GH2132 alloy material and additive manufacturing crack inhibition method and application thereof

Abstract

The invention relates to the technical field of metal additive manufacturing, in particular to a GH2132 alloy material and an additive manufacturing crack inhibition method and application thereof. The GH2132 alloy material is prepared in the mode that GH2132G composite powder is melted and formed through a laser powder bed. The composite powder comprises GH2132 alloy powder and graphite powder, wherein the mass of the graphite powder is 3%-4% of the mass of the GH2132 alloy powder. The carbon content is increased by adding graphite in a specific proportion, grain boundary segregation of low-melting-point elements is inhibited, a crack-free GH2132 additive manufacturing formed part is obtained, and the service performance of the crack-free GH2132 additive manufacturing formed part in aerospace high-temperature bearing parts is improved.

Description

Technical Field

[0001] This invention relates to the field of metal additive manufacturing technology, and in particular to a GH2132 alloy material and its additive manufacturing crack suppression method and application. Background Technology

[0002] GH2132 is a Fe-Ni-Cr based precipitation-hardening wrought superalloy with an operating temperature range of -253℃ to 650℃. It exhibits excellent high and low temperature strength, corrosion resistance, and hot deformation properties, and is widely used in high-temperature load-bearing components such as turbine disks and compressor disks in aero-engines. Laser Powder Bed Fusion (LPBF) technology directly forms complex metal components through layer-by-layer powder deposition and selective laser melting, solving the problems of long processing cycles and high costs associated with traditional forging and casting processes. However, this alloy is prone to cracking defects during the rapid cooling process in LPBF, severely restricting its engineering applications.

[0003] Existing technology discloses a method for eliminating microcracks in GH3230 nickel-based superalloy laser selective melting (SLM). This method involves adding 1%–2% TiB2 ceramic powder (average particle size <1μm) to GH3230 alloy powder, followed by high-speed mixing via dual centrifugation (1400–1600 rpm), and then performing SLM forming using a laser with a power of 180–200 W and a scanning speed of 700–900 mm / s to eliminate microcracks. Specifically: First, the above technology is designed for nickel-based alloys (GH3230), while GH2132 is an iron-based alloy. The two have fundamentally different compositions and cracking mechanisms: GH2132 contains low-melting-point elements such as Ti, S, and P, which makes it more prone to grain boundary segregation and the formation of brittle phases during LPBF, leading to grain boundary weakening and cracking.

[0004] Secondly, when the mixing process of GH3230 (1400-1600rpm) is directly transferred to the GH2132-graphite system, high-speed stirring will cause powder to scatter and agglomerate, destroying the uniformity of powder spreading. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a GH2132 alloy material and its additive manufacturing crack suppression method, solving the crack defect problem of GH2132 iron-based superalloys in LPBF forming. By adding a specific proportion of graphite (3%–4%) to increase the carbon content, the segregation of low-melting-point elements at grain boundaries is suppressed; the composite powder preparation process is optimized to ensure uniform graphite adhesion and avoid powder damage; crack-free GH2132 additively manufactured parts are obtained, improving their performance in high-temperature load-bearing components in aerospace applications.

[0006] To achieve the above objectives, the embodiments of the present invention provide the following technical solutions: A GH2132 alloy material is prepared by laser powder bed melting of GH2132G composite powder; the composite powder comprises GH2132 alloy powder and graphite powder, wherein the mass of graphite powder is 3% to 4% of the mass of GH2132 alloy powder.

[0007] Optionally, the elemental composition of the GH2132 alloy powder by mass percentage is: C<0.08%, Cr13.5%~16%, Ni24%~27%, Mo1%~1.5%, Al<0.35%, Ti1.9%~2.3%, V0.1%~0.5%, B0.001%~0.01%, Si<1%, Mn1%~2%, S<0.02%, P<0.03%, with the balance being Fe and unavoidable impurities.

[0008] Optionally, the graphite powder has an average particle size of less than 1 μm, and the GH2132 alloy powder has a particle size distribution of 15~53 μm and an average particle size of 30-40 μm.

[0009] This invention also provides a method for suppressing cracks in additive manufacturing of GH2132 alloy material, comprising: GH2132 alloy powder and graphite powder were selected and prepared into composite powder according to a set ratio; The composite powder was subjected to multiple high-speed double centrifugal mixing until it was uniformly mixed and there was no obvious agglomeration, thus forming GH2132G composite powder. LPBF forming of stirred composite powder was performed using metal additive manufacturing equipment; The LPBF-formed samples were polished and the metallographic structure was observed to determine the crack situation.

[0010] Optionally, the graphite powder has a mass fraction of 3% to 4% of the GH2132 alloy powder.

[0011] Optionally, the LPBF forming process conditions are: laser power 180-200W, scanning speed 750-800mm / s, powder layer thickness 30-50μm, and scanning spacing 100-120μm.

[0012] Optionally, the LPBF forming process conditions are: laser power 190W, scanning speed 800mm / s, powder layer thickness 40μm, and scanning spacing 110μm.

[0013] Optionally, the mixing speed is 900-1100 rpm, and the mixing time is 1-2 minutes each time. After each mixing, cool to room temperature before mixing again, until the mixture is uniform and there is no obvious agglomeration.

[0014] Optionally, after laser powder bed melting and forming, the formed part is subjected to the following treatments in sequence: solution heat treatment at 1100-1200°C for 2 hours, and then aging heat treatment at 700-750°C for 16 hours.

[0015] This invention also provides an application of the GH2132 alloy material described above in the aerospace, petrochemical, or nuclear energy industries.

[0016] One or more technical solutions provided in the embodiments of the present invention have at least the following technical effects or advantages: 1. The composite powder of the present invention is composed of GH2132 alloy powder and 3% to 4% graphite powder. After being formed by laser powder bed melting, GH2132 alloy material is obtained. By increasing the carbon content to 3% to 4%, a continuous carbide film is formed during solidification, which reduces the tendency of brittle phases at grain boundaries. At the same time, the carbide acts as a heterogeneous nucleation point to refine the grains, reduce residual stress concentration, and suppress solidification cracks and solid-state phase transformation cracks. The rapid cooling characteristics of laser powder bed melting and the high thermal conductivity of graphite work synergistically to make the temperature gradient of the molten pool tend to be moderate, further reducing the probability of crack formation.

[0017] 2. Compared with the method of adding TiB2, increasing the carbon content by adding graphite not only helps to realize the alloying powder preparation process, but also improves its feasibility and practicality in engineering applications.

[0018] Advantages of additional aspects of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In addition, the dimensions or spacing between the components are exaggerated to show the position of each component, and the schematic diagrams are for illustrative purposes only.

[0020] Figure 1 This is a flowchart of the additive manufacturing crack suppression method provided in the embodiments of the present invention; Figure 2 This is a metallographic image of the final formed material provided in the embodiments of the present invention; Figure 3 This is a schematic diagram of the room temperature tensile stress-strain curve results provided in an embodiment of the present invention; Detailed Implementation It should be noted that the following detailed description is illustrative and intended to provide further explanation of the invention. Unless otherwise specified, all technical and scientific terms used in this invention have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0021] Terminology Explanation: GH2132 alloy: a Fe-Ni-Cr based precipitation hardening wrought high-temperature alloy with a service temperature range of -253℃ to 650℃. It has good high and low temperature strength and long-term stability, good corrosion resistance and hot deformation performance, as well as good machinability and satisfactory weldability.

[0022] This embodiment proposes a GH2132 alloy material, which is prepared by laser powder bed melting of GH2132G composite powder; the composite powder contains GH2132 alloy powder and graphite powder, wherein the mass of graphite powder is 3% to 4% of the mass of GH2132 alloy powder.

[0023] The insufficient initial carbon content (<0.08%) of GH2132 leads to the segregation of low-melting-point elements (Ti / S / P) at grain boundaries, forming brittle phases. Adding 3%–4% graphite increases the carbon content, promoting the formation of carbides (such as TiC and Cr7C3), consuming the segregated elements, and strengthening the grain boundaries. Uniform carbide distribution refines the grains and reduces residual stress concentration during the rapid cooling process of LPBF. LPBF forming technology enables the direct fabrication of complex structural parts through layer-by-layer melting and deposition. Combined with composite powders, it can reduce cracking while ensuring forming efficiency.

[0024] The elemental composition of the GH2132 alloy powder by mass percentage is as follows: C<0.08%, Cr13.5%~16%, Ni24%~27%, Mo1%~1.5%, Al<0.35%, Ti1.9%~2.3%, V0.1%~0.5%, B0.001%~0.01%, Si<1%, Mn1%~2%, S<0.02%, P<0.03%, with the balance being Fe and unavoidable impurities.

[0025] Cr and Ni elements endow the alloy with excellent corrosion resistance and high-temperature stability, providing basic protection for high-temperature load-bearing components. Mo, Ti, and other elements participate in precipitation hardening, enhancing the alloy's strength. Strict control of the content of low-melting-point elements such as S and P can reduce their segregation at grain boundaries and lower the probability of brittle phase formation. The balance of Fe elements serves as the matrix, ensuring the alloy's basic structure. Ti combines with added carbon to form TiC particles, blocking crack propagation paths, while B elements promote the precipitation of grain boundary strengthening phases, working with carbides to improve the high-temperature stability of grain boundaries. S < 0.02% and P < 0.03% reduce the formation of low-melting-point brittle phases (such as FeS), preventing grain boundary weakening. This composition allows the alloy to better utilize the grain boundary optimization effect of C when combined with graphite powder, providing a foundation for crack suppression.

[0026] The graphite powder has an average particle size of less than 1 μm, and the GH2132 alloy powder has a particle size distribution of 15~53 μm with an average particle size of 30-40 μm.

[0027] The particle size ratio of GH2132 alloy powder to graphite powder is >30 times, allowing submicron-sized graphite to fully coat the surface of GH2132 particles, preventing delamination due to size differences during mixing. Furthermore, smaller graphite particles melt and diffuse more easily during LPBF (Liquid-Based Burning), ensuring uniform carbon distribution and preventing unmelted graphite clusters from causing porosity or cracks. The matched particle sizes of the two powders ensure uniform incorporation of carbon into the molten pool during LPBF forming, uniformly optimizing the grain boundary structure and improving crack suppression.

[0028] This embodiment also provides a method for suppressing cracks in additive manufacturing of GH2132 alloy materials, such as... Figure 1 As shown, it includes: GH2132 alloy powder and graphite powder were selected and prepared into a composite powder according to a set ratio. Selecting the appropriate powders and preparing the composite powder is fundamental, providing qualified raw materials for subsequent processes.

[0029] The composite powder was subjected to multiple high-speed double centrifugal mixing processes until it was uniformly mixed and free of significant agglomeration, forming the GH2132G composite powder. These multiple high-speed double centrifugal mixing processes ensure uniform mixing of the graphite powder and GH2132 alloy powder, preventing graphite agglomeration from affecting the distribution of carbon and guaranteeing the flowability of the composite powder to meet the requirements for LPBF powder spreading.

[0030] LPBF forming of stirred composite powder was performed using metal additive manufacturing equipment. LPBF forming utilizes laser selective melting to achieve component shaping, and uniformly distributed carbon elements are incorporated to suppress crack formation.

[0031] The LPBF-formed samples are polished and the metallographic structure is observed to determine the crack situation. Polishing and observing the metallographic structure of the formed samples can visually verify the crack suppression effect and ensure the effectiveness of the process.

[0032] The graphite powder has a mass fraction of 3% to 4% of the GH2132 alloy powder. When the graphite mass fraction is 3% to 4%, the introduced carbon element can effectively optimize grain boundary strength, alleviate the adverse effects of residual stress and low-melting-point element segregation, and inhibit crack initiation. When the graphite powder content is below the lower limit (3%), the carbon element is insufficient to completely suppress Ti / S / P segregation, resulting in poor crack suppression. When it is above the upper limit (4%), graphite agglomeration occurs, and excessive carbon forms coarse carbides that weaken toughness, thereby increasing material brittleness and generating new defects. Therefore, a proportion of 3% to 4% can ensure crack suppression while avoiding negative impacts.

[0033] The LPBF forming process conditions are: laser power 180-200W, scanning speed 750-800mm / s, powder layer thickness 30-50μm, and scanning spacing 100-120μm.

[0034] Matching the laser power and scanning speed ensures complete melting of the GH2132G powder while avoiding excessive heat input that could exacerbate residual stress. Matching the powder layer thickness and scanning spacing guarantees interlayer bonding strength and forming accuracy, reducing stress concentration caused by poor interlayer bonding and eliminating incomplete fusion defects. This parameter range is adapted to the flowability and thermal conductivity of the composite powder, enabling uniform stress release during the melting and forming process. Combined with the effect of carbon, this further reduces cracking.

[0035] The mixing speed is 900-1100 rpm, and the mixing time is 1-2 minutes each time. After each mixing, cool to room temperature before mixing again, until the mixture is uniform and there is no obvious agglomeration.

[0036] A rotation speed range of 900-1100 rpm generates sufficient centrifugal force to ensure uniform adhesion of graphite powder to the surface of GH2132 alloy powder, while avoiding overheating or breakage of the powder due to excessive rotation speed. Below the lower limit of rotation speed (900 rpm), the centrifugal force is insufficient, and graphite cannot overcome van der Waals forces to disperse evenly; above the upper limit of rotation speed (1100 rpm), powder collision damage occurs, and the low density of graphite makes it prone to scattering. Each stirring session lasts 1-2 minutes, ensuring effective mixing without causing powder agglomeration due to excessive time; intermittent cooling prevents high-speed frictional heating that could lead to powder oxidation or graphite deterioration. These parameters work synergistically to ensure uniform mixing and stable performance of the composite powder, providing qualified raw materials for LPBF forming and crack suppression.

[0037] After laser powder bed melting and forming, the formed parts are subjected to the following treatments in sequence: solution heat treatment at 1100-1200°C for 2 hours, and then aging heat treatment at 700-750°C for 16 hours.

[0038] Solution heat treatment at 1100-1200℃ for 2 hours can eliminate residual stress generated during forming, dissolve the original γ' phase and carbides, improve the grain structure, and eliminate non-equilibrium phases formed during the LPBF process. Aging heat treatment at 700-750℃ for 16 hours promotes the precipitation of fine γ' strengthening phases while avoiding excessively high temperatures that could lead to grain boundary carbide coarsening, thus improving the alloy's mechanical properties. This heat treatment process does not cause material cracking. Combined with prior crack suppression measures (such as graphite addition and process parameter optimization), it reduces cracking while improving material strength and stability, meeting the requirements for high-temperature load-bearing components.

[0039] Specifically, it includes the following steps: Step 1: Select GH2132 alloy powder and graphite powder and prepare composite powder according to the set ratio.

[0040] In step 1, the mass fraction of graphite powder is 3% to 4% of the mass of GH2132 alloy powder. The particle size distribution of GH2132 alloy powder is 15 to 53 μm, with an average particle size of 30 to 40 μm; the average particle size of the graphite powder is less than 1 μm.

[0041] Step 2: Perform multiple high-speed double centrifugal mixing and stirring of the composite powder until it is uniformly mixed and there is no obvious agglomeration, forming GH2132G composite powder.

[0042] The GH2132G composite powder is prepared using high-speed mixing technology. The requirement is that the C powder adheres uniformly to the surface of the GH2132 powder without significant agglomeration, and the composite powder possesses a certain degree of flowability to meet the powder spreading requirements of the LPBF forming process.

[0043] The composite powder prepared in step 1 is subjected to double centrifugal high-speed mixing. The mixing speed is 900-1100 rpm, and the time is 1-2 minutes each time. After each mixing, the mixture is cooled to room temperature before the next mixing is carried out until the powder is mixed evenly without obvious agglomeration, thus forming GH2132G composite powder.

[0044] Step 3: Use metal additive manufacturing equipment to perform LPBF forming on the stirred GH2132G composite powder to obtain a sample.

[0045] The GH2132G composite powder obtained in the previous step was subjected to LPBF forming using a Concept Laser Mlab 200R metal additive manufacturing equipment. The laser power was 180-200W, the scanning speed was 750-800mm / s, the powder layer thickness was 30-50μm, and the scanning spacing was 100-120μm.

[0046] The sample was ground and polished using a grinding and polishing machine. First, it was ground with 180-grit sandpaper for 15 minutes, then with 320 and 600-grit sandpaper for 10 minutes each, then with 1500 and 2500-grit sandpaper for 15 minutes each, and finally with 3μm polishing cloth for 20 minutes and 0.04μm polishing cloth for 50 minutes. Its metallographic structure was then observed.

[0047] Step 4: The tensile specimens formed by LPBF are first subjected to solution heat treatment, followed by aging heat treatment. The heat treatment is carried out in an NBD-T1500 tubular heat treatment furnace. The specimens are first subjected to solution heat treatment at 1020°C for 2 hours, then subjected to aging heat treatment at 620°C for 16 hours, and finally subjected to high-temperature tensile testing.

[0048] In this embodiment, GH2132 alloy powder and graphite powder are mixed in a set ratio to form a composite powder. After stirring, GH2132G powder is formed and then subjected to LPBF forming. This process can suppress cracks generated during forming and prevent the material from cracking during heat treatment. By adding graphite externally, the carbon content in the GH2132 alloy can be increased, making it easier to quantitatively control the carbon content. This method is highly practical and suitable for industrial production.

[0049] This embodiment also provides an application of the GH2132 alloy material in the aerospace, petrochemical, or nuclear energy industries.

[0050] Components in the aerospace industry, such as turbine disks and compressor disks, operate under high-temperature and high-stress environments, requiring materials with extremely high crack resistance and mechanical properties. Equipment components in the petrochemical and nuclear energy industries also frequently operate under complex conditions (such as high temperature and corrosion). This alloy material improves reliability by suppressing cracks, while also possessing excellent high and low temperature strength and corrosion resistance, meeting the performance requirements of high-temperature load-bearing components in these fields. Therefore, it can be applied in the aforementioned applications.

[0051] Example Step 1: In this embodiment, GH3230 alloy powder with an average particle size of 30.04 μm and graphite powder with an average particle size of 500 nm are selected and a composite powder is prepared according to the mass ratio of GH2132:C powder of 97:3.

[0052] Step 2: Perform double centrifugal high-speed mixing on the composite powder prepared in Step 1. The mixing speed is 1000 rpm and the time is 1.5 minutes each time. After each mixing, cool to room temperature before the next mixing is performed until the powder is evenly mixed without obvious agglomeration, forming GH2132G composite powder.

[0053] Step 3: The GH2132G composite powder obtained in the previous step was subjected to LPBF forming using a Concept Laser Mlab 200R metal additive manufacturing equipment with a laser power of 190W, a scanning speed of 800mm / s, a layer thickness of 40μm, and a scanning spacing of 110μm.

[0054] The sample was ground and polished using a grinding and polishing machine. First, it was ground with 180-grit sandpaper for 15 minutes, then with 320 and 600-grit sandpaper for 10 minutes each, followed by 1500 and 2500-grit sandpaper for 15 minutes each. Finally, it was polished with 3μm polishing cloth for 20 minutes and 0.04μm polishing cloth for 50 minutes. The metallographic structure was then observed (e.g., ...). Figure 2 (As shown).

[0055] Step 4: The tensile specimens formed by LPBF were first subjected to solution heat treatment, followed by aging heat treatment. The heat treatment was performed using an NBD-T1500 tubular heat treatment furnace. The specimens were first subjected to solution heat treatment at 1020°C for 2 hours, then to aging heat treatment at 620°C for 16 hours, followed by high-temperature tensile testing. The tensile strain curves are shown below. Figure 3 As shown.

[0056] Comparative Example The difference between the comparative example and the embodiment is that C powder is not added, and pure GH2132 powder is used.

[0057] like Figure 3 The figure shows a comparison of the tensile properties of the two GH2132 series alloys at room temperature between this embodiment and the comparative example. The results show that the GH2132G-AB alloy prepared in the embodiment has a yield strength of about 880 MPa and a tensile strength close to 900 MPa; while the yield strength of the conventional GH2132 alloy in the comparative example is only about 180 MPa and the tensile strength is less than 200 MPa.

[0058] It can be seen that the GH2132G alloy prepared by this method exhibits a nearly 390% increase in yield strength and an approximately 350% increase in tensile strength. The main reason for this performance improvement is that this method significantly promotes carbide precipitation by increasing the carbon content in the alloy to 3%. During subsequent heat treatment, these carbides can be uniformly dispersed in the matrix, effectively suppressing dislocation movement and slip during tensile testing, thereby significantly improving the material's strength and overall mechanical properties.

[0059] In contrast, the GH2132 alloy, which did not have additional carbon added in the comparison, is a traditional solid solution strengthened iron-based alloy with a low carbon content, making it difficult for strengthening carbides to precipitate after heat treatment. Furthermore, prolonged heat treatment can easily lead to grain coarsening and a decrease in dislocation density, thereby further weakening the alloy's mechanical properties.

[0060] In summary, the GH2132G alloy prepared using the method of this embodiment can achieve a significant increase in strength through simple heat treatment without complex processing after SLM forming. The carbide precipitation strengthening mechanism can effectively enhance material properties without inducing cracking, and this process path is stable and suitable for forming complex components.

[0061] Furthermore, compared to controlling carbon content through vacuum melting or other methods, this method can directly increase the C content through process control during the powder preparation or mixing stage. It is simple to operate, provides precise element control, and is suitable for large-scale industrial production applications.

[0062] While the specific embodiments of the present invention have been described above in conjunction with the accompanying drawings, this is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art without creative effort based on the technical solutions of the present invention are still within the scope of protection of the present invention.

Claims

1. A GH2132 alloy material, characterized in that, It was prepared by laser powder bed melting and forming of GH2132G composite powder; The composite powder comprises GH2132 alloy powder and graphite powder, wherein the mass of graphite powder is 3% to 4% of the mass of GH2132 alloy powder.

2. The GH2132 alloy material according to claim 1, characterized in that, The elemental composition of the GH2132 alloy powder by mass percentage is as follows: C<0.08%, Cr13.5%~16%, Ni24%~27%, Mo1%~1.5%, Al<0.35%, Ti1.9%~2.3%, V0.1%~0.5%, B0.001%~0.01%, Si<1%, Mn1%~2%, S<0.02%, P<0.03%, with the balance being Fe and unavoidable impurities.

3. The GH2132 alloy material according to claim 1, characterized in that, The graphite powder has an average particle size of less than 1 μm, and the GH2132 alloy powder has a particle size distribution of 15~53 μm with an average particle size of 30-40 μm.

4. A method for suppressing cracks in additive manufacturing of GH2132 alloy material, characterized in that, include: GH2132 alloy powder and graphite powder were selected and prepared into composite powder according to a set ratio; The composite powder was subjected to multiple high-speed double centrifugal mixing until it was uniformly mixed and there was no obvious agglomeration, thus forming GH2132G composite powder. LPBF forming of stirred composite powder was performed using metal additive manufacturing equipment; The LPBF-formed samples were polished and the metallographic structure was observed to determine the crack situation.

5. The additive manufacturing crack suppression method according to claim 4, characterized in that, The mass fraction of the graphite powder is 3% to 4% of the mass of the GH2132 alloy powder.

6. The additive manufacturing crack suppression method according to claim 4, characterized in that, The LPBF forming process conditions are: laser power 180-200W, scanning speed 750-800mm / s, powder layer thickness 30-50μm, and scanning spacing 100-120μm.

7. The additive manufacturing crack suppression method according to claim 4, characterized in that, The LPBF forming process conditions are: laser power 190W, scanning speed 800mm / s, powder layer thickness 40μm, and scanning spacing 110μm.

8. The additive manufacturing crack suppression method according to claim 4, characterized in that, The mixing speed is 900-1100 rpm, and the mixing time is 1-2 minutes each time. After each mixing, cool to room temperature before mixing again, until the mixture is uniform and there is no obvious agglomeration.

9. The additive manufacturing crack suppression method according to claim 4, characterized in that, After laser powder bed melting and forming, the formed parts are subjected to the following treatments in sequence: solution heat treatment at 1100-1200°C for 2 hours, and then aging heat treatment at 700-750°C for 16 hours.

10. The application of the GH2132 alloy material as described in any one of claims 1 to 3 in the aerospace, petrochemical or nuclear energy industries.

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