Heat treatment method for uniform precipitated phase of large nickel-iron-based alloy part

Abstract

The invention discloses a heat treatment method for a uniform precipitated phase of a large nickel-iron-based alloy part. The nickel-iron-based high-temperature alloy part is heated to be within the range of 100-300 DEG C above the gamma'strengthening phase complete dissolution temperature, air cooling is conducted, and during air cooling, the time difference when all positions in the nickel-iron-based high-temperature alloy part are cooled to the gamma 'strengthening phase nose tip temperature T nose + 30 DEG C does not exceed the fastest complete precipitation time of the gamma' strengthening phase; the average cooling rate is 0.2 DEG C / min-25 DEG C / min within the range of T nose + / -100 DEG C; and aging. Air cooling is carried out after temperature reduction heating in the whole solid solution stage, the temperature reduction temperature is selected according to the size of a component, it is guaranteed that the cooling time of all positions in the temperature interval where a precipitated phase is rapidly precipitated is close, and it is guaranteed that the structures of all parts of the alloy in the solid solution cooling stage are close. And then aging treatment is carried out, gamma'phase is completely separated out, the structure is stabilized, and the uniform structure property is obtained on the premise that the good comprehensive mechanical property is guaranteed.

Description

Technical Field

[0001] This invention belongs to the field of high-temperature alloy materials technology, specifically relating to a heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components. It can meet the heat treatment requirements for uniformly precipitated phases in large precipitation-strengthened high-temperature alloy components, and is particularly suitable for the preparation of large high-temperature pressure-bearing structural components. Background Technology

[0002] With the rapid development of aerospace, thermal power generation, and chemical industries, the demand for high-performance and cost-effective high-temperature alloys is constantly increasing. The HT700 series of nickel-iron-based alloys, employing precipitation strengthening, can operate safely and reliably in harsh environments with higher temperatures and stresses compared to traditional heat-resistant steels. At the same time, compared to nickel-based alloys, their cost is significantly reduced, making them widely applicable across various industries.

[0003] Precipitation-strengthened alloys achieve matrix strengthening through the precipitation of precipitates. The size and volume fraction of the precipitates are the main factors affecting the alloy's properties. As the size of the precipitates increases, the strength of nickel-iron-based alloys decreases while their ductility increases. Because nickel-iron-based alloys are highly sensitive to heat treatment parameters, solution cooling can achieve a uniform microstructure, but excessively large precipitate sizes weaken the material's strength properties. For large precipitation-strengthened alloy components, air cooling or water cooling is most suitable. However, solution cooling followed by water cooling of large components can lead to excessively rapid cooling, resulting in high residual stress and significant differences in cooling rates between the core and surface. Solution cooling followed by air cooling can significantly reduce residual stress caused by cooling, but differences in cooling rates and temperatures across different parts can also lead to variations in precipitate nucleation and growth rates, resulting in differences in precipitate size across different locations in large components, thus causing inhomogeneous microstructure and properties. This inhomogeneity poses significant challenges to subsequent design and processing; therefore, a heat treatment process that can achieve a uniform microstructure and reduce differences in precipitate size is urgently needed. Summary of the Invention

[0004] To overcome the technical problem of uneven microstructure and properties in precipitation-strengthened alloys in the prior art, the purpose of this invention is to provide a heat treatment method for uniform precipitates in large nickel-iron-based alloy components. This method can achieve uniform microstructure and reduce the size difference of precipitates.

[0005] To achieve the above-mentioned objectives, the technical solution adopted by this invention is as follows: A heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components involves heating the nickel-iron-based superalloy component to a temperature 100°C-300°C above the complete dissolution temperature of the γ' strengthening phase, followed by air cooling. During air cooling, each location within the nickel-iron-based superalloy component is cooled to the nose temperature T of the γ' strengthening phase. 鼻 The time difference at +30℃ does not exceed the fastest complete precipitation time of the γ' strengthening phase, and at T 鼻The average cooling rate within the range of ±100℃ is 0.2℃ / min-25℃ / min; then aging treatment is performed.

[0006] A further improvement of the present invention is that the nickel-iron-based high-temperature alloy component has a regular shape and a component thickness of [missing information]. And satisfy The relationship is given by X, where X is the heating heat transfer coefficient and t is the fastest complete precipitation time of γ'.

[0007] A further improvement of this invention is that the alloy composition of the nickel-iron-based high-temperature alloy component, by mass percentage, includes: Fe: 26%-47%, Cr: 15%-22%, Mo: ≤2.5%, W: ≤2.5%, Ti: 1.2%-3.0%, Co: ≤3.0%, Al: 0.3%-2.5%, Mn: ≤1.0%, Nb: ≤0.1%, Si: ≤0.05%, C: 0.03%-0.10%, B: 0.001%-0.005%, P: ≤0.01%, with the balance being Ni.

[0008] A further improvement of the present invention is that the heating rate when heated to the temperature range of 100°C-300°C above the complete dissolution temperature of the γ' strengthening phase is 3°C / min-6°C / min.

[0009] A further improvement of the present invention is that the γ' strengthening phase precipitate in the nickel-iron-based superalloy component has an L12 structure and conforms to the A3B type atomic ratio, wherein element A is Ni, Fe or Co, and element B is Al, Ti, Nb, Ta, W or Mo.

[0010] A further improvement of this invention is that, before heating the nickel-iron-based superalloy component to a temperature 100°C-300°C above the complete dissolution temperature of the γ' strengthening phase, the component is first heated to a temperature 20°C-50°C above the complete dissolution temperature of the γ' strengthening phase at a heating rate of 5°C / min-15°C / min, and a holding temperature step is established. This temperature is the holding temperature T. 保 The heat preservation time shall not be less than min, after heat preservation, the temperature gradient along the wall thickness direction of the high-temperature alloy component is less than 0.1℃ / mm, where H is the component thickness and X is the heating heat transfer coefficient.

[0011] A further improvement of the present invention is that the aging treatment conditions are as follows: the temperature is increased to 650-660℃ at a heating rate of 5-15℃ / min, held for 20-24 hours, and then air-cooled to room temperature.

[0012] A further improvement of the present invention is that the instantaneous cooling rate of the nickel-iron-based high-temperature alloy component is not less than 0.2℃ / min, and the cooling rate of the outer wall of the nickel-iron-based high-temperature alloy component does not exceed 10 times the instantaneous cooling rate of the core.

[0013] A further improvement of this invention is that when the nickel-iron-based superalloy component is heated to a temperature within the range of 100°C-300°C above the complete dissolution temperature of the γ' strengthening phase, the temperature is the heating temperature T. 升 Temperature T 升 satisfy The relationship.

[0014] A further improvement of the present invention is that, after aging treatment, the size of the precipitated phase at each location of the nickel-iron-based superalloy component is less than 20%, and the difference in impact performance between different parts is less than 20%.

[0015] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components, reducing the difference in microstructure and properties between the surface and core of large alloy components through a simple heat treatment process. Compared with traditional heat treatment processes, the heat treatment process of the present invention involves heating to a high temperature followed by air cooling throughout the solution treatment stage. The high temperature is selected according to the component size to ensure that the cooling time is similar at different locations within the temperature range where the precipitated phase precipitates rapidly, thus ensuring that the microstructure of the alloy is similar in different parts during the solution cooling stage. Subsequently, aging treatment is performed to completely precipitate the γ' phase and stabilize the microstructure. After aging treatment, the size difference of the γ' phase is less than 20%, and the difference in room temperature impact performance is less than 20%. The present invention achieves uniform microstructure and properties while ensuring good overall mechanical properties. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the embodiments will be briefly described below. These drawings are used to provide a further understanding of the present invention, constitute a part of this application, and do not constitute a limitation of the present invention. In the drawings: Figure 1 The near-surface precipitate morphology of the alloy component in Example 1; Figure 2 The image shows the morphology of the precipitated phase in the core of the alloy component in Example 1; Figure 3 The near-surface precipitate morphology of the alloy component in Comparative Example 1; Figure 4 The core morphology of the alloy component in Comparative Example 1 is shown. Figure 5 The near-surface precipitate morphology of the alloy component in Comparative Example 2; Figure 6 The image shows the morphology of the precipitated phase in the core of the alloy component in Comparative Example 2. Detailed Implementation

[0017] To facilitate understanding of the present invention, a more complete description will be given below with reference to the accompanying drawings. Preferred embodiments of the invention are shown in the drawings. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a thorough and complete understanding of the disclosure of the invention.

[0018] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0019] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0020] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0021] The accompanying drawings illustrate various structural schematic diagrams according to embodiments disclosed in this invention. These drawings are not to scale, and some details have been enlarged for clarity, and some details may have been omitted. The shapes of the various regions and layers shown in the drawings, as well as their relative sizes and positional relationships, are merely exemplary and may deviate from reality due to manufacturing tolerances or technical limitations. Furthermore, those skilled in the art can design regions / layers with different shapes, sizes, and relative positions as needed.

[0022] In this invention It represents the multiplication sign.

[0023] The large nickel-iron-based alloy components in this invention refer to components with regular shapes and a thickness of [missing information]. And satisfy The relationship is given by X, where X is the heating heat transfer coefficient, and the required heating heat transfer coefficient X (i.e., heat penetration coefficient) is obtained from actual measurements, T 鼻T represents the nose tip temperature of the γ'-enhanced phase, which is the fastest precipitation temperature in the measured TTT curve (isothermal transition curve, T-time, T-temperature, T-transformation). t represents the fastest complete precipitation time of the γ'-enhanced phase, and t represents the complete precipitation time corresponding to the nose tip temperature in the measured TTT curve. 保 This is the insulation temperature.

[0024] The present invention provides a heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components, comprising the following steps: Solution treatment stage: The nickel-iron-based superalloy is heated at a rate of 5℃ / min-15℃ / min to 20℃-50℃ above the complete dissolution temperature of the γ' strengthening phase, and a holding step is established. This temperature is T. 保 The heat preservation time shall not be less than After holding at that temperature for a period of time, the temperature gradient along the wall thickness of the high-temperature alloy component is less than 0.1℃ / mm. Then, the heating rate is controlled at 3℃ / min-6℃ / min, and the temperature is heated to within 100℃-300℃ above the complete dissolution temperature of the γ' strengthening phase. This temperature is the heating temperature T. 升 After the furnace temperature stabilizes, air cooling is applied. H represents the thickness of the high-temperature alloy component, and X represents the heating heat transfer coefficient.

[0025] During cooling, each location in the large nickel-iron-based superalloy component is cooled to the γ' strengthening phase nose temperature T. 鼻 The time difference at +30℃ does not exceed the fastest complete precipitation time of the γ' strengthening phase, and the average cooling rate within ±100℃ of the γ' strengthening phase nose temperature is 0.2℃ / min-25℃ / min. Subsequently, aging treatment is performed, with the heating rate controlled at 5-15℃ / min to 650-660℃, held for 20-24h, and then air-cooled to room temperature.

[0026] The alloy composition of large nickel-iron-based high-temperature alloy components, by mass percentage, includes: Fe: 26%-47%, Cr: 15%-22%, Mo: ≤2.5%, W: ≤2.5%, Ti: 1.2%-3.0%, Co: ≤3.0%, Al: 0.3%-2.5%, Mn: ≤1.0%, Nb: ≤0.1%, Si: ≤0.05%, C: 0.03%-0.10%, B: 0.001%-0.005%, P: ≤0.01%, with the balance being Ni. The γ' strengthening phase in the alloy conforms to the L12 structure, with Ni3Al and Ni3(Al,Ti) being preferred as intragranular precipitates. It conforms to an A3B type atomic ratio, where A is Ni, Fe, or Co, and B is Al, Ti, Nb, Ta, W, or Mo.

[0027] All alloys within the above-mentioned alloy composition range can be subjected to the heat treatment method of this invention.

[0028] A further improvement of the present invention is that, in order to ensure the uniformity of the alloy components during the heating and cooling process, the furnace heating inside the furnace and the furnace cooling outside the furnace need to be erected or hoisted, and the heat treatment furnace should be a bogie furnace or a pit furnace.

[0029] A further improvement of the present invention is that, during the cooling process, the instantaneous cooling rate of the high-temperature alloy component is not less than 0.2℃ / min, and the cooling rate of the outer wall of the high-temperature alloy component does not exceed 10 times the instantaneous cooling rate of the core.

[0030] A further improvement of this invention is that the heating temperature T 升 satisfy The relationship.

[0031] In this invention, the size difference of precipitates at various locations in the component after final heat treatment is less than 20%, and the difference in impact performance at various locations is less than 20%. This invention can achieve uniform microstructure and reduce the size difference of precipitates.

[0032] The following are specific examples.

[0033] Example 1 The alloy is a precipitation-strengthened wrought superalloy. The measured composition after preparation, by mass percentage, includes: C: 0.05%, Cr: 16%, Mn: 0.1%, Si: 0.025%, W: 0.3%, Mo: 0.6%, Ti: 1.8%, Al: 1.6%, B: 0.002%, Fe: 40%, with the balance being Ni. The complete dissolution temperature of γ' in the alloy is 900℃, the nose temperature of the TTT curve is 855℃, and the fastest complete precipitation time is approximately 19 minutes. The alloy has a heat transfer coefficient of 0.9 mm / min. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging dimensions are 400 mm thick, 1200 mm long, and 1200 mm wide. The heat treatment process is as follows: The high-temperature alloy component was heated to 950°C in the furnace at a rate of 8°C / min and held for 210 min, then heated to 1100°C at a rate of 4°C / min. o C. Wait for the furnace temperature to reach 1100°C. o Once the temperature stabilizes, immediately remove the component and air cool it. An thermocouple is embedded in the surface of the workpiece. The surface of the component is cooled to 885°C in 15 minutes, then to 825°C in 20 minutes, and then further air-cooled to room temperature. Next, the temperature is increased to 650°C at a rate of 7°C / min and held for 20 hours before air-cooling to room temperature. Figure 1 and Figure 2 The images show the γ' phase morphology near the surface and in the core of the component in Example 1. It can be seen that the γ' phase size is uniform at both the surface and core.

[0034] Comparative Example 1 The composition and dimensions are the same as in Example 1, but the heat treatment process is as follows: The high-temperature alloy component was heated to 950°C in the furnace at a rate of 8°C / min and held for 210 min, then heated to 1100°C at a rate of 4°C / min. o After reaching temperature C, hold at that temperature for 210 minutes. Remove and air cool. An thermocouple is embedded in the surface of the workpiece. The surface of the component is cooled to 885°C in 28 minutes, then to 825°C in 37 minutes, and then further air-cooled to room temperature. Next, the temperature is increased to 650°C at a rate of 7°C / min and held for 20 hours before air-cooling to room temperature. Figure 3 and Figure 4 Comparing the γ' phase morphology near the surface and the core of component 1, it can be seen that the size of the γ' phase at the surface and the core differs greatly.

[0035] Comparative Example 2 The composition and dimensions are the same as in Example 1, but the heat treatment process is as follows: The high-temperature alloy component was heated to 950°C in the furnace at a rate of 8°C / min and held for 210 min, then heated to 1100°C at a rate of 4°C / min. o After temperature C, remove and water cool. Then raise the temperature to 650℃ at 7℃ / min and hold for 20 hours before air cooling to room temperature. Figure 5 and Figure 6 To compare the γ' phase morphology near the surface and the core of component 2, it can be seen that the size of the γ' phase at the surface and the core differs greatly.

[0036] Table 1 compares the room temperature impact properties of Example 1, Comparative Example 1, and Comparative Example 2 after heat treatment. It can be seen that the precipitate size and impact properties after heat treatment using the process described in this invention are similar. However, after treatment with Comparative Example 1, the γ' size difference in different parts of the alloy component is approximately 40%, and the impact property difference is approximately 35%. After treatment with Comparative Example 2, the γ' size difference in different parts of the alloy component is approximately 58%, and the impact property difference is approximately 26%. This fully demonstrates that the heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components using this invention can achieve a uniform level of surface and core microstructure properties.

[0037] Table 1. Microstructure and room temperature shock properties of Examples 1, Comparative Examples 1 and 2 after heat treatment.

[0038] Example 2 The alloy composition is the same as in Example 1. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 950°C in the furnace at a rate of 10°C / min and held for 270 min, then heated to 1070°C at a rate of 4°C / min.o Remove C and air cool. Then raise the temperature to 650℃ at 7℃ / min and hold for 20 hours before air cooling to room temperature.

[0039] Example 3 The alloy is a precipitation-strengthened wrought superalloy. The measured composition after preparation, by mass percentage, includes: C: 0.05%, Cr: 16%, Mn: 0.1%, Si: 0.025%, W: 0.3%, Mo: 0.6%, Ti: 2.3%, Al: 2.0%, B: 0.002%, Fe: 38%, with the balance being Ni. The complete dissolution temperature of γ' in the alloy is 937℃, the nose temperature of the TTT curve is 875℃, and the fastest complete precipitation time is approximately 17 minutes. The alloy has a heat transfer coefficient of 0.9 mm / min. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging dimensions are: thickness 572 mm, length 1120 mm, width 845 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 965°C in the furnace at a rate of 7°C / min and held for 300 min, then heated to 1100°C at a rate of 3°C / min. o Remove C and air cool. Then raise the temperature to 650℃ at 8℃ / min and hold for 20 hours before air cooling to room temperature.

[0040] Example 4 The alloy composition is the same as in Example 1. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 930°C in the furnace at a rate of 10°C / min, held at that temperature for 268.5 min, and then heated to 1100°C at a rate of 3°C / min. o Remove C and air cool. Then raise the temperature to 650℃ at 10℃ / min and hold for 20 hours before air cooling to room temperature.

[0041] Example 5 The alloy composition is the same as in Example 1. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 920°C in the furnace at a rate of 5°C / min, held at that temperature for 280 min, and then heated to 1200°C at a rate of 5°C / min. o Remove C and air cool. Then raise the temperature to 650℃ at 25℃ / min and hold for 20 hours before air cooling to room temperature.

[0042] Example 6 The alloy composition is the same as in Example 1. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 950°C in the furnace at a rate of 7°C / min and held for 290 min, then heated to 1110°C at a rate of 6°C / min. o Remove C and air cool. Then raise the temperature to 650℃ at a rate of 0.2℃ / min and hold for 24 hours before air cooling to room temperature.

[0043] Example 7 The alloy composition is the same as in Example 3. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 960°C in the furnace at a rate of 6°C / min, held at that temperature for 287.4 min, and then heated to 1037°C at a rate of 6°C / min. o Remove C and air cool. Then raise the temperature to 655℃ at 3℃ / min and hold for 22 hours before air cooling to room temperature.

[0044] Example 8 The alloy composition is the same as in Example 3. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 987°C in the furnace at a rate of 7°C / min and held for 290 min, then heated to 1237°C at a rate of 4°C / min. o Remove C and air cool. Then raise the temperature to 650℃ at 20℃ / min and hold for 20 hours before air cooling to room temperature.

[0045] Example 9 The alloy composition is the same as in Example 3. The alloy preparation process involves vacuum induction melting followed by vacuum arc remelting, followed by forging. The selected forging has a diameter of 1050 mm and a height of 530 mm. The heat treatment process is as follows: The high-temperature alloy component was heated to 957°C in the furnace at a rate of 8°C / min and held for 300 min, then heated to 1150°C at a rate of 5°C / min. o Remove C and air cool. Then raise the temperature to 660℃ at 15℃ / min and hold for 20 hours before air cooling to room temperature.

[0046] This invention reduces the difference in microstructure and properties between the surface and core of large alloy components through a simple heat treatment process. Compared with traditional heat treatment processes, the heat treatment process of this invention involves heating to a high temperature followed by air cooling throughout the solution treatment stage. The high temperature is selected according to the size of the component to ensure that the cooling time is similar at different locations within the temperature range where the precipitated phase precipitates rapidly, thus ensuring that the microstructure of the alloy is similar in different parts during the solution cooling stage. Aging treatment is then performed to completely precipitate the γ' phase and stabilize the microstructure. After aging treatment, the size difference of the γ' phase is less than 20%, and the difference in room temperature impact properties is less than 20%. This invention achieves uniform microstructure and properties while ensuring good overall mechanical properties.

[0047] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the scope of the invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0048] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that can be understood by those skilled in the art. The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components, characterized in that, The nickel-iron-based superalloy component was heated to a temperature 100°C-300°C above the complete dissolution temperature of the γ' strengthening phase, and then air-cooled. During air cooling, each location in the nickel-iron-based superalloy component was cooled to the nose temperature T of the γ' strengthening phase. 鼻 The time difference at +30℃ does not exceed the fastest complete precipitation time of the γ' strengthening phase, and at T 鼻 The average cooling rate within the range of ±100℃ is 0.2℃ / min-25℃ / min; then aging treatment is performed.

2. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, The nickel-iron-based high-temperature alloy component has a regular shape and a component thickness of [missing information]. And satisfy The relationship is given by X, where X is the heating heat transfer coefficient and t is the fastest complete precipitation time of γ'.

3. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, The alloy composition of nickel-iron-based high-temperature alloy components, by mass percentage, includes: Fe: 26%-47%, Cr: 15%-22%, Mo: ≤2.5%, W: ≤2.5%, Ti: 1.2%-3.0%, Co: ≤3.0%, Al: 0.3%-2.5%, Mn: ≤1.0%, Nb: ≤0.1%, Si: ≤0.05%, C: 0.03%-0.10%, B: 0.001%-0.005%, P: ≤0.01%, with the balance being Ni.

4. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, The heating rate is 3℃ / min to 6℃ / min when heating to a temperature 100℃-300℃ above the complete dissolution temperature of the γ' strengthening phase.

5. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, In nickel-iron-based superalloy components, the γ' strengthening precipitate has an L12 structure and conforms to the A3B atomic ratio, where element A is Ni, Fe, or Co, and element B is Al, Ti, Nb, Ta, W, or Mo.

6. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, Before heating the nickel-iron-based superalloy component to within the range of 100℃-300℃ above the complete dissolution temperature of the γ' strengthening phase, first raise the temperature of the nickel-iron-based superalloy component to 20℃-50℃ above the complete dissolution temperature of the γ' strengthening phase at a heating rate of 5℃ / min-15℃ / min, and establish a holding temperature step. This temperature is called the holding temperature T. 保 The heat preservation time shall not be less than min, after heat preservation, the temperature gradient along the wall thickness direction of the high-temperature alloy component is less than 0.1℃ / mm, where H is the component thickness and X is the heating heat transfer coefficient.

7. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, The aging treatment conditions are as follows: heat up to 650-660℃ at a heating rate of 5-15℃ / min, hold for 20-24 hours, and then air cool to room temperature.

8. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, The instantaneous cooling rate of nickel-iron-based high-temperature alloy components shall not be less than 0.2℃ / min, and the cooling rate of the outer wall of the nickel-iron-based high-temperature alloy components shall not exceed 10 times the instantaneous cooling rate of the core.

9. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, When heating nickel-iron-based superalloy components to a temperature 100℃-300℃ above the complete dissolution temperature of the γ' strengthening phase, the temperature is the heating temperature T. 升 Temperature T 升 satisfy The relationship.

10. The heat treatment method for uniformly precipitated phases in large nickel-iron-based alloy components according to claim 1, characterized in that, After aging treatment, the precipitated phase size at each location of the nickel-iron-based superalloy component is less than 20%, and the difference in impact performance between different parts is less than 20%.

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