Method for heat treatment of a difficult-to-deform superalloy and its application in a turbine disk

Abstract

The application discloses a heat treatment method of a difficult-to-deform high-temperature alloy in the field of high-temperature alloy materials and application of the heat treatment method in a turbine disc, and steps of the heat treatment method comprise the following steps: taking the difficult-to-deform high-temperature alloy, determining a re-dissolution temperature T0 of a gamma prime phase, and heat treating the alloy at a first solid solution temperature T1 for 0.5-8 hours, wherein the first solid solution temperature T1 is 1-20 DEG C higher than the re-dissolution temperature T0; cooling the alloy to a second solid solution temperature T2 at a rate of not more than 10 DEG C / min, wherein the second solid solution temperature T2 is 5-100 DEG C lower than the re-dissolution temperature T0; heat treating the alloy at the second solid solution temperature T2 for 1 min-4 hours; and then performing normal aging heat treatment of the alloy. Through the heat treatment method of two-stage solid solution combined with intermediate slow cooling, sawtooth grain boundaries and gamma prime phases with multi-size distribution are finally obtained, and the plasticity and creep endurance of the alloy can be greatly improved without losing the high-temperature strength of the alloy.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of high-temperature alloy materials, in particular to a heat treatment method of a difficult-to-deform high-temperature alloy and application thereof in a turbine disc. BACKGROUND

[0002] An aero-engine is composed of a cold end system and a hot end system. The cold end system is mainly composed of a fan, a low-pressure compressor and a high-pressure compressor front-end component, and the main function is to introduce air and compress it. The hot end system is mainly composed of a high-pressure compressor rear-end component, a combustor, a high-pressure turbine, a low-pressure turbine and a nozzle, and the main function is to burn gas and discharge it. Since the hot end components of the aero-engine work for a long time under high temperature, high pressure and high load, the materials need to have excellent high-temperature performance, so high-temperature alloys become the first choice. The turbine disc is one of the core components of the aero-engine, and its function is to convert the gas in the combustor into mechanical power to drive the aero-engine to run at high speed. Therefore, the high-temperature alloy for preparing the turbine disc should have excellent yield strength, good creep performance, and good plasticity and impact toughness. It is reported that for every 25℃ increase in the service temperature of the turbine disc in the aero-engine, the service life of the aero-engine is extended by 3 times. Therefore, improving the temperature resistance of the turbine disc material is crucial to the service life of the aero-engine.

[0003] With the continuous exploration of the turbine disc material in the aero-engine, people have devoted themselves to the research and development of high-temperature alloys for turbine discs with higher service temperature. Researchers have developed a series of high-performance deformed high-temperature alloys for turbine discs by adding refractory elements or increasing the volume fraction of γ' phase to improve the temperature resistance of high-temperature alloys, which include GH4720Li alloy, GH4065A alloy and FGH4096 alloy that can be used at 700℃ for a long time, GH4251 alloy, GH4068 alloy, FGH4097 alloy and FGH4098 alloy that can be used at 750℃ for a long time, GH4151 alloy and GH4175 alloy that can be used at 800℃ for a long time, and GH4975 alloy that can be used at 850℃ for a long time. Due to the high degree of alloying and high volume fraction of precipitated phases in these alloys, they are collectively referred to as difficult-to-deform high-temperature alloys. Taking the GH4975 alloy with the highest temperature resistance as an example, the total content of solid solution strengthening elements (Cr+Mo+W+Co) in the alloy is more than 35wt%, and the added W content is as high as 10wt%. The total amount of γ' phase forming elements (Al+Ti+Nb) is 9.0wt%, and the volume fraction of γ' phase in the aging state is 64%, which is close to the level of some cast high-temperature alloys. In addition, the carbon content in the alloy is more than 0.1wt%, which is much higher than that of other high-temperature alloys.

[0004] However, increasing the degree of alloying and the volume fraction of the γ′ phase brings serious difficulties to the deformation and blanking of such alloys. During preparation, this manifests mainly as severe solidification segregation, large precipitate size, and solidification cracking. During blanking, the main problems are high deformation resistance, narrow hot working window, and poor thermoplasticity. Therefore, improving the heat resistance of high-temperature alloys by further increasing the content of alloying elements and the volume fraction of the γ′ phase will be limited.

[0005] Currently, many researchers are working to improve the temperature resistance of high-temperature alloys used in turbine disks by optimizing alloy composition, altering preparation processes, and adjusting heat treatment regimes to change the microstructure of the alloys. For example, the standard heat treatment regime for high-temperature alloys is "solution treatment + aging," which is suitable for alloys with conventional performance requirements. However, for difficult-to-deform high-temperature alloys, it cannot improve the tensile properties and creep resistance of the alloy without sacrificing its high-temperature strength. Summary of the Invention

[0006] The purpose of this invention is to provide a heat treatment method for difficult-to-deform high-temperature alloys and its application in turbine disks. This method solves the problem that existing heat treatment processes for difficult-to-deform high-temperature alloys cannot improve the tensile properties and creep resistance of the alloys without sacrificing their high-temperature strength.

[0007] The present invention achieves the above objectives through the following technical solutions:

[0008] A heat treatment method for a difficult-to-deform high-temperature alloy, the method comprising the following steps:

[0009] S1, single solution treatment

[0010] Take the high-temperature alloy that is difficult to deform and determine the dissolution temperature T0 of its γ′ phase. Hold the alloy at the first solid solution temperature T1 for 0.5-8 hours. The first solid solution temperature T1 is 1-20℃ higher than the dissolution temperature T0.

[0011] S2, Slow Cooling

[0012] The alloy is cooled to a second solution temperature T2 at a rate not exceeding 10°C / min, the second solution temperature T2 being 5-100°C lower than the remelting temperature T0.

[0013] S3, Secondary Solid Solution

[0014] The alloy was held at the second solution temperature T2 for 1 min to 4 h.

[0015] S4. Timeliness.

[0016] A further improvement is that the difficult-to-deform high-temperature alloy is one of the following: GH4720Li alloy, GH4065A alloy, FGH4096 alloy, GH4251 alloy, GH4068 alloy, FGH4097 alloy, FGH4098 alloy, GH4151 alloy, GH4175 alloy, GH4975 alloy, GH4099 alloy, GH4079 alloy, GH4096 alloy, GH586 alloy, GH742 alloy, or GH864 alloy.

[0017] A further improvement is that, in step S2, the alloy is cooled to the second solution temperature T2 at a rate of 1.6 °C / min.

[0018] A further improvement is that, in step S3, the alloy is held at the second solution temperature T2 for 30 minutes.

[0019] A further improvement is that, in step S3, static tensile stress is applied to the alloy during the heat preservation process.

[0020] A further improvement is that the stress is 5%-15% of the alloy's yield strength at the holding temperature.

[0021] A further improvement is that, in step S4, the aging refers to a two-stage aging treatment after the alloy is air-cooled to room temperature.

[0022] A further improvement is that the two aging treatments are as follows: the first stage involves holding the temperature at 950℃ for 12 hours and then air-cooling it to room temperature; the second stage involves holding the temperature at 850℃ for 16 hours and then air-cooling it to room temperature.

[0023] The present invention also provides a difficult-to-deform high-temperature alloy, which is obtained by the heat treatment method described above.

[0024] This invention provides an application of the aforementioned difficult-to-deform high-temperature alloy in turbine disks, wherein the application is to use the difficult-to-deform high-temperature alloy as a material for manufacturing turbine disks.

[0025] The beneficial effects of this invention are as follows:

[0026] (1) The present invention uses a two-stage solid solution combined with intermediate slow cooling heat treatment method to induce the precipitation of γ′ phase at the grain boundary. The formation, growth and subsequent migration of this γ′ phase will induce the straight grain boundary to bend, and finally obtain serrated grain boundary and γ′ phase with multiple sizes. Compared with standard heat treatment, this process can significantly improve the tensile properties and creep endurance of the alloy without losing the high temperature strength of the alloy.

[0027] (2) In a preferred embodiment, the present invention also applies a stress field during the secondary solid solution process to introduce a controllable dislocation density, providing more sites for heterogeneous nucleation of precipitated phases during the subsequent aging process, while also helping to optimize the grain boundary morphology, and ultimately further improving the creep life of the alloy. Attached Figure Description

[0028] Figure 1 The images show the grain boundary morphology of GH4975 alloy after solution treatment and cooling to 1170℃ at different slow cooling rates. Among them, (a) shows the grain boundary morphology after cooling to 1170℃ at 1.6℃ / min, (b) shows the grain boundary morphology after cooling to 1170℃ at 4.6℃ / min, (c) shows the grain boundary morphology after cooling to 1170℃ at 5℃ / min, (d) shows the grain boundary morphology after cooling to 1170℃ at 6.4℃ / min, and (e) shows the grain boundary morphology after cooling to 1170℃ at 5℃ / min.

[0029] Figure 2 The images show the grain boundary morphology of GH4975 alloy after cooling to different temperatures and holding times at a cooling rate of 1.6℃ / min. (a) shows the grain boundary morphology of GH4975 alloy after cooling to 1160℃ at a cooling rate of 1.6℃ / min and holding for 0 min; (b) shows the grain boundary morphology of GH4975 alloy after cooling to 1160℃ at a cooling rate of 1.6℃ / min and holding for 10 min; (c) shows the grain boundary morphology of GH4975 alloy after cooling to 1160℃ at a cooling rate of 1.6℃ / min and holding for 20 min; and (d) shows the grain boundary morphology of GH4975 alloy after cooling to 1160℃ at a cooling rate of 1.6℃ / min and holding for 20 min. (e) shows the grain boundary morphology of GH4975 alloy after cooling to 1160℃ and holding for 30 min at a cooling rate of 1.6℃ / min and holding for 0 min; (f) shows the grain boundary morphology of GH4975 alloy after cooling to 1170℃ and holding for 10 min at a cooling rate of 1.6℃ / min; (g) shows the grain boundary morphology of GH4975 alloy after cooling to 1170℃ and holding for 20 min at a cooling rate of 1.6℃ / min; and (h) shows the grain boundary morphology of GH4975 alloy after cooling to 1170℃ and holding for 30 min at a cooling rate of 1.6℃ / min.

[0030] Figure 3The images show the microstructure of GH4975 alloy after standard heat treatment (a1-a3) and the heat treatment of the present invention (b1-b3). In the images, (a1) is the low-magnification microstructure of GH4975 alloy after standard heat treatment, (a2) is the grain boundary morphology of GH4975 alloy after standard heat treatment, (a3) ​​is the morphology of precipitated phases of GH4975 alloy after standard heat treatment, (b1) is the low-magnification microstructure of GH4975 alloy after heat treatment of the present invention, (b2) is the grain boundary morphology of GH4975 alloy after heat treatment of the present invention, and (b3) is the morphology of precipitated phases of GH4975 alloy after heat treatment of the present invention.

[0031] Figure 4 The graphs show the creep performance of GH4975 alloy after standard heat treatment (a1-a3) and the heat treatment of the present invention (b1-b3). Detailed Implementation

[0032] The present application will now be described in further detail with reference to the accompanying drawings. It should be noted that the following specific embodiments are only used to further illustrate the present application and should not be construed as limiting the scope of protection of the present application. Those skilled in the art can make some non-essential improvements and adjustments to the present application based on the above application content.

[0033] I. Heat Treatment Objects

[0034] This experiment takes GH4975 alloy, which currently has the highest heat resistance, as an example. The material used is GH4975 alloy after deformation (after billeting or forging). Its microstructure characteristics are that the grains are all fine equiaxed grains, and large-sized irregularly shaped γ′ phases are distributed in the grains and at the grain boundaries. Fine, uniform, and regularly sized (round or square) secondary γ′ phases are distributed in the grains.

[0035] II. Determining the remelting temperature

[0036] Taking GH4975 alloy, through DSC experimental testing and JMat Pro software calculation and analysis, the melting temperature T0 of the γ′ phase in this alloy is between 1200-1210℃, approximately 1204℃.

[0037] III. Analysis of Slow Cooling Rate

[0038] The standard heat treatment regime for GH4975 alloy is "solution treatment + aging", namely 1210℃ / 6h / AC + 950℃ / 12h / AC + 850℃ / 16h / AC. First, six GH4975 alloy samples, each 10*10*10mm in size, were taken. After surface polishing, the samples were placed in a vacuum heat treatment furnace. The samples were heated to 1210℃ at a rate of 10℃ / min and held for 6 hours. Then, the samples were cooled to 1170℃ at cooling rates of 1.6℃ / min, 4.6℃ / min, 5℃ / min, 6.4℃ / min, and 10℃ / min, respectively. The furnace was then opened, and the samples were air-cooled. After cooling, the samples were polished. The grain boundary morphology of the alloy at different cooling rates is shown below. Figure 1 As shown in the figure, the grain boundaries exhibit varying degrees of bending at different cooling rates. The smaller the cooling rate, the more pronounced the grain boundary bending, with the slow cooling rate of 1.6℃ / min showing the most significant effect.

[0039] IV. Analysis of Secondary Solution Treatment Temperature and Duration

[0040] Eight deformed GH4975 alloy samples were taken, with dimensions as shown above. The samples were heated in the furnace to 1210℃ at a heating rate of 10℃ / min and held for 6 hours. They were then cooled to 1160℃ and 1170℃ at a cooling rate of 1.6℃ / min, and held at 1160℃ and 1170℃ for 0 min, 10 min, 20 min, and 30 min, respectively. After holding, the samples were removed from the furnace and air-cooled. After cooling, the samples were polished and then subjected to microstructural observation. The grain boundary morphology under each heat treatment condition is shown below. Figure 2 As shown. By Figure 2 It can be seen that, when the slow cooling rate is constant, the lower the second-stage solution temperature, the smaller the wavelength of grain boundary bending, and vice versa; the longer the holding time at the second-stage solution temperature, the larger the amplitude of grain boundary bending, and vice versa. Therefore, holding at 1160℃ for 30 minutes for the second solution stage yields the most outstanding effect.

[0041] V. Determine the final test plan

[0042] A heat treatment method for GH4975 alloy, the method comprising the following steps:

[0043] S1. One-time solution treatment: Hold GH4975 alloy at 1210℃ for 6 hours;

[0044] S2. Slow cooling: Cool the GH4975 alloy to 1160℃ at a rate of 1.6℃ / min;

[0045] S3, Secondary solution treatment: Hold GH4975 alloy at 1160℃ for 30 minutes;

[0046] S4. Aging: After the GH4975 alloy is air-cooled to room temperature, it is subjected to two-stage aging treatment. The first stage is held at 950℃ for 12 hours and then air-cooled to room temperature. The second stage is held at 850℃ for 16 hours and then air-cooled to room temperature.

[0047] VI. Performance Test Comparison

[0048] The deformed GH4975 alloy was machined into multiple standard tensile and creep specimens. These specimens underwent both standard heat treatment (SHT) and special heat treatment (HT2). The standard heat treatment process involved holding at 1210℃ for 6 hours, air cooling to room temperature, followed by a two-stage aging process: the first stage involved holding at 950℃ for 12 hours followed by air cooling to room temperature, and the second stage involved holding at 850℃ for 6 hours followed by air cooling to room temperature. The special heat treatment process was described in section "V" above. The heat-treated GH4975 alloy specimens were then subjected to the following tests:

[0049] (1) Microstructure

[0050] After undergoing both standard heat treatment (SHT) and special heat treatment (HT2), the microstructure of GH4975 alloy is as follows: Figure 3 As shown in the figure, the microstructure after standard heat treatment is characterized by straight grain boundaries, uniform precipitates, and a single size and morphology distribution; the microstructure after special heat treatment is characterized by bent grain boundaries, and the precipitates exhibit a multimodal distribution, with large-sized, irregularly shaped γ′ phases distributed within the grains and at the grain boundaries, and small, regularly shaped secondary γ′ phases dispersed within the grains.

[0051] (2) Tensile properties

[0052] Tensile tests were conducted on the samples after standard heat treatment (SHT) and special heat treatment (HT2) at 20℃, 650℃, 750℃ and 850℃, respectively. The results are shown in Table 1 below:

[0053] Table 1: Tensile properties of alloys under two heat treatment conditions

[0054]

[0055] As shown in Table 1, the yield strength of HT2 alloy is higher than or within the range of the alloy's yield strength when stretched at 20℃-850℃, but the elongation is significantly higher than that of SHT alloy and the highest data of the literature reported in the corresponding conditions.

[0056] (3) Creep durability

[0057] Creep tests were conducted on creep samples after standard heat treatment (SHT) and special heat treatment (HT2) at 850℃ / 412MPa. The creep curves are shown below.Figure 4 As shown, the creep life of the SHT alloy under these conditions reaches 148 hours, while that of the HT2 alloy reaches 300 hours, twice that of the SHT alloy. Furthermore, current literature reports a maximum creep life of 100 hours for this alloy under these conditions, making the creep life of the HT2 alloy three times the highest reported data.

[0058] VII. Parallel Experiments

[0059] Based on the final experimental scheme described in section "5" above, the alloy object and various process parameters were adjusted to obtain the following heat treatment process:

[0060] (1) A heat treatment method for GH4151 alloy, the method comprising the following steps:

[0061] S1. First solution treatment: The GH4151 alloy was held at 1170℃ for 3 hours (based on DSC experimental testing and JMat Pro software calculation and analysis, the remelting temperature T0 of the γ′ phase in the GH4151 alloy is 1160℃).

[0062] S2. Slow cooling: Cool the GH4151 alloy to 1140℃ at a rate of 2℃ / min;

[0063] S3, Secondary solution treatment: Hold GH4151 alloy at 1140℃ for 20 minutes;

[0064] S4. Aging: After air cooling the GH4151 alloy to room temperature, it is subjected to two-stage aging treatment. The first stage is held at 830℃ for 6 hours and then air cooled to room temperature. The second stage is held at 760℃ for 6 hours and then air cooled to room temperature.

[0065] After comparing the same performance tests as described above ("six"), it was found that the above heat treatment method significantly improves tensile properties and creep rupture properties compared to the standard heat treatment process of GH4151 alloy.

[0066] VIII. Experimental Optimization and Exploration

[0067] Based on the aforementioned final experimental scheme ("five"), its optimization direction was explored, revealing that applying a stress field during the secondary solution treatment process affects the creep life of the alloy. Accordingly, based on a special heat treatment (HT2), the following adjusted heat treatment process is studied:

[0068] (1) A heat treatment method for GH4975 alloy, the method comprising the following steps:

[0069] S1. One-time solution treatment: Hold GH4975 alloy at 1210℃ for 6 hours;

[0070] S2. Slow cooling: Cool the GH4975 alloy to 1160℃ at a rate of 1.6℃ / min;

[0071] S3, Secondary solution treatment: The GH4975 alloy was held at 1160℃ for 30 minutes. During the holding process, static tensile stress was applied to the alloy through the fixture of the thermomechanical property testing machine. The stress was 5% of the yield strength of the alloy at the holding temperature (the yield strength at 1160℃ was reduced to 22MPa, and the stress was 1.1MPa).

[0072] S4. Aging: After the GH4975 alloy is air-cooled to room temperature, it is subjected to two-stage aging treatment. The first stage is held at 950℃ for 12 hours and then air-cooled to room temperature. The second stage is held at 850℃ for 16 hours and then air-cooled to room temperature.

[0073] (2) A heat treatment method for GH4975 alloy, the method comprising the following steps:

[0074] S1. One-time solution treatment: Hold GH4975 alloy at 1210℃ for 6 hours;

[0075] S2. Slow cooling: Cool the GH4975 alloy to 1160℃ at a rate of 1.6℃ / min;

[0076] S3, Secondary solution treatment: The GH4975 alloy was held at 1160℃ for 30 minutes. During the holding process, static tensile stress was applied to the alloy through the fixture of the thermomechanical property testing machine. The stress was 10% of the yield strength of the alloy at the holding temperature (the yield strength at 1160℃ drops to 22MPa, so the stress was 2.2MPa).

[0077] S4. Aging: After the GH4975 alloy is air-cooled to room temperature, it is subjected to two-stage aging treatment. The first stage is held at 950℃ for 12 hours and then air-cooled to room temperature. The second stage is held at 850℃ for 16 hours and then air-cooled to room temperature.

[0078] (3) A heat treatment method for GH4975 alloy, the method comprising the following steps:

[0079] S1. One-time solution treatment: Hold GH4975 alloy at 1210℃ for 6 hours;

[0080] S2. Slow cooling: Cool the GH4975 alloy to 1160℃ at a rate of 1.6℃ / min;

[0081] S3. Secondary solution treatment: The GH4975 alloy was held at 1160℃ for 30 minutes. During the holding process, static tensile stress was applied to the alloy through the fixture of the thermomechanical property testing machine. The stress was 15% of the yield strength of the alloy at the holding temperature (the yield strength at 1160℃ drops to 22MPa, and the stress is 3.3MPa).

[0082] S4. Aging: After the GH4975 alloy is air-cooled to room temperature, it is subjected to two-stage aging treatment. The first stage is held at 950℃ for 12 hours and then air-cooled to room temperature. The second stage is held at 850℃ for 16 hours and then air-cooled to room temperature.

[0083] Using the same testing method as in section "VI" above, creep tests were conducted on the three processed creep samples at 850℃ / 412MPa. It was found that the magnitude of the applied static tensile stress had a significant impact on the creep life. Specifically, the creep life was 305 hours for the heat treatment process applying 5% of the yield strength, 355 hours for the process applying 10% of the yield strength, and 270 hours for the process applying 15% of the yield strength. This indicates that only by applying 10% stress can the creep life be significantly improved; applying 5% of the yield strength has virtually no promoting effect, while applying 15% of the yield strength actually reduces the creep life, possibly due to excessive stress.

[0084] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. A heat treatment method for a difficult-to-deform high-temperature alloy, characterized in that, The method induces the precipitation of a γ′ phase at grain boundaries through a two-stage solid solution combined with intermediate slow cooling. The formation, growth, and subsequent migration of the γ′ phase induce the straight grain boundaries to bend, ultimately resulting in serrated grain boundaries and γ′ phases of various sizes. The method steps include: S1, single solution treatment Take the high-temperature alloy that is difficult to deform and determine the dissolution temperature T0 of its γ′ phase. Hold the alloy at the first solid solution temperature T1 for 0.5-8 hours. The first solid solution temperature T1 is 1-20℃ higher than the dissolution temperature T0. S2, Slow Cooling The alloy is cooled to a second solution temperature T2 at a rate not exceeding 10°C / min, the second solution temperature T2 being 5-100°C lower than the remelting temperature T0. S3, Secondary Solid Solution The alloy is held at the second solution temperature T2 for 1-30 minutes. S4. Timeliness.

2. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 1, characterized in that, The difficult-to-deform high-temperature alloy is one of the following: GH4720Li alloy, GH4065A alloy, FGH4096 alloy, GH4251 alloy, GH4068 alloy, FGH4097 alloy, FGH4098 alloy, GH4151 alloy, GH4175 alloy, GH4975 alloy, GH4099 alloy, GH4079 alloy, GH4096 alloy, GH586 alloy, GH742 alloy, or GH864 alloy.

3. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 1, characterized in that, In step S2, the alloy is cooled to the second solution temperature T2 at a rate of 1.6 °C / min.

4. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 1, characterized in that, In step S3, the alloy is held at the second solution temperature T2 for 30 minutes.

5. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 1, characterized in that, In step S3, static tensile stress is applied to the alloy during the heat preservation process.

6. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 5, characterized in that, The stress magnitude is 10% of the alloy's yield strength at the holding temperature.

7. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 1, characterized in that, In step S4, the aging refers to air-cooling the alloy to room temperature and then performing a two-stage aging treatment.

8. The heat treatment method for a difficult-to-deform high-temperature alloy according to claim 7, characterized in that, The two aging treatments are as follows: the first stage involves holding the temperature at 950℃ for 12 hours and then air-cooling it to room temperature; the second stage involves holding the temperature at 850℃ for 16 hours and then air-cooling it to room temperature.

9. A high-temperature alloy that is difficult to deform, characterized in that, It is obtained by heat treatment according to any one of claims 1-8.

10. The application of the difficult-to-deform high-temperature alloy as described in claim 9 in a turbine disk, characterized in that, The application involves using the difficult-to-deform high-temperature alloy as a material for preparing turbine disks.

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