Preparation method of dual-performance deformation turbine disc for aero-engine

Abstract

A preparation method of a dual-performance deformation turbine disc for an aero-engine belongs to the technical field of preparation of nickel-based superalloy dual-performance turbine discs, and comprises the following steps: firstly, smelting a superalloy raw material bar required by electron beam drop melting through a vacuum induction melting technology; secondly, electron beam drop melting is conducted, the raw material bar is bombarded through electron beams with high energy density, heat energy is generated, and the raw material bar is melted and drop-built into a cast ingot; thirdly, simulating a double-cone geometrical shape with the optimal thermal deformation size through a finite element, and optimizing the shape and the size of the high-temperature alloy ingot obtained by the electron beam; and finally, the optimized double-cone geometrical shape is adopted for isothermal forging, and the nickel-based high-temperature alloy double-performance turbine disc is prepared. By means of the method, the alloy ingot metallurgy quality can be greatly improved, the FGH4096 alloy turbine disc is prepared through the casting and forging technology instead of the powder metallurgy technology, one-time forming of the single-alloy double-performance turbine disc can be achieved, and the defects that an existing preparation procedure is complex, accurate control is difficult and the like are overcome.

Description

Technical Field

[0001] The present invention belongs to the technical field of preparation of dual-performance turbine disks of nickel-based high-temperature alloys, and relates to a preparation method of a dual-performance deformed turbine disk for an aero-engine, and specifically to a preparation method of a dual-performance FGH4096 deformed turbine disk for an aero-engine. Background Art

[0002] FGH4096 alloy is a second-generation high-temperature alloy for powder turbine disks developed in China. It has an operating temperature of about 700°C and is widely used in aircraft engine turbine disks. Due to its high degree of alloying and severe element segregation, it cannot be prepared by traditional smelting methods, so powder metallurgy is generally used for preparation. However, powder high-temperature alloys are expensive, have a long production cycle, and inevitable problems such as thermally induced voids (TIP), primary particle boundaries (PPB) and high levels of inclusions inside the alloy, which greatly restricts the application and development of aircraft engine turbine disks. With the continuous development of casting and forging technology, new casting and forging technologies have provided a feasible option for the preparation of highly alloyed high-temperature alloys. Electron beam drip melting technology can effectively reduce element segregation, eliminate impurity elements and inclusions inside the alloy, thereby achieving highly purified and homogenized preparation of high-temperature alloys. At the same time, the introduction of <001> The oriented columnar crystal grain structure optimizes the hot working properties of high-alloy high-temperature alloys and realizes the preparation of high-temperature alloys for turbine disks by casting and forging technology instead of powder metallurgy technology.

[0003] The turbine disk is a key component of an aircraft engine, usually working at high temperature, high pressure and high speed. During service, there are significant differences between the core and edge of the turbine disk. The core of the disk is directly connected to the shaft and bears the extremely large centrifugal tensile stress generated by the high-speed rotating blades, but the working temperature of the core is relatively low. The edge of the turbine disk is in direct contact with the high-temperature gas, and the working temperature is high, but it bears relatively low centrifugal tensile stress. Therefore, it is of great significance to manufacture turbine disks with gradient microstructures in the radial direction. The core of the turbine disk is a fine-grained structure, which exhibits excellent comprehensive performance under low temperature and high stress. The edge of the turbine disk is a coarse-grained structure, which exhibits excellent comprehensive mechanical properties under high temperature and low stress. At present, the most widely used dual-performance turbine disks are mainly dual-alloy dual-structure turbine disks and single-alloy dual-structure. However, the dual-alloy turbine disk requires the two alloys to be combined by welding, hot isostatic pressing, etc., and the joint is prone to become a source of crack propagation. Single-alloy dual-structure turbine disks require controlled gradient heat treatment to regulate different microstructures, which is cumbersome and difficult to accurately control the structure. Summary of the invention

[0004] In view of the problems existing in the prior art, the present invention is based on the great advantages of electron beam refining technology in preparing high-purity and high-homogeneity high-temperature alloys, adopts electron beam drip melting technology to prepare high-purity and high-homogeneity FGH4096 alloy, and proposes a preparation method for a dual-performance deformable turbine disk.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is:

[0006] A method for preparing a dual-performance deformable turbine disk for an aircraft engine, wherein the method firstly uses vacuum induction melting technology to melt the high-temperature alloy raw material rods required for electron beam drip melting. Secondly, a high-energy-density electron beam is used to bombard the raw material rods to generate heat energy to melt them and drip them into ingots. Thirdly, a double-cone geometry with optimal dimensions for thermal deformation is simulated by finite element method, and the shape and size of the high-temperature alloy ingot obtained by the electron beam are optimized. Finally, the optimized double-cone geometry is used for isothermal forging to prepare a nickel-based high-temperature alloy dual-performance turbine disk. Specifically, the following steps are included:

[0007] The first step is to prepare the raw materials;

[0008] The rods obtained by vacuum induction melting (VIM) are used as raw materials for electron beam melting. The surface of the raw material rods is turned. The size of the processed raw material rods is

[0009] The second step, electron beam drip melting, is achieved by adding a feeding system and an ingot pulling system to the traditional electron beam melting equipment, and reasonably controlling the relationship between the feeding system, the ingot pulling system and the electron beam circular scanning system to achieve the electron beam preparation of large high-temperature alloy ingots. The details are as follows:

[0010] Step 2.1, add the raw material bar obtained in the first step to the feeding device of the electron beam melting equipment. After the raw material bar is fixed, close the furnace door for vacuum pre-evacuation. When the vacuum degree of the melting chamber is ≤10Pa, stop vacuuming and introduce argon gas into the melting chamber to purge the melting chamber (can be performed multiple times). Then perform vacuum pre-evacuation again. When the vacuum pre-evacuation is completed, evacuate the equipment to a high vacuum. Before the melting operation, the vacuum condition of the equipment is required to meet the following requirements: the vacuum degree of the melting chamber is less than 1×10 -2 Pa, the vacuum degree of the electron gun is less than 1×10 -3 Pa.

[0011] Step 2.2: Place the raw material bars on the horizontal feeding platform. When the vacuum pressure in the melting chamber reaches 1×10 -2After Pa, the raw material bar is irradiated by the electron beam, causing the bar to melt. When the electron beam equipment starts working, the electron beam spot begins variable frequency circular scanning with appropriate power and scanning rate, and the scanning mode is constantly changing within the range of one-half and one-third of the radius of the crucible; at the same time, the feeding system starts feeding, the raw material bar begins to melt, and the molten droplets fall into the crucible to form a molten pool, and when the molten droplets fall into the crucible, the ingot pulling system pulls the crucible downward to control the ingot pulling rate and the feeding rate to ensure that the height between the raw material bar and the crucible is constant. After the raw material bar is completely melted, the feeding system and the ingot pulling system are turned off, and the electron beam spot still uses a circular scanning method to control the convergence process of the electron beam droplet melting ingot. The electron beam convergence process is completed by slowly reducing the power of the electron beam spot and adjusting the scanning mode of the beam spot. After the electron beam droplet melting ingot is completely solidified, it is fully cooled under vacuum to obtain low segregation and high purity. <001> Columnar crystal High temperature alloy ingots.

[0012] The high-temperature alloy ingot obtained in the step 2.2 has uniform composition. Based on the total mass of 100%, the mass fraction of each component is: 0.45-0.05C, 15.50-16.50Cr, 12.50-13.50Co, 3.80-4.20W, 3.80-4.20Mo, 0.60-0.80Nb, 1.95-2.30Al, 3.55-3.90Ti, 0.03-0.06Zr, 0.01-0.02B, ≤0.01Fe, and the balance is nickel.

[0013] In the third step, the present invention designs a double-cone geometric sample, which is a symmetrical structure consisting of a central cylinder and two end truncated cone structures, specifically a geometric shape with a wider middle portion and a decreasing gradient toward the top and bottom.

[0014] The height of the double cone geometry sample is defined as L1, the radius of the middle cylindrical part is defined as R1, and the height is defined as L2. The radius of the top surfaces of the two truncated cones (the top surfaces are the outer end surfaces, and the inner end surfaces of the truncated cones are connected to the upper and lower end surfaces of the cylinder) is defined as R2.

[0015] The finite element method was used to simulate the reduction of the double-cone geometry under specific conditions, and the double-cone geometry was optimized. It was found that the deformation temperature had little effect on the double-cone geometric dimensions. The ratios of R2 / R1 and H2 / H1 were determined, and the geometric dimensions of the double-cone sample were R1:R2=3:1 and L1:L2=3:1, ensuring that the equivalent strain distribution of the specimen along the radial direction was relatively wide, and there was an obvious equivalent strain gap between the center and the edge.

[0016] Furthermore, in step 2.3, the parameters of the specific conditions include temperature θ, strain rate and deformation, wherein θ is 1100-1180°C and the strain rate is 0.1s -1 , the deformation is 60%.

[0017] Step 4: Heat treatment before forging

[0018] The low-segregation, high-purity high-temperature alloy ingot obtained in step 2.2 is subjected to homogenization annealing and furnace cooling to eliminate the low-melting eutectic phase and microsegregation in the ingot. The annealing temperature is 1050-1140°C and the time is 12-18 hours. The heat-treated high-temperature alloy ingot is processed into the optimized double-cone geometry in step 2.3.

[0019] Further, in the fourth step, the high-temperature alloy ingot processing process is: heating the high-temperature alloy ingot to 200°C, 400°C, 600°C, 800°C, 1000°C, and 1100°C at a heating rate of 10°C / s, keeping warm for 2h, and then transferring it to the isothermal forging furnace for isothermal forging equipment, the transfer time does not exceed 20s, the forging temperature is 1070-1100°C, the mold temperature is 1060°C, the deformation amount is 70%, and the deformation rate is 0.05s -1 , covered with an asbestos blanket and slowly cooled to obtain a dual-performance nickel-based high-temperature alloy turbine disk blank.

[0020] The innovative points of the present invention are:

[0021] (1) Traditional FGH4096 alloy turbine disks are all prepared by powder metallurgy. The present invention adopts electron beam drop melting technology to prepare high-homogeneity and high-purity columnar crystal FGH4096 alloy, improves the thermal deformation ability to replace powder metallurgy technology with casting and forging technology, greatly reduces the production process of turbine disks and saves production costs. In addition, the present invention uses FGH4096 alloy to prepare turbine disks, which can realize two different organizational structures in one turbine disk to meet the service conditions of the core and edge parts of the disk.

[0022] (2) Due to the significant difference between the edge and the center of the traditional dual-performance turbine disk, a special gradient heat treatment process is required to obtain a gradient structure that meets the service requirements. It is difficult to accurately control and the process flow is long. The present invention designs a hot deformation structure of a double-cone specimen, and performs thermal deformation along the columnar crystal direction, which can achieve a smooth gradient transition from the fine grain structure in the center of the specimen to the coarse grain structure at the edge. At the same time, it also avoids cracks caused by poor bonding between the edge and the center of the traditional dual-performance turbine disk.

[0023] The beneficial effects of the present invention are:

[0024] (1) The electron beam drip melting technology of the present invention combined with the developed equipment can greatly improve the metallurgical quality of alloy ingots, control the macro and micro segregation of ingots within a very small range, and obtain complete <001> The columnar crystal structure greatly improves the thermal deformation capacity of the high-temperature alloy, and realizes the preparation of FGH4096 alloy turbine disk by casting and forging technology instead of powder metallurgy technology.

[0025] (2) The present invention conducts hot working experiments by designing a double cone specimen. It can be observed that gradient deformation occurs during isothermal forging, the plastic strain gradually decreases from the center to both sides of the cross section, and the degree of recrystallization gradually decreases. Under 1070°C, complete recrystallization does not occur inside the specimen, a "necklace" structure appears, and serrated grains appear in some areas of the columnar grain boundaries, nucleating and growing at the columnar grain boundaries. As can be seen from the figure, at 1100°C and a strain rate of 0.01s -1 Under the above conditions, complete recrystallization of the double-cone specimen can be achieved, the grain size gradually increases radially from the center to the edge, the grain size of the fine-grained structure is ASTM grade 9-10, and the grain size of the coarse-grained structure is ASTM grade 5-6. The yield strength of the FGH4096 dual-performance deformed turbine disk from the center to the edge can be gradually reduced from 1178MPa to 995Mpa, and the one-time forming of the single-alloy dual-performance turbine disk can be achieved. The casting and forging technology replaces the powder metallurgy technology, which greatly reduces the production cycle and production cost, and overcomes the complexity of the existing preparation process and the difficulty of precise control. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 FGH4096 ingots were prepared for electron beam drop melting;

[0027] Figure 2 The microstructure of FGH4096 alloy ingot prepared by electron beam drop melting; Figure 2 (a) is the morphology of the FGH4096 ingot prepared by electron beam drop melting; Figure 2 (b) Dendrite morphology of FGH4096 ingot prepared by electron beam drip melting; Figure 2 (c) γ' phase diagram of the dendrite stem in the FGH4096 ingot prepared by electron beam drip melting; Figure 2 (d) is the γ' phase diagram of the interdendritic layer in the FGH4096 ingot prepared by electron beam drop melting;

[0028] Figure 3 Optimize the dimensional diagram for the double cone style;

[0029] Figure 4 The gradient microstructure along the radial direction of the double cone sample isothermally forged at 1070℃ and 1100℃: Figure 4 (a) 1070℃-center; Figure 4 (b) 1070℃-1 / 2 radius; Figure 4 (c) 1070°C-edge; Figure 4 (d) 1100°C-center; Figure 4 (e) 1100°C-1 / 2 radius; Figure 4 (f) 1100°C-edge;

[0030] Figure 5 Room temperature tensile stress-strain curves of the center and edge of a double-cone ingot at 1100°C. DETAILED DESCRIPTION

[0031] The present invention is further described below in conjunction with specific implementation cases.

[0032] A method for preparing a dual-performance FGH4096 deformed turbine disk for an aeroengine, the embodiment specifically comprises the following steps:

[0033] The first step is to prepare the raw materials;

[0034] The rods obtained by vacuum induction melting (VIM) are used as raw materials for electron beam melting. The surface of the raw material rods is turned. The size of the processed raw material rods is The second step is electron beam drop melting. This equipment adds a feeding system and an ingot pulling system to the traditional electron beam melting equipment. It reasonably controls the relationship between the feeding system, the ingot pulling system and the electron beam circular scanning system, and realizes the electron beam preparation of large high-temperature alloy ingots.

[0035] Step 2.1, add the raw material bar obtained in the first step to the feeding device of the electron beam equipment. After the raw material bar is fixed, close the furnace door for vacuum pre-evacuation. When the vacuum degree of the melting chamber is ≤10Pa, stop vacuuming and introduce argon gas into the melting chamber to purge the melting chamber (this embodiment is performed 3 times). Then, vacuum pre-evacuation is performed again. After the vacuum pre-evacuation is completed, the equipment is evacuated to a high vacuum. Before the melting operation is performed, the vacuum condition of the equipment is required to meet the following requirements: the vacuum degree of the melting chamber is less than 1×10 -2 Pa (in this embodiment, 1×10 -3 Pa), the vacuum degree of the electron gun is less than 1×10 -3 Pa (5×10 -4 Pa).

[0036] Step 2.2: Place the raw material bars on the horizontal feeding platform. When the vacuum pressure in the melting chamber reaches 1×10 -2After Pa, the electron beam equipment starts to work, and the electron beam spot starts variable frequency circular scanning with a melting power of 25kw. The scanning method is constantly changing within the range of one-half and one-third of the crucible radius. At the same time, the feeding system starts feeding, the raw material bar begins to melt, and the molten droplets fall into the crucible to form a molten pool. The melting rate is 11.4kg / h, and when the molten droplets fall into the crucible, the ingot pulling system pulls the crucible downward, controlling the ingot pulling rate to 3.9mm / min, and the feeding rate to ensure that the height between the raw material bar and the crucible is constant. After the raw material bar is completely melted, the feeding system and the ingot pulling system are turned off, and the electron beam spot still uses a circular scanning method to control the convergence process of the electron beam droplet melting ingot. During the convergence process, the electron beam power is gradually reduced from 25kw to 8kw within 10min, and then reduced from 8kw to 0 within 5min. At the same time, the beam spot is adjusted to the center of the molten pool to complete the convergence process of the electron beam. After the electron beam droplet ingot is completely solidified, it is fully cooled under vacuum to obtain low segregation and high purity. <001> Columnar crystal high temperature alloy ingot, ingot size is

[0037] The high-temperature alloy ingot obtained in the step 2.2 has uniform composition. Based on the total mass of 100%, the mass fraction of each component is: 0.05C, 15.72Cr, 12.98Co, 4.04W, 4.11Mo, 0.68Nb, 2.41Al, 3.56Ti, 0.04Zr, 0.01B, 0.01Fe, and the balance is nickel.

[0038] In the third step, a double cone geometry specimen was designed, which consisted of two symmetrical truncated cones connected at both ends of a cylinder, forming a geometry with a wider middle part and a decreasing gradient toward the top and bottom. The height of the double cone specimen was defined as L1, the radius of the middle cylindrical part was defined as R1, and the height was defined as L2. The radius of the top surface of the truncated cone was defined as R2.

[0039] Finite element method was used to simulate the double cone geometry at θ = 1100 ~ 1180 ° C, 0.01 ~ 0.1s -1 The double-cone geometry was optimized with a strain rate of 100% and a deformation of 60%. It was found that the deformation temperature had little effect on the double-cone geometry. The ratios of R2 / R1 and H2 / H1 were determined, and the geometric dimensions of the double-cone pattern were R1:R2=3:1 and L1:L2=3:1. The optimized dimensions are R1=39mm, R2=13mm, L1=60mm, and L2=20mm, which ensure that the equivalent strain distribution of the specimen along the radial direction is relatively wide, and there is an obvious equivalent strain gap between the center and the edge.

[0040] In this embodiment, in step 2.3, the parameters of the specific conditions include temperature θ, strain rate and deformation, where θ is 1100°C and the strain rate is 0.1s-1 , the deformation is 60%.

[0041] Step 4: Heat treatment before forging

[0042] Step 3.1, subjecting the obtained low-segregation, high-purity high-temperature alloy ingot to homogenization annealing treatment, furnace cooling, and eliminating the low-melting eutectic phase and microsegregation in the ingot. The annealing temperature is 1120°C and the time is 15 hours. The heat-treated high-temperature alloy ingot is processed into the optimized double-cone geometry in step 2.3.

[0043] In this embodiment, the high-temperature alloy ingot processing process is: the high-temperature alloy ingot is heated to 200°C, 400°C, 600°C, 800°C, 1000°C, and 1100°C at a heating rate of 10°C / s, and then transferred to the isothermal forging furnace for isothermal forging equipment after being kept warm for 2 hours. The transfer time does not exceed 20s, the forging temperature is 1070°C and 1100°C, the mold temperature is 1060°C, the deformation amount is 70%, and the deformation rate is 0.05s -1 , covered with an asbestos blanket and slowly cooled to obtain a dual-performance nickel-based high-temperature alloy turbine disk blank.

[0044] The above-described embodiments merely express the implementation methods of the present invention, but they cannot be understood as limiting the scope of the patent of the present invention. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. A method for preparing a dual-performance deformable turbine disk for an aero-engine, characterized in that: The preparation method comprises the following steps: The first step is to melt the high-temperature alloy raw material bars required for electron beam drip melting through vacuum induction melting technology; The second step is electron beam drip melting, which uses high-energy-density electron beams to bombard the raw material bars to generate heat energy to melt them and drip them into ingots; In the third step, the double cone geometry with the optimal size for thermal deformation is simulated by finite element method, and the shape and size of the high-temperature alloy ingot obtained by electron beam are optimized; In the fourth step, the optimized double-cone geometry is used for isothermal forging to produce a nickel-based high-temperature alloy dual-performance turbine disk.

2. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 1, characterized in that: The first step is specifically: using the high-temperature alloy rod obtained by vacuum induction melting as the raw material for electron beam melting, and turning the surface of the raw material rod.

3. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 2, characterized in that: The second step is specifically as follows: Electron beam drip melting is achieved by adding a feeding system and an ingot pulling system to the traditional electron beam melting equipment, and the relationship between the feeding system, the ingot pulling system and the electron beam annular scanning system is reasonably controlled to achieve electron beam preparation of large high-temperature alloy ingots; Step 2.1, adding the raw material bar obtained in the first step into the feeding device of the electron beam melting equipment, and after the raw material bar is fixed, closing the furnace door for vacuum pre-evacuation; Step 2.2: Place the raw material bars on the horizontal feeding platform. When the vacuum pressure in the melting chamber reaches 1×10 -2 After Pa, the raw material bar is irradiated by the electron beam, which causes the bar to melt; The electron beam equipment starts to work, and the electron beam spot starts to scan in a variable frequency circular manner. The scanning mode is constantly changing within the range of one-half and one-third of the radius of the crucible. At the same time, the feeding system starts to feed, the raw material bar starts to melt, and the molten droplets fall into the crucible to form a molten pool. When the molten droplets fall into the crucible, the ingot pulling system pulls the crucible downward, controls the ingot pulling rate and the feeding rate, and ensures that the height between the raw material bar and the crucible is constant. After the raw material bar is completely melted, the feeding system and the ingot pulling system are closed, and the electron beam spot still uses a circular scanning method to control the focusing process of the electron beam droplet melting ingot to obtain a high-temperature alloy ingot.

4. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 3, characterized in that: The vacuum pre-pumping in step 2.1 is as follows: when the vacuum degree of the smelting chamber is ≤10Pa, the vacuum pumping is stopped and argon gas is introduced into the smelting chamber to purge the smelting chamber; then the vacuum pre-pumping is performed again, and after the vacuum pre-pumping is completed, the equipment is evacuated to a high vacuum; before the smelting operation is performed, the vacuum condition of the equipment is required to meet the following requirements: the vacuum degree of the smelting chamber is <1×10 -2 Pa, the vacuum degree of the electron gun is less than 1×10 -3 Pa.

5. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 3, characterized in that: In step 2.2, the electron beam focusing process is completed by slowly reducing the power of the electron beam spot and adjusting the scanning mode of the beam spot. After the electron beam droplet melt ingot is completely solidified, it is fully cooled under vacuum to obtain a low-segregation, high-purity <001> Columnar crystal high temperature alloy ingot.

6. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 3, characterized in that: In the step 2.2, the composition of the high temperature alloy ingot is uniform, and the mass fraction of each component is: 0.45-0.05C, 15.50-16.50Cr, 12.50-13.50Co, 3.80~4.20W, 3.80~4.20Mo, 0.60~0.80Nb, 1.95~2.30Al, 3.55~3.90Ti, 0.03~0.06Zr, 0.01~0.02B, ≤0.01Fe, and the balance is nickel.

7. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 3, characterized in that: The third step is specifically as follows: A double cone geometric shape specimen is designed, which is a symmetrical structure consisting of a central cylinder and two truncated cone structures, specifically a geometric shape with a wider middle part and a decreasing gradient toward the top and bottom; the height of the double cone geometric shape specimen is defined as L1, the radius of the central cylindrical part is defined as R1, and the height is defined as L2; ​​the radius of the top surfaces of the two truncated cones is defined as R2; The finite element method was used to simulate the reduction of the double-cone geometry under specific conditions, the double-cone geometry was optimized, and the ratios of R2 / R1 and H2 / H1 were determined. The geometric dimensions of the double-cone pattern were R1:R2=3:1 and L1:L2=3:

1.

8. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 7, characterized in that: In the third step, the parameters of the specific conditions include temperature θ, strain rate and deformation, where θ is 1100-1180°C and the strain rate is 0.1s -1 , the deformation is 60%.

9. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 7, characterized in that: The fourth step is specifically as follows: The high-temperature alloy ingot obtained in step 2.2 is subjected to homogenization annealing treatment and furnace cooling; the annealing temperature is 1050-1140° C. and the time is 12-18 hours; the high-temperature alloy ingot after heat treatment is processed into the double-cone geometric shape optimized in step 2.

3.

10. The method for preparing a dual-performance deformable turbine disk for an aircraft engine according to claim 9, characterized in that: In the fourth step, the high-temperature alloy ingot processing process is: heating the high-temperature alloy ingot to 200°C, 400°C, 600°C, 800°C, 1000°C, and 1100°C at a heating rate of 10°C / s, keeping warm for 2h, and then transferring it to the isothermal forging furnace for isothermal forging equipment, the transfer time does not exceed 20s, the forging temperature is 1070-1100°C, the mold temperature is 1060°C, the deformation is 70%, and the deformation rate is 0.05s -1 , covered with an asbestos blanket and cooled slowly to obtain a dual-performance deformable turbine disk.

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