A method for preparing high-performance GH4079 disc ring parts and disc ring parts for aircraft engines

Abstract

The present invention belongs to the field of powder metallurgy technology and relates to a method for preparing high-performance GH4079 disk ring parts and disk ring parts for aircraft engines. First, a specific method is used to prepare GH4079 spherical powder of 106μm to 250μm; then the GH4079 spherical powder is placed in a prefabricated sleeve and degassed and sealed; then the sleeve is subjected to high-temperature heat treatment and hot isostatic pressing treatment in sequence; finally, the sleeve is removed to obtain a powder metallurgy GH4079 billet; the powder metallurgy GH4079 billet is heat treated to obtain a GH4079 disk ring part. The method provided by the present invention can effectively solve the problems of billet cracking and low yield in the existing forging process, thereby promoting the improvement of alloy material utilization and the stability of the production process.

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 aero-engine. Background Art

[0002] GH4079 alloy is a Ni-Co-Cr-based precipitation-hardening wrought alloy with a long-term operating temperature range of 750°C to 800°C. Based on GH4742, this alloy increases the aluminum, titanium, and niobium contents to promote the formation of a larger γ' phase, with ω (γ') accounting for approximately 45% of the alloy. This gives GH4079 alloy higher room-temperature strength and high-temperature performance, as well as excellent structural stability and corrosion resistance, making it ideal for manufacturing components such as aircraft engine turbine disks and sealing disks.

[0003] The hot isostatic pressing (HIP) process uses argon as the transmission medium. Under high temperature, compressive stress is applied to metal powder within a sealed container (encapsulation), driving the alloy powder particles to rearrange, plastically deform, and undergo diffusion creep until a densified alloy billet is formed. With the help of pre-engineered encapsulation design, HIP production of parts of any shape is possible.

[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} as a close-packed plane has the lowest surface energy, which allows cracks to expand at lower stresses, that is, cracks are easy to propagate at the same time as the surface. <111> Nucleation and expansion occur at grain boundaries with adjacent orientations, ultimately reducing the creep life. During endurance tests at higher temperatures, cracks extend along grain boundaries. At this point, appropriate grain coarsening can reduce the total length of the grain boundaries, thereby increasing the alloy's creep resistance. Therefore, increasing grain size helps extend the alloy's high-temperature creep life.

[0005] Currently, the manufacturing process of GH4079 disc rings is to first prepare rods using vacuum induction melting and vacuum consumable remelting, then forge the rods to form cakes, and then machine the cakes to obtain rings. Under 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 an extremely narrow 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, unstable residual stresses exist within the blank. This can lead to poor tangential mechanical properties and directional dispersion of the mechanical properties of the GH4079 disc ring. This can easily cause abnormal grain growth during subsequent heat treatment. The presence of tensile stress in the circumferential direction of the blank also leads to poor tangential performance of the disc ring. The extremely low material utilization and yield rate, as well as the directional dispersion of mechanical properties during the forging of the GH4079 disc ring, result in a long production cycle and extremely poor performance stability, seriously hindering the installation and test evaluation of aircraft engines.

[0006] Furthermore, the mechanical performance requirements for GH4079 disk rings used in aircraft engines indicate that these components, while demanding room-temperature mechanical performance indicators, also place higher demands on high-temperature durability. However, in traditional hot isostatic pressing (HIP), due to limitations in initial powder particle size (typically 53 μm to 150 μm) and the size of the internal grains, the grain size of high-temperature alloy components produced using direct HIP is often too fine. This often results in a grain size of 6 to 8, making it difficult to meet the high-temperature durability requirements. Summary of the Invention

[0007] The purpose of the present invention is to overcome the shortcomings of the above-mentioned 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 with a size of 106 μm to 250 μm using a specific method;

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

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

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

[0014] Step 5: heat-treating the powder metallurgy GH4079 blank to obtain a GH4079 disk ring part.

[0015] Furthermore, the specific method in step 1 is specifically 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.

[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: 130 MPa to 160 MPa, time 2 h to 4 h, 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 component 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 components in both the radial and chordal directions exceeds 1400 MPa, the yield strength exceeds 980 MPa, the elongation exceeds 15%, and the reduction of area exceeds 18%. Furthermore, the endurance life of both radial and chordal specimens exceeds 100 hours when subjected to a stress of 882 MPa at 650°C.

[0022] Furthermore, the GH4079 disk ring component has a durability life of more than 100 h when subjected to a stress of 882 MPa at 650°C.

[0023] In addition, the present application also provides a disc ring component for an aircraft engine, which 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 produces parts with large grain size, qualified performance, and fully meeting the requirements of use by precisely controlling the grain size of the initial powder particles and then performing hot isostatic pressing. 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 ℃ ~ 1230 ℃ (higher than T γ'The high-temperature heat treatment temperature (approximately 40°C to 60°C, and below the alloy's initial melting point) allows the γ' phase to completely dissolve back into the γ matrix during high-temperature heat treatment (the γ' phase in GH4079 alloy begins to dissolve at approximately 1060°C and is completely dissolved at approximately 1167°C), reducing its hindrance to grain boundary migration. Furthermore, during high-temperature heat treatment, the powder particles remain in contact with each other without relative deformation, preventing grain boundaries from migrating across the particle surface and preventing excessive grain coarsening. By carefully controlling the high-temperature heat treatment temperature and duration, a microstructure characterized by the presence of only a few grains within a single powder particle is ultimately achieved.

[0027] 3. The traditional forging process has an extremely low material utilization rate (about 30%) and an extremely low part yield rate (about 20%). However, the method described in this invention only requires the necessary machining allowances and flaw detection allowances to be reserved, and the material utilization rate from alloy powder to final part can reach over 80%.

[0028] 4. This invention increases the grain size, which can extend the alloy's lifespan. For engine hot-end components like sealing disks and turbine disks, an alloy with a grain size of 2-5 helps achieve the optimal combination of room-temperature and high-temperature performance.

[0029] 5. The compressive stress (130 MPa to 160 MPa) applied during the high-temperature, high-pressure process described in the present invention effectively improves the stress distribution within the component (forged rings exhibit residual tensile stress in the circumferential direction, while the present invention applies compressive stress). This effectively avoids problems such as cracking and deformation during the component forming process and abnormal grain growth during subsequent heat treatment. More importantly, it solves the problems of poor tangential mechanical properties and directional dispersion of the mechanical properties of GH4079 disc rings.

[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 invention.

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 the 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 internal grain size characteristics of the initial powder 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 the GH4079 disc ring obtained by the technical solution provided by the present invention during blanking;

[0037] Figure 5 This is the chord tensile stress diagram when the blank is made using the traditional process;

[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 obtained by the technical solutions provided in Examples 1 to 3 of the present invention and the forged disc ring obtained by the prior art at 650°C / 882 MPa. 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 high performance GH4079 disc ring parts, such as Figure 1 As shown, the specific steps include:

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

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

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

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

[0047] Step 5: heat-treating the powder metallurgy GH4079 blank to obtain a GH4079 disk ring part.

[0048] Furthermore, the specific method in step 1 is specifically 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.

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

[0050] Furthermore, the parameters of the high-temperature heat treatment in step 3 are: temperature of 1210°C to 1230°C, time of 8 hours to 16 hours, and cooling method of 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 in the figure, before high-temperature heat treatment, the powder particles showed multi-grain characteristics, with an average grain size of about 28 μm; after high-temperature heat treatment, the grains inside the powder merged and grew under the driving force of the decrease in grain boundary energy, with an average grain size of about 125 μm.

[0052] Furthermore, during high-temperature heat treatment, the grains within the original powder particles with a large number and small grain size can rapidly coalesce and grow, driven by the decrease in grain boundary energy. Higher temperatures also help increase the element diffusion rate. In contrast, the original powder particles with a small number and larger grain size have a low grain boundary density, resulting in a smaller driving force for the decrease in grain boundary energy and slower grain coalescence and growth. Over time, the grain numbers within the two characteristic powder particles approach a similar value.

[0053] Furthermore, 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 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 130 MPa, 140 MPa, 150 MPa, 160 MPa; and the time can be 2 h, 3 h, or 4 h.

[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 in the figure, 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 component 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 component in the radial and chord directions 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%. Moreover, the endurance life of the radial and chord specimens of the component exceeds 100 h when subjected to a stress of 882 MPa at 650°C.

[0059] Furthermore, the GH4079 disk ring component has a durability life of more than 100 h when subjected to a stress of 882 MPa at 650°C.

[0060] Specifically, radial specimens and chordal specimens were cut from the GH4079 disk ring component. The radial specimens and chordal specimens had endurance lives exceeding 100 h when subjected to a stress of 882 MPa at 650°C.

[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 large-sized grains and small-sized grain areas have different effects on the room temperature and high temperature properties of the alloy, this microstructure with large grain size differences will affect the service performance of the alloy, especially the high temperature endurance life. The parts made by 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: disc ring parts include sealing discs for aircraft engines and turbine discs for aircraft engines.

[0064] Under 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> Nucleation and extension occur at grain boundaries with adjacent orientations, resulting in a decrease in the alloy's creep life. During endurance testing at higher temperatures, cracks propagate along grain boundaries. Appropriate grain coarsening can reduce the total length of grain boundaries, thereby improving the alloy's creep resistance. Therefore, increasing grain size is beneficial for extending the alloy's creep life. For engine hot-end components such as sealing disks and turbine disks, which require both room-temperature and high-temperature mechanical properties, an alloy with a grain size of 2 to 5 (i.e., 63 μm to 180 μm) is more conducive to achieving the optimal combination of room-temperature and high-temperature performance.

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

[0066] Example 1

[0067] The preparation of a disk ring component for an aerospace engine specifically includes the following steps:

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

[0069] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then put it into the prefabricated package and perform degassing and sealing treatment;

[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 h. 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 hot isostatic pressing, the alloy powder inside the can is formed into a dense alloy billet under high temperature and high pressure conditions. The density of the alloy billet is measured to be 99.97%;

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

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

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

[0075] Example 2

[0076] The preparation of a disk ring component for an aerospace engine specifically includes the following steps:

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

[0078] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then put it into the prefabricated package and perform degassing and sealing treatment;

[0079] 3) The package that has completed step 2 is subjected to high-temperature heat treatment. The actual heat treatment temperature is measured to be 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 hot isostatic pressing, the alloy powder inside the can is formed into a dense alloy billet under high temperature and high pressure conditions. The density of the alloy billet is measured to be 99.99%;

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

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

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

[0084] Example 3

[0085] The preparation of a disk ring component for an aerospace engine specifically includes the following steps:

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

[0087] 2) The alloy powder prepared in step 1) is placed in a high vacuum of ≤1×10 -4 Pa, and then put it into the prefabricated package and perform degassing and sealing treatment;

[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 hot isostatic pressing, the alloy powder inside the can is formed into a dense alloy billet under high temperature and high pressure conditions. The density of the alloy billet is measured to be 99.98%;

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

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

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

[0093] In addition, the inventors compared the room temperature tensile strength and 650°C / 882 MPa high-temperature endurance performance of the GH4079 disc ring parts produced by the present invention and the parts produced by the traditional process (in the test, if the endurance life exceeds 100 hours without breaking, the endurance is increased by 44 MPa every 8 hours until it breaks). In particular, the inventors paid attention to the directional issues of the mechanical properties of the parts. The specific test results are shown in Table 1 below:

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

[0095]

[0096] The test results in Table 1 show that the mechanical properties of the GH4079 disc ring parts obtained by the present invention are significantly superior to those prepared by conventional processes. Specifically, the room temperature tensile strength of the GH4079 disc ring parts prepared by the present invention is greater than 1500 MPa, the yield strength is greater than 1020 MPa, the elongation is greater than 18%, and the cross-sectional shrinkage is greater than 22%. Figure 8As shown in the figure, there is no directional difference in the high-temperature endurance performance of the parts at 650 ℃. The endurance life of the radial and chordal specimens exceeds 100 h. That is, the endurance life of the GH4079 disk ring parts subjected to a stress of 882 MPa at 650 ℃ exceeds 100 h.

[0097] The foregoing description is intended only to provide specific embodiments of the present invention, which will enable those skilled in the art to understand and implement the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention.

[0098] It should be understood that the present invention is not limited to the above description and that various modifications and changes may be made without departing from the scope thereof. 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 with a size of 106 μm to 250 μm using a specific method; Step 2: Place GH4079 spherical powder into a prefabricated package and perform degassing and sealing treatment; Step 3: Perform high temperature heat treatment and hot isostatic pressing on the package in sequence; Step 4: Remove the can to obtain the powder metallurgy GH4079 blank; Step 5: heat treating the powder metallurgy GH4079 blank to obtain a GH4079 disc ring part; 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 to remove impurities in sequence; The GH4079 spherical powder in step 2 is vacuumed to a degree of ≤1×10 -4 Pa under the conditions of the prefabricated package; The parameters of the high temperature heat treatment in step 3 are: temperature of 1210°C to 1230°C, time of 8 h to 16 h, and cooling method of air cooling; The parameters of the hot isostatic pressing treatment in step 3 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.

2. 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%.

3. The 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%.

4. A method for preparing a high-performance GH4079 disc ring according to claim 3, characterized in that: The GH4079 disk ring component has a durability of more than 100 h when a stress of 882 MPa is applied at 650°C.

5. 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 according to any one of claims 1 to 4.

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