine a virtual grid A of 1 to 10% of the maximum diameter × 1 to 20% of the maximum height; S2. Prepare high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method. The particle size of high-temperature alloy powder is ≤45μm. The powder is loaded into carbon steel or stainless steel sheath by vacuum degassing method. The sheath is pressed by hot isostatic pressing to obtain the hot isostatic pressing test blank required for the design model. The blank size should be φ120~220×120~300mm; S3, taking the hot isostatic pressing test blank obtained in step S2 and making cylindrical and biconical specimens according to the virtual grid size divided in step S1, performing isothermal hot compression test on the specimens and combining with finite element simulation software to obtain the pre-forging rough shape A′ of the turbine disk to be processed with the size requirements; S4, preparing high-temperature alloy powder by ultra-high-speed plasma rotating electrode method or argon atomization method, the particle size of high-temperature alloy powder is ≤45 μm, processing powder into powder sleeve according to the rough size before forging obtained in step S3, filling the powder into carbon steel or stainless steel sleeve by vacuum degassing method, and forming the sleeve by hot isostatic pressing to obtain hot isostatic pressed blank before forging; S5, machining the hot isostatic pressed blank before forging obtained in step S4 to remove the jacket and then isothermally forging to obtain an isostrain turbine disk that meets the size requirements.

2. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: In step S1, the measurement of the cavity after the isothermal forging die is closed includes: regional division of the longitudinal strain component and regional division of the transverse strain component. The specific steps of regional division of the longitudinal strain component are: measuring the vertical distance from the upper die to the lower die after the isothermal forging die is closed, and the measurement interval is 1 to 10% of the maximum diameter; The specific steps of regional division of the transverse strain component are: measuring the radial distance of the isothermal forging, and the measuring interval is 1 to 20% of the maximum height.

3. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: In step S2, the proportion of high-temperature alloy powder with a particle size of ≤15 μm does not exceed 5%, and the proportion of ultrafine powder with a particle size of ≤5 μm does not exceed 3%. When the ultra-high-speed plasma rotating electrode method is used to prepare powder, the rotation speed is 25000-32000 r / min, and the rod diameter is not greater than 53 mm.

4. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: The size of the isothermal compression test specimen in step S3 should not be less than the size of the virtual grid A in step S1. In the isothermal hot compression test, the maximum effective strain inside the specimen should be less than 1, and the total compression true strain should not be less than 0.

69.

5. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: The isothermal hot compression test parameters in step S3 include the temperature and strain rate of each area during the isothermal forging process of the disc: considering the temperature drop during the transfer and forging process, the temperature range should be 1030℃~1130℃, considering the different contact time between each position of the forging and the die, the pressing strain rate range should be 0.1~0.0001s -1 .

6. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: During the isothermal hot compression test in step S3, the changes in the diameter and height of the sample are monitored by an extensometer, and at least the maximum values ​​of the height and diameter changes when the total true strain is 0.1, 0.2, 0.3, 0.4, 0.5, and 0.6 are recorded respectively.

7. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 6, characterized in that: The diameter and height data of the deformed specimen are refilled into the virtual grid A to form a new grid B. The deformed specimen is then restored to its pre-deformation size. The restored and displaced specimens form grid C, and the outer contour of grid C is recorded as grid A.

8. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 7, characterized in that: In step S3, the rough shape A model is imported using finite element simulation software, and the flownet tracking module is used for simulation and iteration, so that the strain of each part of the disk is greater than 0.6 and less than 0.9, and the strain difference of each part is less than 30%. The final rough shape A′ before forging can be obtained through multiple iterations.

9. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: In step S4, the powder-filled sheath is processed according to the rough size before forging obtained in step S3, and the sheath needs to be welded, leak-checked, and annealed in a vacuum heat treatment at 700-1200° C.; then the carbon steel sheath is cleaned, powder-filled, degassed, and sealed, and then hot isostatic pressing is performed at 900-1100° C. and 185-205 MPa for 3-10 hours; after the hot isostatic pressing is completed, the sheath is removed by machining for isothermal forging.

10. The forging method of high-strain uniform powder high-temperature alloy turbine disk according to claim 1, characterized in that: The isothermal hot compression test using a double-conical specimen in step S3 is to consider the influence of the coordinated deformation between adjacent virtual grids A on the metal flow.

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