High-performance nickel-based high-temperature alloy for gas turbine blade and preparation method of high-performance nickel-based high-temperature alloy

Abstract

The invention discloses a high-performance nickel-based high-temperature alloy for a gas turbine blade and a preparation method of the high-performance nickel-based high-temperature alloy. The nickel-based high-temperature alloy comprises the following components in percentage by mass: 0.05 to 0.15 percent of C, 13.5 to 14.5 percent of Cr, 9.0 to 11.0 percent of Co, 1.0 to 2.0 percent of Mo, 3.8 to 4.8 percent of W, 3.5 to 4.5 percent of Al, 2.2 to 3.2 percent of Ti, 4.2 to 5.2 percent of Ta, 0.01 to 0.1 percent of RE and the balance of Ni and inevitable impurities. According to the preparation method, alloy components are optimized, and the size of a phase serving as a main strengthening phase in the nickel-based high-temperature alloy is optimized by introducing two rare earth elements Y or Ce, so that the strength of the as-cast alloy at the room temperature is improved, and the application range of the alloy is widened.

Description

Technical Field

[0001] This invention relates to the field of high-temperature alloys, and more specifically to a high-performance nickel-based high-temperature alloy for gas turbine blades and its preparation method. Background Technology

[0002] Nickel-based superalloys possess excellent high-temperature strength, oxidation resistance, and hot corrosion resistance, maintaining good mechanical properties and structural stability in high-temperature environments. Therefore, they are widely used in high-temperature, high-pressure, and corrosive environments such as aerospace, energy, and petroleum. They are particularly prevalent in critical components such as aero-engines and gas turbines.

[0003] Strength is a key performance indicator for nickel-based superalloys, directly affecting their wear resistance, creep resistance, fatigue resistance, machinability, oxidation and corrosion resistance, and microstructural stability. High-strength superalloys can maintain good performance under harsh environments such as high temperature, high stress, and corrosion, extending component lifespan and improving economic efficiency. Therefore, proper strength control is crucial in the design and application of superalloys. In superalloys, The strengthening phase is the primary strengthening phase, and its form, content, size, and distribution all affect the strength of high-temperature alloys. By adjusting these characteristics, the strength of nickel-based high-temperature alloys can be significantly improved, thereby enhancing their performance under harsh environments such as high temperature and high stress. Summary of the Invention

[0004] The purpose of this invention is to provide a high-performance nickel-based superalloy for gas turbine blades and a method for its preparation, which improves the strength of the nickel-based superalloy and enhances its comprehensive performance under harsh environments such as high temperature and high stress.

[0005] To achieve the above objectives, the present invention employs the following technical solution: a high-performance nickel-based superalloy for gas turbine blades, the nickel-based superalloy comprising the following components by mass percentage: C 0.05–0.15%, Cr 13.5–14.5%, Co 9.0–10.0%, Mo 1.0–2.0%, W 3.8–4.8%, Al 3.5–4.5%, Ti 2.2–3.2%, Ta 4.2–5.2%, RE 0.01–0.1%, with the balance being Ni and unavoidable impurities.

[0006] Furthermore, the RE is either Y or Ce.

[0007] Furthermore, the mass percentages of each component in the nickel-based superalloy are: C 0.05%, Cr 13.5%, Co 9.0%, Mo 1.0%, W 3.8%, Al 3.5%, Ti 2.2%, Ta 4.2%, Y 0.05%, with the balance being Ni and unavoidable impurities. At room temperature, the nickel-based superalloy contains... The phase has an equivalent diameter of 56.4 nm and an average Vickers hardness of 490.

[0008] Furthermore, the mass percentages of each component in the nickel-based superalloy are: C 0.15%, Cr 14.5%, Co 10.0%, Mo 2.0%, W 4.8%, Al 4.5%, Ti 3.2%, Ta 5.2%, Ce 0.05%, with the balance being Ni and unavoidable impurities. At room temperature, the nickel-based superalloy contains... The phase has an equivalent diameter of 55.3 nm and an average Vickers hardness of 524.

[0009] Another objective of this invention is to provide a method for preparing the above-mentioned nickel-based superalloy. The method involves first subjecting each raw material to ultrasonic treatment and drying treatment, and then mixing the treated raw materials and repeatedly melting and casting them to obtain the nickel-based superalloy.

[0010] Furthermore, the method specifically includes the following preparation steps: S1) Calculate the mass required to weigh each element based on the mass percentage of each alloy component; S2) Remove impurities and oxide scale from the surface of the selected raw material block, place it in anhydrous ethanol for ultrasonic vibration cleaning to remove surface impurities, and then dry it. S3) Weigh the raw material blocks after processing S2) based on the mass of each raw material calculated according to S1). Place the weighed mixed raw materials and oxygen-consuming titanium ingots into the copper crucible of the vacuum non-consumable electric arc furnace. S4) First, the furnace cavity is evacuated, then a protective atmosphere is introduced into the furnace cavity, and multiple melting processes are carried out under a certain current to obtain a nickel-based high-temperature alloy.

[0011] Furthermore, the specific process parameters in S4) are: vacuuming to 5 × 10 -3 Below Pa, a protective atmosphere is introduced at a pressure of 0.02 MPa. After the residual oxygen is consumed by titanium ingots, the mixed raw materials are smelted at least 10 times, with each smelting time being 2 to 3 minutes. The current requirement during smelting is 200A-250A. The mixture must be turned over after each smelting.

[0012] Furthermore, the protective atmosphere is high-purity argon. This invention has the following beneficial effects: By optimizing the alloy composition and introducing rare earth elements (Y and Ce) to the main strengthening phases in nickel-based superalloys... The phase size is optimized to make it more uniformly distributed in the matrix. This results in a finer phase size. The phase can increase the phase interface area, thereby more effectively hindering dislocation movement, improving the strength of the alloy, and broadening the application range of nickel-based superalloys. Moreover, the average Vickers hardness of the alloy is increased by up to 15.4%. This invention also discloses a method for preparing the above-mentioned high-performance nickel-based high-temperature alloy that can be used for gas turbine blades. The method uses a non-consumable vacuum arc furnace to melt the alloying elements to obtain alloy ingots. The operation is simple and easy to implement, with low energy consumption and low cost, and has high economic benefits. Attached Figure Description

[0013] Figure 1 SEM image of the Y-added as-cast nickel-based superalloy prepared in Example 1.

[0014] Figure 2 SEM image of the as-cast nickel-based superalloy with added Ce prepared in Example 2.

[0015] Figure 3 SEM image of the as-cast nickel-based high-temperature alloy without rare earth elements prepared for Comparative Example 1.

[0016] Figure 4 Vickers hardened as-cast nickel-based superalloys prepared in Examples 1-2 and Comparative Example 1 Degree comparison chart. Detailed Implementation

[0017] The present invention will be further described below with reference to specific embodiments. Unless otherwise specified, the methods described are conventional methods, and the raw materials described are obtainable from publicly available commercial sources.

[0018] In the following embodiments: The purity (mass percentage, wt%) of the elemental substances corresponding to C, Cr, Co, Mo, W, Al, Ti, Ta, Ni, Y and Ce is greater than 99.9%; Hardness test: HV-50 Vickers hardness tester test parameters: loading force 1kN, loading time 15s, 12 points of hardness value are taken for each test, the maximum and minimum values ​​are removed, and the average value of the remaining values ​​is taken.

[0019] Microstructure characterization: The microstructure of the prepared as-cast nickel-based superalloy was observed using a Supra 55 field emission scanning electron microscope (SEM) manufactured by Zeiss, Germany. Columnar samples with dimensions of Φ8×8mm were cut using wire EDM. The surfaces of the samples were polished smooth using 60#, 400#, 800#, and 2000# sandpaper, respectively. The samples were then mechanically polished using diamond polishing paste on a metallographic polishing machine. Electropolishing was performed using a solution of 20 vol% concentrated sulfuric acid + 80 vol% methanol (volume fraction) at a voltage of 9–10 V for approximately 5 seconds. Electrolytic etching was then performed using an electrolyte solution of 15 g chromium oxide + 150 ml phosphoric acid + 10 ml concentrated sulfuric acid at a voltage of 4.5–5 V for approximately 2 seconds. The samples were then ultrasonically cleaned in anhydrous ethanol. After thorough drying, the samples were observed under an electron microscope.

[0020] Example 1 A method for preparing a high-performance nickel-based superalloy for gas turbine blades with added Y element, comprising the following steps: Raw material preparation: Calculate and take a fixed amount of raw material blocks containing C, Cr, Co, Mo, W, Al, Ti, Ta, Ni, and Y. After sanding off impurities and oxide scale from the surface of the raw materials, place all weighed raw materials in anhydrous ethanol for ultrasonic cleaning to further remove surface impurities, followed by drying. Finally, accurately weigh the required mass of raw materials on a balance.

[0021] The mass percentages of each component in the nickel-based superalloy are: C 0.05%, Cr 13.5%, Co 9.0%, Mo 1.0%, W 3.8%, Al 3.5%, Ti 2.2%, Ta 4.2%, Y 0.05%, with the balance being Ni and unavoidable impurities.

[0022] Melting and preparation: The raw materials are placed in a small vacuum arc furnace for melting to obtain a high-performance nickel-based superalloy suitable for gas turbine blades. The current requirement during melting is 230A, and the vacuum degree of the vacuum arc furnace needs to be evacuated to 5×10⁻⁶ before melting. -3 The melting time is below Pa. Each melting session takes 2 to 3 minutes. The alloy needs to be flipped after each melting session. After melting 12 times, the alloy ingot is obtained.

[0023] Figure 1 The image shows a SEM image of the as-cast nickel-based superalloy from Example 1. Statistical analysis is performed. The equivalent diameter of the phase is 56.4 nm.

[0024] Table 1 shows the Vickers hardness test results for Example 1: .

[0025] Example 2 A method for preparing a high-performance nickel-based superalloy for gas turbine blades with added Ce element, comprising the following steps: Raw material preparation: Calculate and take a fixed amount of raw material blocks containing C, Cr, Co, Mo, W, Al, Ti, Ta, Ni, and Ce. After sanding off impurities and oxide scale from the surface of the raw materials, place all weighed raw materials in anhydrous ethanol for ultrasonic cleaning to further remove surface impurities, followed by drying. Finally, accurately weigh the required mass of raw materials on a balance.

[0026] The mass percentages of each component in the nickel-based superalloy are: C 0.15%, Cr 14.5%, Co 10.0%, Mo 2.0%, W 4.8%, Al 4.5%, Ti 3.2%, Ta 5.2%, Ce 0.05%, with the balance being Ni and unavoidable impurities.

[0027] Melting and preparation: The raw materials are placed in a small vacuum arc furnace for melting to obtain a high-performance nickel-based superalloy suitable for gas turbine blades. The current requirement during melting is 230A, and the vacuum degree of the vacuum arc furnace needs to be evacuated to 5×10⁻⁶ before melting. -3 The melting time is below Pa. Each melting session takes 2 to 3 minutes. The alloy needs to be flipped after each melting session. After melting 12 times, the alloy ingot is obtained.

[0028] Figure 2 The image shows a SEM image of the as-cast nickel-based superalloy from Example 2. Statistical analysis is performed. The equivalent diameter of the phase is 55.3 nm.

[0029] Table 2 shows the Vickers hardness test results for Example 2: .

[0030] Comparative Example 1 A method for preparing a nickel-based superalloy for gas turbine blades without the addition of rare earth elements includes the following steps: Raw material preparation: Calculate and take a fixed amount of raw material blocks of C, Cr, Co, Mo, W, Al, Ti, Ta, and Ni. After sanding off impurities and oxide scale from the surface of the raw materials, place all weighed raw materials in anhydrous ethanol for ultrasonic cleaning to further remove surface impurities, followed by drying. Finally, accurately weigh the required mass of raw materials on a balance.

[0031] Melting and preparation: The raw materials are placed in a small vacuum arc furnace for melting to obtain a nickel-based superalloy. The current required during melting is 230A. Before melting, the vacuum degree of the vacuum arc furnace needs to be evacuated to 5×10⁻⁶. -3The melting time is below Pa. Each melting session takes 2 to 3 minutes. The alloy needs to be flipped after each melting session. After melting 12 times, the alloy ingot is obtained.

[0032] Figure 3 For comparative example 1, SEM images of the as-cast nickel-based superalloy were obtained, and statistical analysis was performed. The equivalent diameter of the phase is 98.6 nm.

[0033] Table 3 shows the Vickers hardness test results for Comparative Example 1: ; Table 4 lists the nickel-based superalloys prepared in Examples 1-2 and Comparative Example 1. Comparison results of equivalent diameters: ; Figure 4 The results show the columnar comparison of the hardness of the nickel-based superalloys prepared in Examples 1-2 and Comparative Example 1.

[0034] The foregoing has provided a detailed description of a high-performance nickel-based superalloy for gas turbine blades and its preparation method, as provided in the embodiments of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of this application; furthermore, those skilled in the art will recognize that, based on the ideas of this application, there will be changes in specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this application.

[0035] Certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that hardware manufacturers may use different names to refer to the same component. This specification and claims do not distinguish components based on differences in name, but rather on differences in function. The terms "comprising" and "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising / including but not limited to". "Approximately" means that within an acceptable margin of error, those skilled in the art can solve the technical problem and substantially achieve the technical effect within a certain margin of error. The following descriptions in the specification are preferred embodiments for carrying out this application; however, these descriptions are for the purpose of illustrating the general principles of this application and are not intended to limit the scope of this application. The scope of protection of this application shall be determined by the appended claims.

[0036] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a product or system comprising a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a product or system. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the product or system that includes said element.

[0037] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0038] The foregoing description illustrates and describes several preferred embodiments of this application. However, as previously stated, it should be understood that this application is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the application concept described herein through the foregoing teachings or techniques or knowledge in related fields. Any modifications and variations made by those skilled in the art that do not depart from the spirit and scope of this application should be within the protection scope of the appended claims.

Claims

1. A high performance nickel-base superalloy for use in gas turbine turbine blades, characterized in that, The nickel-based superalloy comprises the following components in mass percentage: C 0.05-0.15%, Cr 13.5-14.5%, Co 9.0-10.0%, Mo 1.0-2.0%, W 3.8-4.8%, Al 3.5-4.5%, Ti 2.2-3.2%, Ta 4.2-5.2%, RE 0.01-0.1%, and the balance of Ni and inevitable impurities.

2. The nickel-base superalloy of claim 1, wherein, The RE is Y or Ce.

3. The high-performance nickel-base superalloy of claim 2, wherein, The mass percentages of the individual components of the nickel-based superalloy are: C 0.05%, Cr 13.5%, Co 9.0%, Mo 1.0%, W 3.8%, Al 3.5%, Ti 2.2%, Ta 4.2%, Y 0.05%, the remainder being Ni, and at room temperature, the nickel-based superalloy has a an equivalent diameter of the phase of 56.4 nm and an average Vickers hardness of 490.

4. The high-performance nickel-base superalloy of claim 2, wherein, The mass percentage of each component of the nickel-based superalloy is: C 0.15%, Cr 14.5%, Co 10.0%, Mo 2.0%, W 4.8%, Al 4.5%, Ti 3.2%, Ta 5.2%, Ce 0.05%, and the balance is Ni; and at room temperature, the equivalent diameter of the phase in the nickel-based superalloy is 55.3 nm, and the average Vickers hardness is 524. The equivalent diameter of the phase is 55.3 nm, and the average Vickers hardness is 524.

5. A method of producing a nickel-based superalloy as claimed in any one of claims 1 to 4, characterised in that, The method comprises the following steps of: firstly, ultrasonic treatment and drying treatment are performed on each raw material respectively; then, the treated raw materials are mixed and sequentially subjected to repeated melting and casting forming, thereby obtaining the nickel-based superalloy.

6. The method of claim 5, wherein, The method comprises the following preparation steps: S1) according to the mass percentage of each alloy component, the mass required for weighing each element is calculated; S2) the selected raw material block surface impurities and oxide scale are removed, and placed in anhydrous ethanol for ultrasonic oscillation cleaning, so as to remove the surface impurities, and drying treatment is performed; S3) according to the mass of each raw material calculated in S1), the raw material block treated in S2) is weighed, and the weighed mixed raw materials and titanium ingot for consuming oxygen are placed into a copper crucible of a vacuum non-consumable arc furnace; S4) the furnace cavity is first vacuumized, then a protective atmosphere is filled into the furnace cavity, and multiple melting is performed under a certain current, thereby obtaining the nickel-based superalloy.

7. The method of claim 6, wherein, The specific process parameters in S4) are: vacuum extraction to 5x10 -3 After the residual oxygen is consumed by the titanium ingot, the mixed raw materials are smelted for at least 10 times, each time for 2-3 minutes, the current during smelting is required to be 200A-250A, and the smelted materials need to be turned over after each smelting is completed.

8. The method of claim 7, wherein, The protective atmosphere is high-purity argon.

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