A nickel-based alloy and a preparation method and application thereof

Abstract

The application discloses a nickel-based alloy and a preparation method and application thereof. The preparation method of the nickel-based alloy comprises the following steps: sequentially performing laser selective melting forming treatment and heat treatment on a nickel-based alloy raw material, and the nickel-based alloy is obtained. In the laser selective melting forming, the laser power is 315-325 W, and the spot diameter is 0.1 mm. In the heat treatment, the heating temperature is 790-810 DEG C, the time for keeping the heating temperature is 8h+ / -15min, and after keeping the heating temperature for 8h+ / -15min, cooling is performed; the cooling rate is greater than 14 DEG C / min, and the cooling temperature is 528-548 DEG C. The preparation method of the nickel-based alloy is simple and short in period, the high-temperature mechanical properties of the nickel-based alloy are remarkably improved, the structure is uniform and dense, and the application requirements in the field of aerospace can be met.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of metal additive manufacturing and high-temperature alloy, in particular to a nickel-based alloy and a preparation method and application thereof. BACKGROUND

[0002] Nickel-based high-temperature alloy has good high-temperature strength, excellent fatigue resistance and creep resistance, and has become an irreplaceable key material for modern national defense construction. GTD222 alloy (domestic brand K4222) is a Ni-Cr-based precipitation hardening type nickel-based high-temperature alloy, and the service temperature is below 1000 DEG C. The alloy has moderate high-temperature strength, good creep resistance and fatigue resistance, and good microstructure stability at high temperature, and is suitable for manufacturing gas turbine guide vanes and other long-term service static parts working below 1000 DEG C.

[0003] With the development of advanced aero-engine and gas turbine technology, the structural design of hot end components is becoming more and more complex, and the traditional manufacturing process cannot manufacture special complex part structure due to the limitation of processing technology, and has to sacrifice part of the structural functionality, which seriously restricts the development of aero-engine and gas turbine. At present, the laser selective melting forming technology (Select Laser Melting, SLM) uses high-energy laser beam to scan and melt the pre-set powder of powder bed layer by layer, realizes the direct manufacturing of near-net-shaped parts from three-dimensional model, has the advantages of small forming constraint, high precision and low surface roughness, and has been gradually applied in the manufacturing field of complex shape or internal cavity structure parts.

[0004] The laser selective melting forming process is significantly different from the traditional forging, casting and other manufacturing processes, mainly in the following aspects: ① The laser selective melting forming process has small molten pool (100-300 μm), large molten pool temperature gradient (105-106 K / s) and extremely fast solidification speed; ② The temperature gradient of the molten pool is roughly along the deposition direction, when the laser beam scans the powder layer, the top of the columnar crystal of the previous layer which has been solidified is remelted, and the unmelted part of the columnar crystal becomes the crystal nucleus of directional solidification of the layer, so that the original columnar grains of the previous layer continue to grow along the deposition direction; ③ During the forming process, the rapid repeated heating of the molten pool caused by layer-by-layer accumulation results in large residual stress. The above characteristics promote the great difference between the SLM forming structure and the microstructure of traditional castings and forgings.

[0005] However, the performance of GTD222 alloy mainly depends on the microstructure of the alloy, and the microstructure of the alloy is closely related to the composition of the alloy, the manufacturing method and the heat treatment parameters. The unique process of laser selective melting forming means that the heat treatment system suitable for cast GTD222 alloy may not be suitable for SLM manufactured GTD222 alloy.

[0006] In order to ensure that the SLM formed GTD222 alloy has good high temperature mechanical properties, the forming process and heat treatment system matched with the laser selective melting forming process must be established. The literature (R. Wang, G. Zhu, Q. Tan, W. Zhou, C. Yang, D. Wang, A. Dong, D. Shu, L. Zhang, B. Sun, Effect of high temperature aging on microstructures and tensile properties of a selective laser melted GTD222 superalloy, Journal of Alloys and Compounds (2020), doi: https: / / doi.org / 10.1016 / j.jallcom.2020.157226.) gives a kind of GTD222 alloy SLM forming process and heat treatment method, but the obtained GTD222 alloy has high strength but poor plasticity at room temperature, or good plasticity but poor strength, which cannot realize the simultaneous possession of better strength and plasticity, and the comprehensive mechanical properties are not good.

[0007] GTD222 alloy is an important material for manufacturing 1000℃ below working aero-engine and ground gas turbine parts, and its mechanical properties at 1000℃ are extremely critical to the durability of the parts, and improving its mechanical properties has important engineering significance. The unique process of laser selective melting forming is significantly different from the traditional casting GTD222 alloy process, and the GTD222 forming process and heat treatment system need to be developed according to the characteristics of the laser selective forming process. In addition, when the content of Al+Ti+Ta elements that cause cracks in GTD222 alloy is in the range of 4.2-4.8wt%, the crack generation tendency is large during the additive manufacturing process, and defects that reduce the mechanical properties are easy to produce. Through retrieval of domestic and foreign related patents and literature, there are few methods to improve the mechanical properties of laser selective melting formed GTD222 alloy, or the SLM forming process and heat treatment method proposed by some methods cannot obtain GTD222 alloy with high strength and toughness. SUMMARY

[0008] The technical problem to be solved by the present scheme is to overcome the defects of poor high temperature mechanical properties and high temperature endurance performance of the existing nickel-based alloy, and to provide a nickel-based alloy, a preparation method and application thereof. The preparation method of the nickel-based alloy in the present application optimizes the process parameters in the steps of laser selective melting forming and heat treatment, suppresses the generation of defects of laser selective melting formed GTD222 alloy, and improves the strength and plasticity of laser selective melting formed GTD222 alloy.

[0009] In order to achieve the above object, the present application provides the following technical solutions.

[0010] One of the technical solutions provided by the present application is a preparation method of a nickel-based alloy, which comprises the following steps: sequentially performing laser selective melting forming treatment and heat treatment on a nickel-based alloy raw material, and then the nickel-based alloy raw material is obtained.

[0011] In the laser selective melting forming, the laser power is 315-325 W, and the spot diameter is 0.1 mm.

[0012] In the heat treatment, the heating temperature is 790-810 DEG C, and the time for maintaining the heating temperature is 8 h ± 15 min.

[0013] After maintaining the heating temperature for 8 h ± 15 min, cooling is performed, the cooling rate is greater than 14 DEG C / min, and the cooling temperature is 528-548 DEG C.

[0014] In the present application, the nickel-based alloy raw material comprises C, Cr, Co, Nb, Ti, Al, Ta, Ni and B.

[0015] The content of C can be 0.07-0.13%, preferably 0.10%, and the percentage is the mass percentage of C in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0016] The content of Cr can be 21.50-23.50%, preferably 22.3%, and the percentage is the mass percentage of Cr in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0017] The content of Co can be 18.0-20.0%, preferably 18.82%, and the percentage is the mass percentage of Co in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0018] The content of Nb can be 0.6-1.0%, preferably 0.8%, and the percentage is the mass percentage of Nb in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0019] The content of Ti can be 2.0-2.5%, preferably 2.32%, and the percentage is the mass percentage of Ti in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0020] The content of Al can be 0.9-1.5%, preferably 1.18%, and the percentage is the mass percentage of Al in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0021] The content of Ta can be 0.7-1.3%, preferably 0.99%. The percentage is the mass percentage of Ta in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0022] The content of B can be 0.002-0.013%, preferably 0.003%. The percentage is the mass percentage of B in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0023] The content of Ni is the balance. The percentage is the mass percentage of Ni in the total mass of the nickel-based alloy raw material used in the laser selective melting forming.

[0024] In the present application, the "balance" does not exclude other elements in addition to the elements mentioned in the present application that can also be included in the nickel-based alloy raw material, such as Mn, Si, P or S. When the nickel-based alloy raw material also includes other elements in addition to the elements mentioned in the present application, the amount of Ni is adjusted accordingly so that the mass percentage of elements other than Ni in the nickel-based alloy raw material is within the range defined in the present application.

[0025] In the present application, the particle size of the nickel-based alloy raw material can be conventional in the art, and the particle size distribution range is generally 15-45 μm. Preferably, D10 is 15-25 μm, D50 is 26-35 μm, and D90 is 40-60 μm.

[0026] In the present application, according to the conventional practice in the art, D10 generally refers to the particle size corresponding to the cumulative particle size distribution volume percentage of 10% of the nickel-based alloy raw material. D50 generally refers to the particle size corresponding to the cumulative particle size distribution volume percentage of 50% of the nickel-based alloy raw material, i.e. the volume distribution median particle size or volume distribution median particle size. D90 generally refers to the particle size corresponding to the cumulative particle size distribution volume percentage of 90% of the nickel-based alloy raw material.

[0027] In the present application, the laser selective melting forming can generally be carried out in an argon atmosphere. In the argon atmosphere, the purity of argon can be greater than 99.99 wt%.

[0028] In the laser selective melting forming, the oxygen content in the forming chamber can be 0.1% or less.

[0029] In the laser selective melting forming, the laser power is preferably 320 W. The scanning pitch can be 0.09-0.1 mm. The scanning speed can be 1130-1230 mm / s, preferably 1150 mm / s. The powder layer thickness can be 0.04 mm.

[0030] In the present application, the heat treatment can generally be carried out in a vacuum or in a protective atmosphere.

[0031] The heating temperature in the heat treatment is preferably 800℃. The rate of temperature rise to the heating temperature can be conventional in the art, preferably 5-15℃ / min; for example 10℃. The time of maintaining the heating temperature is preferably 8h.

[0032] After maintaining the heating temperature for 8h±15min, cooling is performed; the rate of temperature drop in the cooling is preferably 15-20℃ / min. The temperature in the cooling is preferably 538℃.

[0033] In the heat treatment, after the temperature drop to the temperature in the cooling (528-548℃), a step of cooling to room temperature is generally included. The room temperature can be generally 20-30℃.

[0034] In the present application, the preparation method of the nickel-based alloy preferably does not include a step of hot isostatic pressing.

[0035] The isostatic pressing can be conventional in the art; for example, under the condition that the vacuum degree in the working chamber is not higher than 100pa, argon is filled as the protective gas, the heating rate is 5℃ / min, the temperature is 1175±10℃, the pressure is 160MPa±10MPa, and the temperature is maintained for 2h, and then the temperature is cooled to below 425℃ at a rate of 10℃ / min.

[0036] The second technical solution provided by the present application is a nickel-based alloy prepared by the above preparation method of the nickel-based alloy.

[0037] In the present application, the nickel-based alloy can be conventional in the art, for example, the nickel-based alloy with the brand GTD222.

[0038] The third technical solution provided by the present application is an application of the nickel-based alloy in the hot end parts of an aero-engine and a gas turbine.

[0039] On the basis of common sense in the art, the above-mentioned preferred conditions can be combined arbitrarily, i.e. to obtain each preferred example of the present application.

[0040] The reagents and raw materials used in the present application are commercially available.

[0041] The positive progress effect of the present application is that:

[0042] 1. In the present application, the preparation method of the nickel-based alloy adopts SLM technology, which realizes the short-period manufacturing of the GTD222 alloy complex component.

[0043] 2. In the preparation method of the nickel-based alloy in the present application, the SLM forming rate is high, which improves the SLM forming efficiency and ensures the compactness of the structure.

[0044] Further, through the control of the SLM forming process, although the content of the elements Al+Ti+Ta causing crack generation in the GTD222 alloy is high, the SLM forming structure density can be more than 99.5% without heat isostatic pressing treatment.

[0045] 3、The preparation method of the nickel-based alloy in the application has simple heat treatment process steps, and improves the mechanical properties of the nickel-based alloy at room temperature and high temperature (760℃), which significantly exceeds the casting standard requirements of GTD222, and the structure is uniform and dense, which can meet the application requirements in the field of aerospace. BRIEF DESCRIPTION OF DRAWINGS

[0046] Figure 1 The microstructure morphology diagram of the as-deposited GTD222 alloy prepared by SLM described in Example 1.

[0047] Figure 2 The microstructure morphology of the GTD222 alloy prepared by SLM after heat treatment / heat isostatic pressing treatment described in Comparative Example 1.

[0048] Figure 3 The grain morphology of the GTD222 alloy prepared by SLM before heat treatment described in Example 1.

[0049] Figure 4 The intragranular and grain boundary precipitate morphology of the GTD222 alloy prepared by SLM after heat treatment described in Example 1.

[0050] Figure 5 The intragranular and grain boundary precipitate morphology of the GTD222 alloy prepared by SLM after heat treatment described in Comparative Example 3. DETAILED DESCRIPTION

[0051] The application will be further described in the following examples, but the application is not limited in the scope of the examples. The experimental methods in the following examples without specific conditions are selected according to conventional methods and conditions, or according to the instructions of the commodity.

[0052] Explanation of technical terms:

[0053] Additive manufacturing technology, also known as 3D printing technology, mainly uses powder, granules or metal wire as raw material, through CAD model pre-layering processing, using high-energy beam melting accumulation growth ("additive manufacturing"), directly completing the "near-net-shape" of high-performance components from the CAD model in one step.

[0054] Selective laser melting: an additive manufacturing technology for forming parts by laser melting pre-placed metal powder.

[0055] The preparation method of the nickel-based alloy in the following examples and comparative examples includes the following steps:

[0056] (1) Prepare the powder of nickel-based alloy (GTD222 superalloy) ;

[0057] (2) Introduce the model of the part to be formed into the laser selective melting forming equipment, and perform substrate leveling and pre-powder laying;

[0058] (3) Introduce the protective atmosphere, and set the melting forming parameters;

[0059] (4) After the melting forming is completed, clean the part;

[0060] (5) Perform heat treatment on the part;

[0061] (6) Separate the part after heat treatment from the substrate.

[0062] Example 1

[0063] (1) Preparation of GTD222 superalloy powder:

[0064] The particle size distribution range of the GTD222 superalloy powder is 15-45 μm; wherein, D10 is 15-25 μm, D50 is 26-35 μm, and D90 is 40-60 μm.

[0065] The powder composition is (the mass percentage of each component in the total mass of the GTD222 superalloy powder) :

[0066] C: 0.10%, Mn: 0.0001%, Si: 0.019%, P: 0.002%, S: 0.0007%, Cr: 22.3%, Co: 18.82%, Nb: 0.8%, Ti: 2.32%, Al: 1.18%, Ta: 0.99%, Ni: balance, B: 0.003%.

[0067] (2) Introduce the model of the part to be formed into the laser selective melting forming equipment, and perform substrate leveling and pre-powder laying, specifically as follows:

[0068] 1) According to the characteristics of the part to be formed, establish a three-dimensional model on a computer and save it as an STL format file, introduce it into the building software of the laser selective melting forming equipment, and perform layering processing.

[0069] 2) The substrate of the forming bin uses stainless steel material, and the substrate is leveled, then the nickel-based superalloy powder obtained in step (1) is loaded into the powder supply cylinder of the powder bed selective laser melting forming equipment, and the powder is uniformly laid on the forming substrate using a scraper, and the equipment cabin door is closed.

[0070] The microstructure morphology diagram of the as-deposited GTD222 alloy sample obtained by laser selective melting forming is as shown in Figure 1As shown, a small amount of porosity defects exist in the organization.

[0071] (3) Introduce a protective atmosphere, and set the melting forming parameters;

[0072] Introduce high-purity argon (purity 99.99wt%) protection, control the oxygen content in the cavity ≤0.1%; set the solid forming parameters: laser power 320W, spot diameter 0.1mm, scanning speed 1150mm / s, scanning interval 0.09mm, powder layer thickness 0.04mm.

[0073] (4) After the melting forming is completed, the workpiece is cleaned: the residual powder of the formed sample is cleaned.

[0074] (5) Heat treatment of the workpiece:

[0075] Heated to 800℃±10℃ at 10℃ / min in vacuum or protective atmosphere, held for 8h, furnace cooled to 538℃±10℃ at 20℃ / min, and then air cooled to room temperature.

[0076] As shown in the microstructure morphology of the GTD222 alloy sample obtained by laser selective melting after heat treatment, and the intracrystalline and grain boundary precipitate morphology is as shown in Figure 3 , it can be seen that a small amount of carbide exists in the intracrystalline and grain boundary, which is beneficial to reduce the crack initiation after stress. Figure 4 Figure 4

[0077] (6) Separate the heat-treated workpiece from the substrate: use wire cutting process to separate the formed piece from the substrate.

[0078] The density of the GTD222 high-temperature alloy formed piece obtained by SLM in Example 1 is 99.53%, and the room temperature and high-temperature mechanical properties are as shown in Table 1, which meet the requirements of GTD222 casting standards. Among them, the tensile properties are measured by MTS Landmark 370.10 testing machine; the endurance properties are measured by high-temperature endurance creep testing machine.

[0079] Table 1

[0080]

[0081] Comparative Example 1

[0082] (1) GTD222 high-temperature alloy powder preparation

[0083] Consistent with Example 1.

[0084] (2) The to-be-formed piece model is introduced into the laser selective melting forming equipment, and the substrate is leveled and pre-powdered​​

[0085] The same as example 1.

[0086] (3) Introduce a protective atmosphere, and set the melting forming parameters

[0087] Introduce high-purity argon (purity 99.99wt%) protection, control the oxygen content in the cavity ≤0.1%; set the laser power to 295W, the spot diameter to 0.1mm, the scanning speed to 1130mm / s, the scanning interval to 0.1mm, and the powder layer thickness to 0.04mm.

[0088] (4) After the melting forming is completed, clean the workpiece

[0089] The same as example 1.

[0090] (5) The workpiece is subjected to heat treatment

[0091] The heat treatment system of the GTD222 alloy workpiece is: heated to 800℃±10℃ at 10℃ / min in vacuum or a protective atmosphere, kept for 8h, furnace-cooled to 538℃±10℃ at 20℃ / min, and then air-cooled to room temperature.

[0092] The microstructure morphology of the GTD222 alloy sample obtained by laser selective melting after heat treatment is shown in Figure 2 It can be seen that there are many pores in the microstructure.

[0093] (6) The workpiece is separated from the substrate

[0094] The formed workpiece is separated from the substrate by wire cutting process.

[0095] The density of the GTD222 high-temperature alloy workpiece obtained by SLM in this comparative example is 99.10%.

[0096] Comparative example 2

[0097] (1) Preparation of GTD222 high-temperature alloy powder

[0098] The same as example 1.

[0099] (2) The model of the workpiece to be formed is introduced into the laser selective melting forming equipment, and the substrate is leveled and pre-powdered

[0100] The same as example 1.

[0101] (3) Introduce a protective atmosphere, and set the melting forming parameters

[0102] The high-purity argon gas (purity of 99.99wt%) is introduced to protect, and the oxygen content in the cavity is controlled to be less than or equal to 0.1%; the laser power is set to be 285W, the spot diameter is 0.1mm, the scanning speed is 1050mm / s, the scanning interval is 0.1mm, and the powder layer thickness is 0.04mm.

[0103] (4) After the melting forming is completed, the workpiece is cleaned

[0104] The embodiment 1 is adopted.

[0105] (5) The workpiece is subjected to heat treatment

[0106] The heat treatment system of the GTD222 alloy workpiece is as follows: heating to 800℃±10℃ at a rate of 10℃ / min in vacuum or protective atmosphere, holding for 8h, furnace cooling to 538℃±10℃ at a rate of more than 14℃ / min, and then air cooling to room temperature.

[0107] (6) The workpiece is separated from the substrate

[0108] The forming piece is separated from the substrate by using the wire cutting process.

[0109] The density of the GTD222 high-temperature alloy forming piece obtained by the SLM of the present comparative example is 99.05%.

[0110] Comparative example 3

[0111] (1) Preparation of GTD222 high-temperature alloy powder

[0112] The embodiment 1 is adopted.

[0113] (2) The model of the workpiece to be formed is introduced into the laser selective melting forming equipment, and the substrate is leveled and pre-powdered

[0114] The embodiment 1 is adopted.

[0115] (3) The protective atmosphere is introduced, and the melting forming parameters are set

[0116] The high-purity argon gas (purity of 99.99wt%) is introduced to protect, and the oxygen content in the cavity is controlled to be less than or equal to 0.1%; the solid forming parameters are set as follows: the laser power is 320W, the spot diameter is 0.1mm, the scanning speed is 1150mm / s, the scanning interval is 0.09mm, and the powder layer thickness is 0.04mm.

[0117] (4) After the melting forming is completed, the workpiece is cleaned

[0118] The residual powder of the formed sample is cleaned.

[0119] (5) The workpiece is subjected to heat isostatic pressing treatment

[0120] The hot isostatic pressing parameters of the GTD222 alloy part are as follows: under the condition that the working chamber vacuum degree is not higher than 100 Pa, argon is filled as a protective gas, the heating rate is 5 ℃ / min, the temperature is 1175±10 ℃, the pressure is 160 MPa±10 MPa, and the temperature is kept for 2 hours, and then the temperature is cooled to below 425 ℃ at a rate of 10 ℃ / min.

[0121] (6) Heat treatment of the part

[0122] The heat treatment system of the GTD222 alloy part is as follows: heating to 800 ℃±10 ℃ at a rate of 10 ℃ / min in vacuum or a protective atmosphere, keeping for 8 hours, furnace cooling to 538 ℃±10 ℃ at a rate of 20 ℃ / min, and then air cooling to room temperature.

[0123] As shown in FIG. 5, the intracrystalline and grain boundary precipitate morphology of the GTD222 alloy sample formed by laser selective melting and then heat treated is obtained by a scanning electron microscope (ZEISS SIGMA 500). Figure 5 As shown in FIG. 5, the intracrystalline and grain boundary precipitate morphology of the GTD222 alloy sample formed by laser selective melting and then heat treated is obtained by a scanning electron microscope (ZEISS SIGMA 500). Figure 5 As shown in FIG. 5, the intracrystalline and grain boundary precipitate morphology of the GTD222 alloy sample formed by laser selective melting and then heat treated is obtained by a scanning electron microscope (ZEISS SIGMA 500). Figure 5 As shown in FIG. 5, the intracrystalline and grain boundary precipitate morphology of the GTD222 alloy sample formed by laser selective melting and then heat treated is obtained by a scanning electron microscope (ZEISS SIGMA 500).

[0124] (7) Separation of the part from the substrate

[0125] The formed part is separated from the substrate by wire cutting.

[0126] The density of the GTD222 high-temperature alloy part obtained by SLM in Comparative Example 3 is 99.92%, and the room temperature and high-temperature mechanical properties are as shown in Table 2, and part of the high-temperature properties (δ5 and ψ under the condition of 760 ℃) do not meet the requirements of the GTD222 casting standard.

[0127] Table 2

[0128]

[0129] As can be seen from the examples and comparative examples, there is a synergistic effect between the various process parameters and conditions of the present application, and when a parameter or a process link is not within the protection scope of the present application, the performance of the obtained product is far worse than that of the present application.

Claims

1. A method for preparing a nickel-based alloy, comprising the following steps: sequentially performing a laser selective melting forming treatment and a heat treatment on a nickel-based alloy raw material, wherein the nickel-based alloy raw material comprises C, Cr, Co, Nb, Ti, Al, Ta, Ni and B, wherein, the content of the C is 0.07-0.13%; the content of the Cr is 21.50-23.50%; the content of the Co is 18.0-20.0%; the content of the Nb is 0.6-1.0%; the content of the Ti is 2.0-2.5%; the content of the Al is 0.9-1.5%; the content of the Ta is 0.7-1.3%; the content of the B is 0.002-0.013%; and the content of the Ni is the balance; the percentages are mass percentages of the components in the total mass of the nickel-based alloy raw material used in the laser selective melting forming; in the laser selective melting forming, the laser power is 315-325 W; the spot diameter is 0.1 mm; the scanning interval is 0.09-0.1 mm; the scanning speed is 1130-1230 mm / s; and the powder layer thickness is 0.04 mm; in the heat treatment, the heating temperature is 790-810℃; and the time for maintaining the heating temperature is 8 h±15 min; after maintaining the heating temperature for 8 h±15 min, cooling is performed; the cooling rate is greater than 14℃ / min; and the cooling temperature is 528-548℃; the particle size distribution range of the nickel-based alloy raw material is 15-45 μm, D10 is 15-25 μm, D50 is 26-35 μm, and D90 is 40-60 μm. the content of the C is 0.10%; the content of the Cr is 22.3%; the content of the Co is 18.82%; the content of the Nb is 0.8%; the content of the Ti is 2.32%; the content of the Al is 1.18%; the content of the Ta is 0.99%; the content of the B is 0.003%. the laser selective melting forming is performed in an argon atmosphere; in the argon atmosphere, the purity of argon is greater than or equal to 99.99 wt%; in the laser selective melting forming, the oxygen content in the forming chamber can be less than or equal to 0.1%. in the laser selective melting forming, the laser power is 320 W. the heat treatment is performed in a vacuum condition or a protective atmosphere; in the heat treatment, the heating temperature is 800℃; in the heat treatment, the heating rate is 5-15℃ / min; 2. The method of producing a nickel-based alloy according to claim 1, wherein the time for maintaining the heating temperature is 8 h; after maintaining the heating temperature for 8 h±15 min, cooling is performed; the cooling rate is 15-20℃ / min; and the cooling temperature is 538℃; in the heat treatment, after cooling to the cooling temperature, a step of cooling to room temperature is further included; and the room temperature is 20-30℃. the method for preparing the nickel-based alloy does not comprise a step of hot isostatic pressing treatment. the nickel-based alloy is prepared by the method for preparing a nickel-based alloy according to any one of claims 1-7. ​ ​ ​ 3. The method of producing a nickel-based alloy according to claim 1, wherein ​ 4. The method of producing a nickel-based alloy according to claim 1, wherein ​ 5. The method of producing a nickel-based alloy according to claim 1, wherein ​ 6. The method of producing a nickel-based alloy according to claim 1, wherein ​ ​ ​ ​ ​ ​ 7. The method of producing a nickel-based alloy according to claim 1, wherein ​ 8. A nickel-based alloy characterized in that, ​ 9. Use of a nickel-base alloy as claimed in claim 8 in hot section components of aircraft engines and gas turbines.

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