Method for preparing high-performance GH4079 disc ring piece and disc ring piece for aero-engine

Abstract

The invention belongs to the technical field of powder metallurgy, and relates to a method for preparing a high-performance GH4079 disc ring piece and a disc ring piece for an aero-engine. The preparation method comprises the following steps: firstly, preparing GH4079 spherical powder with the particle size of 106-250 microns by adopting a specific method; then, the GH4079 spherical powder is loaded into a prefabricated sheath, and degassing and seal welding treatment is carried out on the GH4079 spherical powder; then the sheath is sequentially subjected to high-temperature heat treatment and hot isostatic pressing treatment; and finally, the sheath is removed, and the powder metallurgy GH4079 blank is obtained. And the powder metallurgy GH4079 blank is subjected to heat treatment, and the GH4079 disc ring workpiece is obtained. According to the method provided by the invention, the problems of blank cracking and low yield in the existing forging process can be practically and effectively solved, and the utilization rate of the alloy material and the stability of the production process are promoted to be improved.

Description

Technical Field

[0001] The invention belongs to the technical field of powder metallurgy and relates to a method for preparing a high-performance GH4079 disc ring component and a disc ring component for an aeroengine. Background Art

[0002] GH4079 alloy is a Ni-Co-Cr based precipitation hardening deformation alloy, and its long-term use temperature can reach 750℃ to 800℃. Based on GH4742, this alloy increases the content of aluminum, titanium and niobium elements to promote the formation of more γ' phase, of which ω (γ') accounts for about 45% of the alloy, which makes GH4079 alloy have higher room temperature strength and high temperature performance, as well as good organizational stability and corrosion resistance, making it very suitable for manufacturing aircraft engine turbine disks, sealing disks and other components.

[0003] The hot isostatic pressing process uses argon as the transmission medium to apply compressive stress to the metal powder in a closed container (encasement) under high temperature, thereby promoting the rearrangement, plastic deformation and diffusion creep of the alloy powder particles until a densified alloy billet is formed. With the help of the early encasement design, hot isostatic pressing production of parts of any shape can be achieved.

[0004] Under high temperature conditions, the diffusion creep effect of fine grain size samples is more prominent due to the large number of grain boundaries. In the face-centered cubic structure, {111} is a close-packed plane with the lowest surface energy, which allows cracks to extend at lower stresses, that is, cracks are easy to propagate at the same time as the <111> The nucleation and continuous expansion of the grain boundaries of adjacent orientations eventually lead to a decrease in the endurance life. During the endurance test at higher temperatures, the cracks extend along the grain boundaries. At this time, appropriate grain coarsening can reduce the total length of the grain boundaries, thereby improving the creep resistance of the alloy. Therefore, increasing the grain size helps to extend the high-temperature endurance life of the alloy.

[0005] At present, the manufacturing process of GH4079 disc rings is to first prepare rods by vacuum induction melting and vacuum consumable remelting, then forge the rods to form cakes, and then machine the cakes to obtain rings. In this process mode, the material utilization rate of the blank is extremely low, only about 30%. In addition, GH4079 alloy is a critical deformation alloy with poor hot working plasticity and a very narrow applicable temperature range for hot working. It is very easy to crack during the hot deformation process, resulting in an extremely low yield rate of only about 20%. In addition, if Figure 5As shown in the figure, during the forging process, there is residual stress in an unstable state inside the blank, which will cause problems such as poor tangential mechanical properties and directional dispersion of mechanical properties of GH4079 disc ring parts, which makes it easy for abnormal grain growth to occur in the subsequent heat treatment process; the circumferential tensile stress of the blank also makes the tangential performance of the disc ring part poor. The extremely low material utilization rate, yield rate and directional dispersion of mechanical properties when forging GH4079 disc ring parts make the production cycle of parts long and the performance stability of parts extremely poor, which seriously hinders the installation and test progress of aircraft engines.

[0006] In addition, according to the mechanical performance requirements of GH4079 disc ring parts for aircraft engines, it can be found that this type of parts requires room temperature mechanical performance indicators while also putting forward higher standards for high temperature endurance performance. In the traditional hot isostatic pressing process, due to the limitations of the initial powder particle size (usually 53μm to 150μm) and the grain size inside the powder, the grains are too small after direct hot isostatic pressing. The grain size of high-temperature alloy parts prepared by the traditional hot isostatic pressing process is often between 6 and 8, which is difficult to meet the high temperature endurance performance requirements of the parts. Summary of the invention

[0007] The purpose of the present invention is to overcome the disadvantages of the prior art and to provide a method for preparing a high-performance GH4079 disc ring component and a disc ring component for an aero-engine.

[0008] In order to achieve the above object, the present invention adopts the following technical solutions:

[0009] A method for preparing a high-performance GH4079 disc ring component comprises the following steps:

[0010] Step 1: Prepare GH4079 spherical powder of 106 μm to 250 μm by a specific method;

[0011] Step 2: Put the GH4079 spherical powder into the prefabricated package and perform degassing and sealing treatment;

[0012] Step 3: performing high temperature heat treatment and hot isostatic pressing treatment on the package in sequence;

[0013] Step 4: Remove the can to obtain the powder metallurgy GH4079 blank;

[0014] Step 5: heat treat the powder metallurgy GH4079 blank to obtain a GH4079 disc ring part.

[0015] Furthermore, the specific method in step 1 is specifically: firstly preparing alloy powder by plasma rotating electrode method, and then subjecting the alloy powder to screening, electrostatic and magnetic separation and impurity removal treatments in sequence.

[0016] Furthermore, the GH4079 spherical powder in step 2 is vacuumed to a degree of ≤1×10 -4 Pa into the prefabricated package.

[0017] Furthermore, the parameters of the high temperature heat treatment in step three are: temperature of 1210° C. to 1230° C., time of 8 h to 16 h, and cooling method of air cooling.

[0018] Furthermore, the parameters of the hot isostatic pressing treatment in step three are: temperature 1180°C to 1220°C, pressure: 130MPa to 160MPa, time 2h to 4h, and the cooling process adopts furnace cooling.

[0019] Furthermore, the density of the powder metallurgy GH4079 billet in step 4 is greater than 99.9%.

[0020] Furthermore, the tensile strength of the GH4079 disc ring in step five is greater than 1400 MPa, the yield strength is greater than 980 MPa, the elongation is greater than 15%, and the cross-sectional shrinkage is greater than 18%.

[0021] Specifically, the room temperature tensile strength of the disc ring parts in radial and chord directions is greater than 1400MPa, the yield strength is greater than 980MPa, the elongation is greater than 15%, and the cross-sectional shrinkage is greater than 18%. In addition, the endurance life of the radial and chordal specimens of the parts at 650°C with a stress of 882MPa is greater than 100h.

[0022] Furthermore, the GH4079 disc ring component has a durability of more than 100 hours when a stress of 882 MPa is applied at 650°C.

[0023] In addition, the present application also provides a disc ring component for an aircraft engine, wherein the disc ring component is prepared based on a method for preparing high-performance GH4079 disc ring components by hot isostatic pressing.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention successfully prepares a product with large grain size and qualified performance that can fully meet the use requirements by accurately controlling the grain size in the initial powder particles and then performing hot isostatic pressing treatment; the method proposed in the present invention can effectively solve the problems of easy cracking of the billet and low yield rate in the existing forging process, and effectively promotes the improvement of the utilization rate of alloy materials and the optimization of the stability of the production process.

[0026] 2. The present invention adopts a high temperature heat treatment process, wherein the high temperature heat treatment temperature is 1210°C to 1230°C (higher than T γ'About 40℃~60℃ and lower than the initial melting temperature of the alloy), which can make the γ' phase completely dissolve back into the γ matrix during high-temperature heat treatment (the γ' phase in the GH4079 alloy begins to dissolve at about 1060℃ and is completely dissolved at about 1167℃), reducing its hindrance to grain boundary migration. In addition, during high-temperature heat treatment, the powder particles only contact each other without relative deformation, and the grain boundaries cannot migrate through the surface of the particles, avoiding excessive coarsening of the grains. Through the coordinated regulation of high-temperature heat treatment temperature and time, a microstructural feature in which only a few grains exist in a powder particle is finally formed.

[0027] 3. The traditional forging process has an extremely low material utilization rate (about 30%) and an extremely low product yield rate (about 20%). However, by adopting the method described in the present invention, only the necessary machining allowance and flaw detection allowance need to be reserved, and the material utilization rate from alloy powder to final product can reach more than 80%.

[0028] 4. The invention increases the grain size, and the increase in grain size can extend the alloy's long-term service life. For engine hot end components such as sealing disks and turbine disks, when the alloy grain size grade is 2 to 5, it is more helpful to achieve the optimal combination of room temperature and high temperature properties of the alloy.

[0029] 5. The compressive stress (130MPa-160MPa) applied in the high temperature and high pressure process of the present invention effectively improves the internal stress distribution of the workpiece (the forged ring has residual tensile stress in the circumferential direction, and the present invention applies compressive stress), effectively avoids cracking and deformation in the process of forming the workpiece and abnormal grain growth in the subsequent heat treatment process, and more importantly, solves the problem of poor tangential mechanical properties and directional discreteness of the mechanical properties of the GH4079 disc ring.

[0030] 6. Compared with forgings, powder metallurgy parts have significant advantages such as strong forming ability, isotropic performance, high material utilization, short production process and good stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying drawings are incorporated in and constitute a part of this specification and, together with the description, serve to explain the principles of the present invention.

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0033] Figure 1 A flow chart of a method for preparing high-performance GH4079 disc ring parts by hot isostatic pressing provided by the present invention;

[0034] Figure 2 The technical solution provided by the present invention is to measure the initial powder internal grain size characteristics before the powder is subjected to high temperature heat treatment;

[0035] Figure 3 The technical solution provided by the present invention is to treat the powder with high temperature heat treatment to determine the internal grain size characteristics of the powder;

[0036] Figure 4 The chordal compressive stress diagram of GH4079 disc ring during blanking obtained by the technical solution provided by the present invention;

[0037] Figure 5 This is the chord tensile stress diagram when the traditional process is used to make the blank;

[0038] Figure 6 The microstructure diagram of the GH4079 disk ring obtained by the technical solution provided by the present invention;

[0039] Figure 7 The microstructure diagram of the forged disk ring obtained by the prior art;

[0040] Figure 8 This is a comparison chart of the endurance life of the GH4079 disc ring parts obtained by the technical solutions provided in Examples 1 to 3 of the present invention and the forged disc ring parts obtained by the prior art at 650°C / 882MPa. DETAILED DESCRIPTION

[0041] Here, exemplary embodiments will be described in detail, and the embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are only examples of devices consistent with some aspects of the present invention as detailed in the appended claims.

[0042] A method for preparing a high performance GH4079 disc ring component, such as Figure 1 As shown, the specific steps include:

[0043] Step 1: Prepare GH4079 spherical powder of 106 μm to 250 μm by a specific method;

[0044] Step 2: Put the GH4079 spherical powder into the prefabricated package and perform degassing and sealing treatment;

[0045] Step 3: performing high temperature heat treatment and hot isostatic pressing treatment on the package in sequence;

[0046] Step 4: Remove the can to obtain the powder metallurgy GH4079 blank;

[0047] Step 5: heat treat the powder metallurgy GH4079 blank to obtain a GH4079 disc ring part.

[0048] Furthermore, the specific method in step 1 is specifically: firstly preparing alloy powder by plasma rotating electrode method, and then subjecting the alloy powder to screening, electrostatic and magnetic separation and impurity removal treatments in sequence.

[0049] Furthermore, the GH4079 spherical powder in step 2 is vacuumed to a degree of ≤1×10 -4 Pa into the prefabricated package.

[0050] Further, the parameters of the high temperature heat treatment in step three are: temperature of 1210°C to 1230°C, time of 8h to 16h, and air cooling. It should be noted that the temperature of the high temperature heat treatment can be adjusted according to actual needs, and the temperature of the high temperature heat treatment can be: 1210°C, 1211°C, 1212°C, 1213°C, 1214°C, 1215°C, 1216°C, 1217°C, 1218°C, 1219°C, 1220°C, 1221°C, 1222°C, 1223°C, 1224°C, 1225°C, 1226°C, 1227°C, 1228°C, 1229°C, 1230°C.

[0051] like Figure 2 and Figure 3 As shown, before high-temperature heat treatment, the powder particles showed multi-grain characteristics, and the average grain size was about 28μm; after high-temperature heat treatment, the grains inside the powder merged and grew under the driving force of the decrease in grain boundary energy, and the average grain size was about 125μm.

[0052] Moreover, during the high-temperature heat treatment process, the original powder particles with a large number and small grain size can promote the rapid merging and growth of the grains under the driving force of the decrease of grain boundary energy, and the higher temperature is also conducive to increasing the element diffusion rate, while the original powder particles with a small number and large grain size have low internal grain boundary density, the driving force of the decrease of grain boundary energy is small, and the rate of grain merging and growth is slow. With the passage of holding time, the number of grains inside the two characteristic powder particles tends to be similar.

[0053] Furthermore, the parameters of the hot isostatic pressing treatment in step three are: temperature 1180°C to 1220°C, pressure: 130MPa to 160MPa, time 2h to 4h, and the cooling process adopts furnace cooling.

[0054] Preferably, it should be noted that the temperature, pressure and time of the hot isostatic pressing treatment can be adjusted according to actual needs. The temperature can be 1180℃, 1185℃, 1190℃, 1195℃, 1200℃, 1205℃, 1210℃, 1215℃, 1220℃; the pressure can be 130MPa, 140MPa, 150MPa, 160MPa; and the time can be 2h, 3h, or 4h.

[0055] like Figure 4 As shown, the GH4079 disc ring blank obtained by the technical solution provided by the present invention is obtained under compressive stress conditions, and the chord direction of the product is subjected to compressive stress; Figure 5 As shown, when the traditional forging process is used to make the blank, the workpiece is subjected to tensile stress in the chord direction.

[0056] Furthermore, the density of the powder metallurgy GH4079 billet in step 4 is greater than 99.9%.

[0057] Furthermore, the tensile strength of the GH4079 disc ring in step five is greater than 1400 MPa, the yield strength is greater than 980 MPa, the elongation is greater than 15%, and the cross-sectional shrinkage is greater than 18%.

[0058] Specifically, the room temperature tensile strength of the disc ring in radial and chord directions is greater than 1400MPa, the yield strength is greater than 980MPa, the elongation is greater than 15%, and the cross-sectional shrinkage is greater than 18%; and the endurance life of the radial and chordal specimens of the workpiece corresponding to a stress of 882MPa applied at 650°C is more than 100h.

[0059] Furthermore, the GH4079 disc ring component has a durability of more than 100 hours when a stress of 882 MPa is applied at 650°C.

[0060] Specifically, radial specimens and chordal specimens were cut from the GH4079 disk ring, and the endurance life of the radial specimens and the chordal specimens corresponding to a stress of 882 MPa applied at 650° C. was more than 100 h.

[0061] like Figure 7 As shown in the figure, the microstructure of the parts made by the traditional forging process has straight grain boundaries and large grain size differences. Since the large-sized grains and small-sized grain areas have different effects on the room temperature and high temperature properties of the alloy, the microstructure with large grain size differences will affect the service performance of the alloy, especially the high temperature endurance life; the parts of the present invention overcome the shortcomings of the traditional forging process, such as Figure 6 As shown, the average grain size of the microstructure of the product of the present invention is about 140 μm, and the grain size grade is 2.5, which can meet the performance requirements.

[0062] In addition, the present application also provides a disc ring component for an aircraft engine, which is prepared based on the above-mentioned method of preparing high-performance GH4079 disc ring components by hot isostatic pressing.

[0063] Among them: the disc ring parts include sealing discs for aircraft engines and turbine discs for aircraft engines.

[0064] In high temperature environment, the diffusion creep effect of fine grain size specimens is more significant due to the large number of grain boundaries. In the face-centered cubic structure, {111} is a close-packed plane with the lowest surface energy, which allows cracks to propagate at lower stresses. In other words, cracks are easy to propagate at the same time as the <111> The nucleation and extension at the grain boundaries of adjacent orientations lead to a decrease in the endurance life. In the endurance test at a higher temperature, the cracks extend along the grain boundaries. At this time, appropriate grain coarsening can reduce the total length of the grain boundaries, thereby improving the creep resistance of the alloy. Therefore, increasing the grain size is beneficial to prolonging the endurance life of the alloy. For the hot end parts of the engine such as sealing disks and turbine disks that require both room temperature and high temperature mechanical properties, when the alloy grain size grade is between 2 and 5 (i.e. 63μm ~ 180μm), it is more conducive to achieving the optimal combination of room temperature and high temperature performance of the alloy.

[0065] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0066] Example 1

[0067] The preparation of a disk ring for an aero-engine specifically comprises the following steps:

[0068] 1) GH4079 alloy powder was prepared by plasma rotating electrode method, and high-quality GH4079 powder with a particle size range of 106μm to 150μm was obtained after screening, electrostatic and magnetic separation.

[0069] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then the powder was loaded into the prefabricated package and degassed and sealed. The vacuum degree was measured to be 5.3×10 -4 Pa;

[0070] 3) The package that has completed step 2 is subjected to high-temperature heat treatment. After measurement, the actual heat treatment temperature is 1220°C and the time is 8 hours. After the heat treatment is completed, it is taken out of the furnace and air-cooled.

[0071] 4) The entire can obtained in step 3 is subjected to hot isostatic pressing. After the hot isostatic pressing, the alloy powder inside the can forms a dense alloy blank under high temperature and high pressure conditions. The density of the alloy blank is measured to be 99.97%;

[0072] The parameters of hot isostatic pressing treatment are as follows: temperature is 1180°C, pressure is 160MPa, time is 4h, and the cooling process adopts furnace cooling;

[0073] 5) removing the jacket from the product obtained in step 4 to obtain a powder metallurgy GH4079 blank;

[0074] 6) The GH4079 disc ring with the jacket removed is heat treated according to the standard heat treatment system to obtain the target sealed disc.

[0075] Example 2

[0076] The preparation of a disk ring for an aero-engine specifically comprises the following steps:

[0077] 1) GH4079 alloy powder was prepared by plasma rotating electrode method, and high-quality GH4079 powder with a particle size range of 150μm to 212μm was obtained after screening, electrostatic and magnetic separation.

[0078] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then the powder was loaded into the prefabricated package and degassed and sealed. The vacuum degree was measured to be 6.2×10 -4 Pa;

[0079] 3) The package that has completed step 2 is subjected to high-temperature heat treatment. After measurement, the actual heat treatment temperature is 1210°C and the time is 12 hours. After the heat treatment is completed, it is taken out of the furnace and air-cooled.

[0080] 4) The entire can obtained in step 3 is subjected to hot isostatic pressing. After the hot isostatic pressing, the alloy powder inside the can forms a dense alloy blank under high temperature and high pressure conditions. The density of the alloy blank is measured to be 99.99%;

[0081] The parameters of hot isostatic pressing treatment are set as follows: temperature is 1220°C, pressure is 130MPa, time is 2h, and the cooling process adopts furnace cooling;

[0082] 5) removing the jacket from the product obtained in step 4 to obtain a powder metallurgy GH4079 blank;

[0083] 6) The GH4079 disc ring with the jacket removed is heat treated according to the standard heat treatment system to obtain the target sealed disc.

[0084] Example 3

[0085] The preparation of a disk ring for an aero-engine specifically comprises the following steps:

[0086] 1) GH4079 alloy powder was prepared by plasma rotating electrode method, and high-quality GH4079 powder with a particle size range of 212μm to 250μm was obtained after screening, electrostatic and magnetic separation.

[0087] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then the powder was loaded into the prefabricated package and degassed and sealed. The vacuum degree was measured to be 3.9×10-4 Pa;

[0088] 3) The package that has completed step 2 is subjected to high-temperature heat treatment. After measurement, the actual heat treatment temperature is 1230°C and the time is 16 hours. After the heat treatment is completed, it is taken out of the furnace and air-cooled.

[0089] 4) The entire can obtained in step 3 is subjected to hot isostatic pressing. After the hot isostatic pressing, the alloy powder inside the can forms a dense alloy blank under high temperature and high pressure conditions. The density of the alloy blank is measured to be 99.98%;

[0090] The parameters of hot isostatic pressing treatment are set as follows: temperature is 1200°C, pressure is 145MPa, time is 3h, and the cooling process adopts furnace cooling;

[0091] 5) removing the jacket from the product obtained in step 4 to obtain a powder metallurgy GH4079 blank;

[0092] 6) The GH4079 disc ring with the jacket removed is heat treated according to the standard heat treatment system to obtain the target sealed disc.

[0093] In addition, the inventors compared the room temperature tensile and 650°C / 882MPa high temperature endurance performance of the GH4079 disc ring component finally prepared by the present invention and the final product of the traditional process (when the endurance life exceeds 100h without breaking, the endurance is increased by 44MPa every 8h until it breaks), and paid special attention to the directional problem of the mechanical properties of the product. The specific test results are shown in Table 1 below:

[0094] Table 1 Performance comparison results of the sealing disk made by the present invention and the sealing disk made by the traditional process

[0095]

[0096]

[0097] The test results in Table 1 show that the mechanical properties of the GH4079 disc ring parts obtained by the present invention are significantly better than those of the disc ring parts prepared by the traditional process. Specifically, the room temperature tensile strength of the GH4079 disc ring parts prepared by the present invention is greater than 1500MPa, the yield strength is greater than 1020MPa, the elongation is greater than 18%, and the cross-sectional shrinkage is greater than 22%. Figure 8 As shown in the figure, there is no directional difference in the high-temperature endurance performance of the parts at 650℃, and the endurance life corresponding to the radial and chordal specimens is more than 100h, that is, the endurance life corresponding to the GH4079 disk ring parts applied with a stress of 882MPa at 650℃ is more than 100h.

[0098] The above description is only a specific embodiment of the present invention, so that those skilled in the art can understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention.

[0099] It should be understood that the present invention is not limited to what has been described above and that various modifications and changes may be made without departing from its scope. The scope of the present invention is limited only by the appended claims.

Claims

1. A method for preparing high-performance GH4079 disc ring parts, characterized in that: The specific steps include: Step 1: Prepare GH4079 spherical powder of 106 μm to 250 μm by a specific method; Step 2: Put the GH4079 spherical powder into the prefabricated package and perform degassing and sealing treatment; Step 3: performing high temperature heat treatment and hot isostatic pressing treatment on the package in sequence; Step 4: Remove the can to obtain the powder metallurgy GH4079 blank; Step 5: heat treat the powder metallurgy GH4079 blank to obtain a GH4079 disc ring part.

2. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The specific method in step 1 is as follows: firstly, alloy powder is prepared by plasma rotating electrode method, and then the alloy powder is subjected to screening, electrostatic and magnetic separation and impurity removal treatments in sequence.

3. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The GH4079 spherical powder in step 2 is vacuumed to a degree of ≤1×10 -4 Pa into the prefabricated package.

4. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The parameters of the high temperature heat treatment in step three are: temperature of 1210° C. to 1230° C., time of 8 h to 16 h, and cooling method of air cooling.

5. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The parameters of the hot isostatic pressing treatment in step three are: temperature 1180° C. to 1220° C., pressure: 130 MPa to 160 MPa, time 2 h to 4 h, and furnace cooling is used in the cooling process.

6. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The density of the powder metallurgy GH4079 billet in step 4 is greater than 99.9%.

7. A method for preparing a high-performance GH4079 disc ring according to claim 1, characterized in that: The tensile strength of the GH4079 disc ring in step 5 is greater than 1400 MPa, the yield strength is greater than 980 MPa, the elongation is greater than 15%, and the cross-sectional shrinkage is greater than 18%.

8. A method for preparing a high-performance GH4079 disc ring according to claim 7, characterized in that: The GH4079 disk ring component has a durability of more than 100 hours when a stress of 882 MPa is applied at 650°C.

9. A disc ring for an aircraft engine, characterized in that: The disc ring component is prepared based on the method for preparing high-performance GH4079 disc ring components by hot isostatic pressing as described in any one of claims 1 to 8.

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