In-situ rapid fabrication method of high-organization-uniform nickel-based alloy turbine disc

Abstract

This invention provides an in-situ rapid preparation method for a nickel-based alloy turbine disk with high microstructure and uniformity, relating to the field of nickel-based superalloy technology. The method includes the following steps: modeling the nickel-based alloy turbine disk using 3D digital software to form a turbine disk model, and simultaneously reverse-engineering the mold shape of the turbine disk; slicing the turbine disk model, forming a complete printing path in a laser additive manufacturing device, and performing 3D printing on the mold; after printing, moving the mold as a whole to a vacuum isothermal forming device for vacuum isothermal forging, and automatically demolding to obtain a precision forged turbine disk; heat-treating and machining the forging to obtain the nickel-based alloy turbine disk. This invention combines the advantages of precise 3D printing and vacuum isothermal precision forming, solving the problems of solidification defects and microstructure in printed parts, achieving in-situ precision forming, enabling automated and standardized processes, improving product production efficiency, yield, and material utilization, and possessing significant commercial value.

Description

Technical Field

[0001] This invention relates to the field of nickel-based superalloy technology, and in particular to an in-situ rapid preparation method for a nickel-based alloy turbine disk with high microstructure and uniformity. Background Technology

[0002] Aerospace engines are hailed as the "crown jewel of industry," representing a nation's comprehensive industrial technological strength. Engines are the primary power source for aerospace and a major determinant of aircraft capabilities. Nickel-based alloys are typical materials used in hot-end components, which account for 40-60% of aero-engine components. Nickel-based alloy turbine disks are a prime example of hot-end components, operating in harsh environments (high temperature and high stress), with stringent performance requirements, complex manufacturing processes, and low yield rates.

[0003] Currently, the manufacturing processes for turbine disks in industrial production generally fall into two categories: 1) For wrought alloys, after casting, the disks are repeatedly upsetting and drawn into suitable billets, then subjected to appropriate die forging and machining before shipment; 2) For powder metallurgy alloys, billets are formed after hot isostatic pressing, then extruded into bars, followed by appropriate die forging and machining. The disadvantages of these manufacturing processes are: both methods involve lengthy processes, numerous specialized equipment, and a high degree of reliance on experience in selecting process parameters, resulting in low billet yield, low utilization of die forging raw materials, low finished product yield, and difficulty in controlling microstructure uniformity.

[0004] To address the current issues, the industry is continuously controlling and improving the forming process. Among them, Chinese patent "CN117798293A, A forging process and turbine disk component for GH4065A alloy low-pressure turbine disk" proposes a process path of upsetting-punching-ring rolling-hot die forging for the preparation of GH4065A alloy low-pressure turbine disks. Chinese patent "CN114160747A, A forging method for fine-grained disk components made of GH4169" proposes a method of upsetting bar stock-soft-sleeve forging (using a special mold)-machining to manufacture fine-grained turbine disks of GH4169 alloy. Chinese patent "CN119346792A, A forging method for a high strain uniformity powder superalloy turbine disk" proposes to form a powder superalloy turbine disk by powder preparation-hot isostatic pressing-isothermal forging; Chinese patent "CN105436373A, A method for superplastic isothermal closed-circuit upsetting of nickel-based powder superalloy ingots" proposes to use closed-circuit forging for nickel-based powder superalloy ingots.

[0005] The methods described above can all be used to process nickel-based alloy discs. Among these, forging with a sheath or isothermal forging remains a crucial step in billet preparation and part machining. This places high demands on material microstructure control and yield control, while also making it difficult to significantly improve material utilization. With the continuous development of technology and the maturity of 3D printing, many researchers have begun using this advanced technology to manufacture hot-end components, such as turbine discs, turbine blades, and casings. However, 3D printing technology has exposed a key problem: the phenomenon of density and mechanical property delamination after printing, i.e., the anisotropy of mechanical properties in the material.

[0006] To address the problems existing in the prior art, this invention proposes an in-situ rapid preparation method for highly uniform nickel-based alloy turbine disks. Through in-situ printing, forging, and machining, highly uniform nickel-based alloy turbine disks are successfully prepared. This method improves yield, saves materials, and increases work efficiency. Summary of the Invention

[0007] To overcome the shortcomings of existing technologies, this invention provides an in-situ rapid preparation method for high-uniformity nickel-based alloy turbine disks. Precision printing is used to pre-fabricate billets, achieving precise billet preparation and grain size control. After in-situ transfer and multiple vacuum isothermal forging micro-deformation, the billets undergo standard heat treatment and simple machining to become the product available for delivery.

[0008] To achieve the above objectives, the technical solution of the present invention is as follows:

[0009] This invention provides an in-situ rapid preparation method for a nickel-based alloy turbine disk with highly uniform microstructure, comprising the following steps:

[0010] Step 1: Model the nickel-based alloy turbine disk using 3D digital software to form a turbine disk model, and simultaneously reverse-engineer the shape of the turbine disk mold.

[0011] Step 2: Slice the turbine disk model obtained in Step 1, form a complete printing path in the laser additive manufacturing equipment, and 3D print it on the mold manufactured according to the configuration in Step 1.

[0012] Step 3: After 3D printing is completed, the mold is moved to the vacuum isothermal forming device for vacuum isothermal forging. After automatic demolding, the turbine disk precision forging is obtained.

[0013] Step 4: Perform heat treatment and machining on the turbine disk precision forging obtained in Step 3 to obtain the nickel-based alloy turbine disk.

[0014] Preferably, in step one, the three-dimensional digitization software is selected from at least one of UG, Solidworks, Pro / E, and Deform, and the nickel-based alloy turbine disk has a height margin of 1-5%. The height margin is prepared for subsequent deformation. Plastic forming is a type of equal-volume deformation, and providing a height margin is beneficial for subsequent forming and machining.

[0015] Preferably, in step two, the mold material is hard high-temperature graphite, TZM alloy, high-entropy alloy, or ceramic. The mold includes an upper mold and a lower mold. The upper mold is driven by a forging machine, and the lower mold serves as the printing substrate, which can be transferred in situ in step three. A thin sheet of the same material as the mold, with a thickness of 1-5 mm, is provided between the bottom of the lower mold and the printed part. Before 3D printing, a boron nitride lubricating release agent is coated on the surface of the mold and the surface of the thin sheet.

[0016] Preferably, in step two, the nickel-based alloy used for 3D printing is selected from one of wrought superalloys, cast superalloys, and powder superalloys. Nickel-based alloys or nickel-based superalloys refer to a class of superalloys that include wrought, cast, powder, and directional solidification types. Except for directional solidification alloys, which cannot be prepared using this method, other types of alloys are suitable for this preparation method.

[0017] Preferably, the nickel-based alloy is in powder form, with a powder particle size distribution of d≤50μm, 50-100μm, and 100-150μm, and a mixed powder volume ratio of (1-3):(4-6):(1-3). Excessive fine powder can easily lead to agglomeration and powder blowing during printing, but this reduces the grain size of the printed parts and improves the compactness of the blank. Conversely, excessive coarse powder makes it difficult to melt during printing, resulting in larger and less uniform grains in the printed parts, increasing porosity. Using this powder mixing method can significantly improve the compactness of the parts during printing. Furthermore, the appropriate mixing of powders with different particle sizes can improve the overall printing quality, reduce the adhesion of pure fine powder and the presence of unmelted material in pure coarse powder, and allow for control of the alloy grain size during blank preparation.

[0018] Preferably, in step two, the 3D printed turbine disk adopts a circular printing path, printing a turbine disk blank within the lower mold area. The heating temperature of the lower mold is 300~700℃. The printing process parameters are: laser power 800~1200W, scanning speed 7~21mm / s, and powder feed rate 8.5~17.5g / min. Research has found that when the proportion of coarse powder is large, the overall powder flowability is very good, and the powder feed rate can be appropriately increased. However, increasing the laser power and decreasing the scanning speed are necessary to ensure complete powder melting. When the proportion of fine powder is large, the flowability decreases, and the powder feed rate can be appropriately reduced. In this case, the laser power can be reduced, and the scanning speed can be appropriately increased.

[0019] Preferably, in step three, after the 3D printing of the turbine disk is completed, it is not necessary to wait for it to cool down. It is directly transferred in situ, along with the mold, to the vacuum isothermal forging station for vacuum isothermal forging. Rapid transfer after printing minimizes equipment energy consumption and reduces the risk of cracking caused by rapid temperature drops in the printed part. Preferably, the mold transfer time is ≤60s, the forging temperature is 980~1200℃, and the forging rate is ≤0.15s. -1 The number of deformation cycles is 1 ≤ N ≤ 5, the deformation amount decreases with each deformation, the single deformation amount is 1~5%, the cumulative deformation amount is ≤15%, and the hot vacuum degree is ≤8×10. -3 Pa. This invention improves density and reduces porosity by controlling the amount and number of deformations per cycle, while also preventing deformation flow lines and microstructure inhomogeneity caused by large single deformations during forging. The cumulative deformation is limited to within 15% because this value is the critical deformation amount for recrystallization of this type of metal alloy; experiments have shown that within this range, grain size can be precisely controlled through micro-deformation.

[0020] Preferably, in step four, after forming, a standard heat treatment method (refer to the Chinese High Temperature Alloy Handbook) is used for processing. Milling is performed using a five-axis machine tool, with an average removal depth ≤1mm and an overall material utilization rate ≥97%. Currently, the material utilization rate of 3D printing technology in the industry is approximately 95%, and that of forging technology is approximately 90%. Therefore, this invention can significantly improve the material utilization rate of nickel-based alloy turbine disks prepared using 3D printing technology.

[0021] Preferably, steps one to four above can be repeated to achieve automated continuous production.

[0022] The present invention also provides different types of nickel-based alloy turbine disks prepared by the method, with a density of approximately 99.5-99.9%, tensile strength increased by 5-20%, elongation increased by 10-50%, and grain size difference along the diameter direction of the turbine disk ≤ ±1 grade.

[0023] The present invention has the following beneficial effects:

[0024] (1) This invention targets nickel-based high-temperature alloys and achieves in-situ, short-process, high-performance precision fabrication of nickel-based alloy turbine disks by integrating advanced printing technology with vacuum isothermal forging micro-deformation technology in a spatiotemporal orderly manner. It breaks through the technical difficulties of precision billet preparation of nickel-based alloy raw materials, realizes the preparation of high-quality billets with fine and uniform grains, lays a solid raw material foundation for subsequent multiple micro-deformations, saves materials, and improves work efficiency.

[0025] (2) The present invention adopts a combination of three-dimensional digital blank design and reverse engineering mold design to further improve the accuracy of preparation, ensure micro deformation, and realize the control of turbine disk forming accuracy and the improvement of raw material utilization.

[0026] (3) The present invention utilizes a vacuum isothermal forging equipment to perform in-situ multiple micro-deformations on the printed blank, successfully avoiding void defects in the printed blank. The combination of vacuum isothermal forging process parameters and multiple deformations further utilizes the recrystallization process to achieve control over grain size and uniformity, realizing a radial dimension grain size difference of ≤±1 grade for the turbine disk.

[0027] (4) The existing processes for preparing nickel-based superalloys are all billet preparation, die forging, heat treatment, and machining. The billet preparation process is cumbersome, and the die forging process involves multiple upsetting and drawing processes. Compared with the existing technology, the present invention uses the same mold platform for both printing billet preparation and vacuum isothermal forging, realizing the integration of billet preparation and die forging. It achieves in-situ operation as much as possible, which is conducive to improving forming accuracy, shortening the preparation cycle, and reducing material waste. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 The following are three-dimensional model drawings of the turbine disk, including (a) a schematic diagram of the parting surface of the turbine disk; (b) a three-dimensional schematic diagram of the turbine disk; (c) a schematic diagram of the upper mold for vacuum isothermal forging; and (d) a schematic diagram of the lower mold for vacuum isothermal forging.

[0030] Figure 2 The images show the microstructure of the turbine disk prepared in Example 1 at different locations, where (a) is the microstructure of the disk edge and (b) is the microstructure of the disk center. Detailed Implementation

[0031] To make the technical problems, technical solutions and advantages of the present invention clearer, a detailed description will be given below in conjunction with the accompanying drawings and specific embodiments.

[0032] Example 1

[0033] Step 1: Model the turbine disk component using the 3D digitization software Solidworks to create a turbine disk model with a size of 400mm. Simultaneously, reverse engineer the turbine disk mold shape. The mold material is TZM molybdenum alloy; the mold includes an upper mold and a lower mold. A thin metal sheet, made of the same material as the mold and approximately 1mm thick, is left between the bottom of the lower mold and the printed part. Before operation, apply boron nitride lubricant and release agent to the surfaces of the mold and the thin metal sheet.

[0034] Figure 1 The figures are three-dimensional modeling diagrams of the turbine disk, where (a) is a schematic diagram of the parting surface of the turbine disk; (b) is a three-dimensional schematic diagram of the turbine disk; (c) is a schematic diagram of the upper mold for vacuum isothermal forging; and (d) is a schematic diagram of the lower mold for vacuum isothermal forging.

[0035] Step 2: Slice the turbine disk model obtained in Step 1, form a complete circular printing path in the laser additive manufacturing equipment, and perform 3D printing on the mold manufactured in Step 1. The nickel-based alloy powder material is FGH96, with a powder particle size d≤50μm, 50-100μm, and 100-150μm mixed in a ratio of 2:6:2; the lower mold preheating temperature is 400℃, and the printing parameters are: laser power 990W, scanning speed 20mm / s, and powder feed rate 9g / min.

[0036] Step 3: After printing, immediately transfer the die to the vacuum isothermal forging station for vacuum isothermal forging. The die transfer time is 20 seconds, the forging temperature is 1100℃, and the forging rate is 0.1 seconds. -1 The deformation cycle N=2, with the deformation amount decreasing each time. The single deformation amounts are 3% and 2% respectively, and the cumulative deformation amount is ≤5%. The hot vacuum degree is 6×10. -3 Pa.

[0037] Step 4: After forming, the part is subjected to standard heat treatment (refer to the Chinese High Temperature Alloy Handbook: (1140~1170)℃×(2~4)h / OQ+(740~770)℃×(10~20)h / AC) and milled using a five-axis machine tool. The average removal depth is approximately 0.7mm, and the material utilization rate is approximately 98%. The grain size difference in the diameter direction of the part is grade 1.

[0038] Figure 2 The images show the microstructure of the turbine disk prepared in Example 1 at different locations, where (a) is the microstructure of the disk edge and (b) is the microstructure of the disk center. It can be seen that in the same turbine disk, the grain size at the disk edge and the disk center is basically the same, around 40 µm. This indicates that using the method provided by this invention, the grain size in different regions of the turbine disk is essentially the same, achieving control over grain size and uniformity.

[0039] Example 2

[0040] Step 1: Model the turbine disk using the 3D digital software UG to create a turbine disk model with a size of 420mm. Simultaneously, reverse engineer the turbine disk mold shape. The mold material is a high-entropy alloy; the mold includes an upper mold and a lower mold. A thin metal sheet, made of the same material as the mold and approximately 2mm thick, is left between the bottom of the lower mold and the printed part. Before operation, apply boron nitride lubricant and release agent to the surfaces of the mold and the thin metal sheet.

[0041] Step 2: Slice the turbine disk model obtained in Step 1, form a complete circular printing path in the laser additive manufacturing equipment, and perform 3D printing on the mold manufactured in Step 1. The nickel-based alloy powder material is GH4169, with a powder particle size d≤50μm, 50-100μm, and 100-150μm mixed in a ratio of 3:6:1; the lower mold preheating temperature is 300℃, and the printing parameters are: laser power 1100W, scanning speed 11mm / s, and powder feed rate 9g / min.

[0042] Step 3: After printing, immediately transfer the die to the vacuum isothermal forging station for vacuum isothermal forging. The die transfer time is 20 seconds, the forging temperature is 1100℃, and the forging rate is 0.1 seconds. -1 The deformation cycle N=2, with the deformation amount decreasing each time. The single deformation amounts are 3% and 2% respectively, and the cumulative deformation amount is ≤5%. The hot vacuum degree is 6×10. -3 Pa.

[0043] Step 4: After forming, the part is subjected to standard heat treatment (refer to the Chinese High Temperature Alloy Handbook: (950~980)℃±10℃×1h / OQ+(710~730)℃×8h / FC→(610~630)℃×8h / AC). Milling is performed using a five-axis machine tool, with an average removal depth of approximately 1mm and a material utilization rate of approximately 97%. The grain size difference in the diameter direction of the part is grade 0.5.

[0044] Example 3

[0045] Step 1: Model the turbine disk component using the 3D digital software Solidworks to create a turbine disk model with a size of 350mm. Simultaneously, reverse engineer the turbine disk mold shape. The mold material is TZM molybdenum alloy. The mold includes an upper mold and a lower mold. A thin metal sheet, made of the same material as the mold and approximately 5mm thick, is left between the bottom of the lower mold and the printed part. Before operation, a boron nitride lubricant and release agent is applied to the surfaces of the mold and the metal sheet.

[0046] Step 2: Slice the turbine disk model obtained in Step 1, form a complete circular printing path in the laser additive manufacturing equipment, and perform 3D printing on the mold manufactured in Step 1. The nickel-based alloy powder material is FGH97, with a powder particle size d≤50μm, 50-100μm, and 100-100μm mixed in a ratio of 3:4:3; the lower mold preheating temperature is 600℃, and the printing parameters are: laser power 1200W, scanning speed 15mm / s, and powder feed rate 9g / min.

[0047] Step 3: After printing, immediately transfer the die to the vacuum isothermal forging station for vacuum isothermal forging. The die transfer time is 30 seconds, the forging temperature is 1070℃, and the forging rate is 0.07 seconds. -1 The deformation cycle N=3, with the deformation amount decreasing each time. The single deformation amounts are 3%, 3%, and 1% respectively, and the cumulative deformation amount is ≤7%. The hot vacuum degree is 8×10⁻⁶. -3 Pa.

[0048] Step 4: After forming, the part is subjected to standard heat treatment (refer to the Chinese High Temperature Alloy Handbook: (1190~1210)℃×8h / FC→(1150~1170)℃ / AC+(800~900)×(25~40)h / AC). Milling is performed using a five-axis machine tool, with an average removal depth of approximately 1mm and a material utilization rate of approximately 97%. The grain size difference in the diameter direction of the part is grade 1.

[0049] Comparative Example 1

[0050] Step 1: Same as Example 1.

[0051] Step 2: Slice the turbine disk model obtained in Step 1, form a complete circular printing path in the laser additive manufacturing equipment, and 3D print it on the mold manufactured in Step 1. The nickel-based alloy powder material is FGH96, with a random particle size distribution of 50-150μm; the lower mold preheating temperature is 600℃, and the printing parameters are: laser power 1200W, scanning speed 15mm / s, and powder feed rate 9g / min.

[0052] Step 3: Same as Example 1.

[0053] Step 4: After forming, the material is treated with standard heat treatment and milled using a five-axis machine tool. The average cutting depth is about 2mm, and the material utilization rate is about 94%.

[0054] Comparative Example 2

[0055] Step 1: Same as Example 1.

[0056] Step 2: Slice the turbine disk model obtained in Step 1, form a complete circular printing path in the laser additive manufacturing equipment, and perform 3D printing on the mold manufactured in Step 1. The nickel-based alloy powder material is FGH96, with a powder particle size d≤50μm, 50-100μm, and 100-150μm mixed in a ratio of 3:2:5; the lower mold preheating temperature is 600℃, and the printing parameters are: laser power 1200W, scanning speed 15mm / s, and powder feed rate 9g / min.

[0057] Step 3: Same as Example 1.

[0058] Step 4: After forming, the material is treated with standard heat treatment and milled using a five-axis machine tool. The average cutting depth is about 2mm, and the material utilization rate is about 95%.

[0059] Comparative Example 3

[0060] Steps one and two: Same as in Example 1.

[0061] Step 3: After printing, immediately transfer the die to the vacuum isothermal forging station for vacuum isothermal forging. The die transfer time is 20 seconds, the forging temperature is 1100℃, and the forging rate is 0.1 seconds. -1 The deformation cycle N=2, with the deformation amount decreasing each time. The single deformation amounts are 7% and 3% respectively, and the cumulative deformation amount is ≤10%. The hot vacuum degree is 6×10. -3 Pa.

[0062] Step 4: After forming, the material is treated with standard heat treatment and milled using a five-axis machine tool. The average cutting depth is about 2mm, and the material utilization rate is about 95%.

[0063] Comparative Example 4

[0064] Steps one and two: Same as in Example 1.

[0065] Step 3: After printing, immediately transfer the die to the vacuum isothermal forging station for vacuum isothermal forging. The die transfer time is 20 seconds, the forging temperature is 1100℃, and the forging rate is 0.1 seconds. -1 The deformation process has N=11 cycles, with the deformation amount decreasing with each cycle. The individual deformation amounts are 5%, 4.5%, 4%, 3.5%, 3%, 2%, 2.5%, 1%, 1.5%, 1%, and 0.5%, respectively. The cumulative deformation amount is >20%, and the hot vacuum degree is 6×10⁻⁶. -3 Pa.

[0066] Step 4: After forming, due to the large cumulative deformation, the shape of the disc has lost the shape designed in Step 1 and cannot be formed into a part. After standard heat treatment, its radial grain size difference is approximately 2-3 levels.

[0067] The performance test results of the above embodiments and comparative examples are shown in Table 1.

[0068] Table 1

[0069]

[0070] Table 1 shows that the nickel-based alloy turbine disk prepared by the method of the present invention has a density of 99.5-99.9%, a tensile strength increase of 5-20%, an elongation increase of 10-50%, and a grain size difference of ≤±1 grade along the diameter direction of the turbine disk.

[0071] Comparative Example 1 did not classify the particle size of the nickel-based alloy powder, nor did it mix powders of different particle sizes in proportion, resulting in a grain size difference of about 2.5 grades along the diameter direction of the turbine disk, and its mechanical properties and material utilization rate were low.

[0072] Comparative Example 2 performed preliminary particle size classification on the nickel-based alloy powder, resulting in better overall turbine disk performance than Comparative Example 1. However, the particle size classification method differed from the example, with excessive addition of coarser-sized powder, leading to a grain size difference of approximately 1.5 grades in the diameter direction of the turbine disk, and consequently, lower mechanical properties and material utilization.

[0073] Comparative Example 3 was not deformed according to the specified single deformation amount, resulting in a grain size difference of about 1.5 grade along the diameter direction of the turbine disk, poor microstructure uniformity, and low mechanical properties.

[0074] Comparative Example 4 was not deformed according to the specified cumulative deformation amount, resulting in the inability to form a turbine disk. At the same time, the grain size difference in the diameter direction was about 2.5-3 grades, the microstructure was poorly uniform, and the mechanical properties of the disk edge and disk center were low.

[0075] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for in-situ rapid fabrication of a high-uniformity nickel-based alloy turbine disk, characterized in that, Includes the following steps: Step 1: Model the nickel-based alloy turbine disk using 3D digital software to form a turbine disk model, and simultaneously reverse-engineer the shape of the turbine disk mold. Step 2: Slice the turbine disk model obtained in Step 1, form a complete printing path in the laser additive manufacturing equipment, and 3D print it on the mold manufactured according to the configuration in Step 1. Step 3: After 3D printing is completed, the mold is moved to the vacuum isothermal forming device for vacuum isothermal forging. After automatic demolding, the turbine disk precision forging is obtained. Step 4: Perform heat treatment and machining on the turbine disk precision forging obtained in Step 3 to obtain the nickel-based alloy turbine disk.

2. The in-situ rapid preparation method of the high-uniformity nickel-based alloy turbine disk according to claim 1, characterized in that, In step one, the three-dimensional digitization software is selected from at least one of UG, Solidwork, Pro / E, and Deform, and the nickel-based alloy turbine disk has a margin of 1-5% in the height direction.

3. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 1, characterized in that, In step two, the mold is made of hard high-temperature graphite, TZM alloy, high-entropy alloy, or ceramic. And / or, the mold includes an upper mold and a lower mold, the upper mold being driven by a forging machine, and the lower mold serving as the printing substrate; And / or, a thin sheet of the same material as the mold is provided between the bottom of the lower mold and the printed part, with a thickness of 1-5mm.

4. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 1, characterized in that, In step two, the nickel-based alloy used for 3D printing is selected from one of the following: wrought superalloys, cast superalloys, and powder superalloys.

5. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 4, characterized in that, The nickel-based alloy is in the form of powder, and the volume ratio of the mixed powder with a particle size distribution of d≤50μm, 50-100μm, and 100-150μm is (1-3):(4-6):(1-3).

6. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 3, characterized in that, In step two, the 3D printed turbine disk adopts a circular printing path to print a turbine disk blank in the lower mold area. The heating temperature of the lower mold is 300~700℃. And / or, the printing process parameters are: laser power 800~1200W, scanning speed 7~21mm / s, and powder feeding amount 8.5~17.5g / min.

7. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 1, characterized in that, In step three, after the turbine disk is 3D printed, there is no need to wait for it to cool down. It is directly transferred to the vacuum isothermal forging station along with the mold for vacuum isothermal forging. And / or, die transfer time ≤ 60s, forging temperature 980~1200℃, forging rate ≤ 0.15s. -1 The number of deformation cycles is 1 ≤ N ≤ 5, the deformation amount decreases with each deformation, the single deformation amount is 1~5%, the cumulative deformation amount is ≤15%, and the hot vacuum degree is ≤8×10. -3 Pa.

8. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to claim 1, characterized in that, In step four, after the heat treatment is completed, a five-axis machine tool is used for milling, with an average removal depth of ≤1mm and an overall material utilization rate of ≥97%.

9. The in-situ rapid preparation method of a high-uniformity nickel-based alloy turbine disk according to any one of claims 1 to 8, characterized in that, Steps one through four above can be repeated to achieve automated continuous production.

10. Different types of nickel-based alloy turbine disks prepared by the method according to any one of claims 1 to 9, characterized in that, The turbine disk has a density of approximately 99.5-99.9%, tensile strength increased by 5-20%, elongation increased by 10-50%, and grain size difference along the diameter direction of the turbine disk ≤ ±1 grade.

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