Surface treatment technology for improving high-temperature service performance of nickel-based high-temperature alloy

Abstract

The invention provides a surface treatment technology for improving the high-temperature service performance of a nickel-based high-temperature alloy, and relates to the technical field of alloy surface treatment. The surface treatment technology comprises the steps that firstly, the surface of the nickel-based superalloy is pretreated; then plating a layer of coating on the pretreated surface; and finally, the nickel-based high-temperature alloy with the coating is subjected to overall heat treatment, and the nickel-based high-temperature alloy with the coating and high oxidation resistance, creep resistance and fatigue resistance is obtained. According to the method, nickel-based high-temperature alloy surface pretreatment, coating plating and overall heat treatment are adopted, and the oxidation resistance, creep resistance and fatigue resistance of the alloy in a high-temperature service environment are further improved on the basis that the room-temperature strength and plasticity of the alloy are not affected; the method is simple in process, low in operation difficulty, low in cost, high in efficiency, capable of achieving synergistic improvement of oxidation resistance, creep resistance and fatigue resistance under the long-time service condition of 850 DEG C, and beneficial to industrial large-scale application and popularization.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of alloy surface treatment, and particularly relates to a surface treatment technology for improving high-temperature service performance of a nickel-based high-temperature alloy. BACKGROUND

[0002] Nickel-based high-temperature alloys have become the key materials for the hot end components (including turbine blades, guide vanes and combustion chambers) of aero-engines due to their high strength and structural stability under severe conditions. With the continuous increase of the thrust-to-weight ratio of modern aero-engines, the demand for higher working temperatures is increasing, especially in high-pressure turbine blades. These components must have excellent mechanical properties, oxidation resistance and long-term reliability in service under high pressure, heavy load, strong vibration and corrosive environment. However, the alloy design relying only on chemical composition optimization has been difficult to meet the above multiple requirements. In order to prolong the service life of the nickel-based high-temperature alloy, protective coating has become an indispensable technical means.

[0003] Traditional coatings (such as MCrAlY (M = Ni, Co or Ni+Co) and modified aluminide coatings) are widely used, but often cause a decrease in the mechanical properties of the substrate. For example, Chinese patent CN117721400A is such a case. As for the tensile properties, Li et al. and Parlikar et al. studied the effect of PtAl coating on nickel-based single-crystal high-temperature alloys. The results showed that the yield strength and tensile strength of the coated samples decreased in the range of room temperature to 1100℃. For example, the strength of the coated CMSX-2 alloy decreased by 7.4% at room temperature, and René 80 and other nickel-based single-crystal alloys also showed similar trends. The main failure mechanism is interface weakening, that is, the initiation of cracks in the coating surface or interdiffusion zone (IDZ), although the elongation after fracture remains basically stable.

[0004] And Chinese patent CN110172703A discloses a method for improving the service life of a high-temperature coating on a nickel-based alloy. The method first deposits a Pt layer by electroplating, then deposits an aluminide coating on the substrate, and then performs a pre-oxidation treatment on the sample coated with the modified aluminide coating; a high-temperature coating is obtained by performing a cyclic oxidation experiment on the pre-oxidized sample; obviously, the structure of the high-temperature coating is relatively complex, the preparation process is difficult to be efficient, and the prepared coating is relatively thick, so as to affect the mechanical properties of the overall nickel-based alloy.

[0005] During long-term service, the interdiffusion of elements intensifies, making the creep and long-term rupture properties decrease more obviously. For example, in the range of 850-1100℃, the PtAl coating in the nickel-based single crystal makes the creep life decrease by 7-23%, and the ductility decrease by 10-20%. For the advanced alloy such as TMS-138, the sensitivity is higher, and the life decreases by 14.2% compared with the uncoated substrate, which is mainly due to the enrichment of refractory elements at the interface. Similarly, in Cotac 784 alloy, the NoCoCrAlYTa coating makes the fracture life decrease by 20-50%; and the aluminized coating makes the fracture life of the thin sample with a thickness of 0.2mm at 980℃, 230MPa shorten to less than 1h. In the aluminide and MCrAlY coating, the fatigue resistance is also significantly reduced; the high-cycle fatigue strength at 870℃ decreases significantly, mainly because both accelerate crack initiation and propagation.

[0006] The Chinese patent CN111893418A discloses a method for improving the high-temperature oxidation resistance of the surface of a nickel-based alloy, which not only needs to analyze the stress of a multi-layer coating powder model, but also needs to be hot sprayed according to the proportion to the surface of the pretreated machine body, and the process of preparing the coating clearly needs electron cladding. There is a mutual diffusion of coating elements and matrix elements in the process of preparing a thin coating, which increases the oxidation resistance of the nickel-based superalloy, increases the brittleness, and decreases the mechanical properties.

[0007] During high-temperature exposure, the inevitable interdiffusion of elements between the coating and the alloy matrix is the main reason for this systematic degradation. The diffusion of Al, Cr and other elements in the coating to the matrix destroys the γ / γ' two-phase structure, thereby reducing the oxidation resistance of the coating. This process leads to the formation of various regions at the coating-matrix interface, such as the interdiffusion zone (IDZ), the substrate diffusion zone (SDZ) and the secondary reaction zone (SRZ). In addition, due to the significant decrease in solubility of refractory elements such as W, Mo, Re and Ta, the precipitation of brittle topological close-packed (TCP) phases further destroys the mechanical integrity of the matrix.

[0008] Therefore, one of the main challenges and key research focuses in the field of advanced coating / alloy systems is to understand and control the interfacial behavior of the coating / alloy. SUMMARY

[0009] The technical problem to be solved by the present application is how to efficiently and at low cost improve the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys. Although the coating composition used in the prior art can form a dense Al2O3 and Cr2O3 oxide film, these brittle oxides are prone to cracking and failure during long-term service at 850 DEG C or higher. In addition, the prior art does not fully consider the impact of long-term oxidation on material performance, especially the weakening effect of high-temperature oxidation on creep and fatigue performance. At the same time, structural defects often occur during the preparation of the coating, which will continuously expand and worsen under long-term service conditions at 850 DEG C or higher, resulting in significant weight gain due to oxidation, thereby further reducing the reliability of the material under high-temperature working conditions.

[0010] To solve the above technical problems, the present application provides a surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, which comprises the following steps: first, pretreating the surface of the nickel-based superalloy; then, plating a coating layer on the pretreated surface; and finally, subjecting the nickel-based superalloy with the coating layer to overall heat treatment to obtain a nickel-based superalloy with the coating layer having high oxidation resistance, high creep resistance and high fatigue resistance.

[0011] Optionally, the surface treatment technology specifically comprises the following steps:

[0012] S1, surface pretreatment: pretreating the surface of the nickel-based superalloy to remove oil stains and oxides to obtain a nickel-based superalloy with a clean surface;

[0013] S2, coating plating: using electroplating, chemical plating or magnetron sputtering method to plate a coating layer on the surface of the nickel-based superalloy with a clean surface obtained in S1, the coating layer having high oxidation resistance, high creep resistance and high fatigue resistance under high-temperature environment, to obtain a nickel-based superalloy with a coating layer;

[0014] S3, overall heat treatment: subjecting the nickel-based superalloy with the coating layer obtained in S2 to heat treatment to obtain a nickel-based superalloy with improved high-temperature service performance.

[0015] Optionally, the pretreatment in S1 comprises alkali washing with a hot alkali solution to remove oil stains on the surface of the nickel-based superalloy, and acid washing with a dilute hydrochloric acid solution to remove oxides on the surface of the nickel-based superalloy.

[0016] Optionally, the nickel-based superalloy in S1 comprises wrought superalloy, cast superalloy, powder metallurgy superalloy and oxide dispersion strengthened alloy.

[0017] Optionally, the wrought superalloy includes GH2132, GH3044, GH4169; the cast superalloy includes K213, K418, K419; the powder metallurgy superalloy includes FGH51, ME501, RR1000; and the oxide dispersion strengthened alloy includes MHP-5, 0Cr25Ni20MoWV and Inconel 617.

[0018] Optionally, the coating chemical composition in S2 is at least one of Pt, Re and Ru, and the coating thickness is 0.1-10 microns.

[0019] Optionally, in S2, the coating is formed by electroplating, electroless plating or magnetron sputtering according to the coating composition and the shape and roughness of the substrate surface; and the coating decomposes and disperses in the oxide generated during high-temperature service of the nickel-based superalloy.

[0020] Optionally, in S3, the heat treatment is annealing, which is performed in an argon atmosphere, the annealing temperature is 400-750 DEG C, and the annealing time is 2-24 hours.

[0021] Optionally, in S3, the nickel-based superalloy with improved high-temperature service performance has reduced weight gain at 900 DEG C for 200 hours compared with the substrate, and the creep life is improved under the creep conditions of 900 DEG C and 25 MPa or 900 DEG C and 50 MPa.

[0022] Optionally, in S3, the weight gain at 900 DEG C for 200 hours is reduced by 67% in the nickel-based superalloy with Re coating compared with the substrate.

[0023] Under the creep conditions of 900 DEG C and 25 MPa, the creep life of the nickel-based superalloy with Pt coating is increased by 23.01% at most compared with the substrate; the creep life of the substrate is 115.6 hours, and the creep life of the workpiece after treatment is 142.2 hours.

[0024] Under the creep conditions of 900 DEG C and 50 MPa, the creep life of the nickel-based superalloy with Re coating is 75.5 hours, and the creep life of the substrate is 64.8 hours.

[0025] Optionally, in S3, the nickel-based superalloy with Ru coating has a fatigue life of 1.17 times that of the substrate under the low-cycle fatigue conditions of 900 DEG C and a total strain amplitude of 0.8-1.2%, the fatigue life is 1.2 times that of the substrate when the total strain amplitude is 1%, and the fatigue life is 1.28 times that of the substrate when the total strain amplitude is 1.2%.

[0026] Technical principle of the application:

[0027] Nickel-based superalloys are usually applied to high-temperature structural components, which often have complex shapes, thus a surface treatment process suitable for complex-shaped workpieces is needed. Meanwhile, the treated workpiece also needs to be subjected to mechanical property evaluation under actual service conditions, and the introduction of the coating cannot weaken other service properties of the nickel-based superalloy.

[0028] In view of the problems that the high-temperature oxidation resistance of the nickel-based superalloy is insufficient, and most of the existing coatings have high brittleness, are difficult to provide protection for a long time, and even have an adverse effect on the mechanical properties of the alloy substrate, the present application provides a method for treating a nickel-based superalloy. A Pt, Ru, Re stable noble metal coating with a thickness of 0.1-10 μm is prepared on the surface of the nickel-based superalloy. Since the Pt, Ru, Re, etc. stable noble metal has good plasticity, it can be doped into the originally generated oxide during high-temperature oxidation, thereby reducing the brittleness of the oxide film. The method not only significantly improves the oxidation resistance of the nickel-based superalloy in a high-temperature environment, but also shows improvement in the creep resistance and fatigue resistance.

[0029] Compared with the prior art, the above technical solution has at least the following beneficial effects:

[0030] The above scheme, a surface treatment technology for improving the high-temperature service properties of a nickel-based superalloy, can solve the technical problems of the prior art, such as that brittle oxides are prone to failure due to cracking during long-term service at 850°C or above, that high-temperature oxidation weakens the creep and fatigue properties, that structural defects of the coating continuously expand and worsen under long-term service conditions at 850°C or above, that the oxidation weight gain is obvious, and that the reliability of the material under high-temperature working conditions is low.

[0031] The noble metal coating technology adopted by the present application can effectively avoid the defects that the existing coating components are prone to generate brittle Al2O3 and Cr2O3 oxides, which leads to cracking and peeling of the coating; and simultaneously improve the oxidation resistance, creep resistance and fatigue resistance of the material.

[0032] The Pt, Ru, Re noble metal coating adopted by the present application has a relatively thin thickness, low cost and simple operation, and is suitable for complex-shaped workpieces.

[0033] The noble metal elements in the coating of the present application can diffuse into the generated oxides during high-temperature service, improve the plasticity of the oxides, and slow down the problem of the decrease in the room temperature strength and plasticity of the alloy after long-term oxidation.

[0034] The present application can promote the stable formation of the oxides under service conditions by heat treatment after coating, significantly improve the high-temperature oxidation resistance, reduce the oxidation weight gain, and further improve the high-temperature creep resistance and fatigue resistance.

[0035] In summary, the method of the present application uses nickel-based superalloy surface pretreatment, coating plating and overall heat treatment to further improve the oxidation resistance, creep resistance and fatigue resistance of the superalloy in high-temperature service environment without affecting the room temperature strength and plasticity of the superalloy, relative to conventional superalloy coating structures and preparation techniques. The method is simple in process, low in operation difficulty, low in cost and high in efficiency, can realize the synergistic improvement of the oxidation resistance, creep resistance and fatigue resistance of the superalloy under 850℃ long-time service conditions, and is conducive to the large-scale industrial application and promotion. BRIEF DESCRIPTION OF DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0037] Figure 1 is a process schematic diagram of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to the present application;

[0038] Figure 2 is a surface SEM graph after Pt treatment of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application;

[0039] Figure 3 is a surface XRD graph after Pt treatment of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application;

[0040] Figure 4 is an oxidation kinetics curve graph after Pt treatment and 900℃ oxidation for 200h of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application;

[0041] Figure 5 is a surface SEM graph after Pt treatment and 900℃ oxidation for 200h of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application;

[0042] Figure 6 is a cross-section SEM graph after Pt treatment and 900℃ oxidation for 200h of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application;

[0043] Figure 7 is a creep life-strain curve graph after Pt treatment and 900℃ oxidation for 200h of a surface treatment technology for improving high-temperature service performance of a nickel-based superalloy according to Embodiment 3 of the present application. DETAILED DESCRIPTION

[0044] The technical solutions in the present application will be described below with reference to the drawings.

[0045] In the embodiments of the present application, the words such as "example", "for example" are used to represent an example, illustration or description. Any embodiment or design scheme described as "example" in the present application should not be interpreted as more preferred or more advantageous than other embodiments or design schemes. In fact, the word "example" is intended to present the concept in a specific way. In addition, in the embodiments of the present application, the meaning expressed by "and / or" can be both, or can be one of the two.

[0046] In the embodiments of the present application, "image" and "picture" can be used interchangeably at times. It should be pointed out that when the distinction is not emphasized, the meanings expressed are consistent.

[0047] In the embodiments of the present application, sometimes the subscript such as W1 can be written in the form of non-subscript such as W1. When the distinction is not emphasized, the meanings expressed are consistent.

[0048] To make the technical problems, technical solutions and advantages to be solved by the present application clearer, the following will be described in detail with reference to the drawings and specific embodiments.

[0049] A surface treatment technology for improving high-temperature service performance of a nickel-based high-temperature alloy, the surface treatment technology comprising: first, pretreating the surface of the nickel-based high-temperature alloy; then, plating a coating layer on the pretreated surface; finally, subjecting the nickel-based high-temperature alloy with the coating layer to overall heat treatment, to obtain the nickel-based high-temperature alloy with the coating layer having high oxidation resistance, high creep resistance and high fatigue resistance.

[0050] In particular, the surface treatment technology is specifically combined with Figure 1 comprising the following steps:

[0051] S1, surface pretreatment: pretreating the surface of the nickel-based high-temperature alloy to remove oil stains and oxides, to obtain the nickel-based high-temperature alloy with a clean surface;

[0052] S2, coating plating: using the method of electroplating, chemical plating or magnetron sputtering, plating a coating layer on the surface of the nickel-based high-temperature alloy with a clean surface obtained in S1, the coating layer having high oxidation resistance, high creep resistance and high fatigue resistance in a high-temperature environment, to obtain the nickel-based high-temperature alloy with the coating layer;

[0053] S3, overall heat treatment: subjecting the nickel-based high-temperature alloy with the coating layer obtained in S2 to heat treatment, to obtain the nickel-based high-temperature alloy with improved high-temperature service performance.

[0054] Specifically, the pretreatment of S1 includes: alkaline washing with hot alkaline solution to remove oil stains from the surface of the nickel-based superalloy, and acid washing with dilute hydrochloric acid solution to remove oxides from the surface of the nickel-based superalloy.

[0055] Specifically, nickel-based superalloys in S1 include wrought superalloys, cast superalloys, powder metallurgy superalloys, and oxide dispersion strengthened alloys.

[0056] Specifically, wrought superalloys include GH2132, GH3044, and GH4169; cast superalloys include K213, K418, and K419; powder metallurgy superalloys include FGH51, ME501, and RR1000; and oxide dispersion strengthened alloys include MHP-5, 0Cr25Ni20MoWV, and Inconel 617.

[0057] Specifically, the coating chemical composition in S2 is at least one of Pt, Re, and Ru, and the coating thickness is 0.1-10 μm.

[0058] Specifically, in S2, electroplating, electroless plating, or magnetron sputtering is selected for coating based on the coating composition and the shape and roughness of the substrate surface; the coating will decompose and disperse in the oxides generated during the high-temperature service of the nickel-based superalloy.

[0059] Specifically, the heat treatment in S3 is annealing, which is carried out in an argon atmosphere at a temperature of 400-750℃ for 2-24 hours.

[0060] In particular, the nickel-based superalloy with improved high-temperature service performance in S3 showed reduced oxidation weight gain compared to the matrix at 900℃ and 200h, improved creep life under creep conditions of 900℃ and 25MPa, and improved creep life under creep conditions of 900℃ and 50MPa.

[0061] In particular, the oxidation weight gain at 900℃ for 200h in S3 was reduced by at least 67% compared to the base material in nickel-based superalloys containing a Re coating;

[0062] Under creep conditions of 900℃ and 25MPa, the creep life of nickel-based superalloys with Pt coating can be increased by up to 23.01% compared with the substrate; the creep life of the substrate is 115.6h, and the creep life of the treated workpiece is 142.2h.

[0063] In nickel-based superalloys with Re coating, under creep conditions of 900℃ and 50MPa, the creep life of the substrate is 64.8h, and the creep life of the treated workpiece is 75.5h.

[0064] Specifically, the nickel-based superalloy containing Ru coating in S3 under low-cycle fatigue conditions of 900℃ and a total strain amplitude of 0.8-1.2%, has a fatigue life 1.17 times that of the substrate when the total strain amplitude is 0.8%, 1.2 times that of the substrate when the total strain amplitude is 1%, and 1.28 times that of the substrate when the total strain amplitude is 1.2%.

[0065] Example 1

[0066] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is FGH51 alloy, and the surface treatment technology specifically includes the following steps:

[0067] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: Rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the specimens were subjected to alkaline washing with a 0.2 mol / L alkaline solution at 60℃ for 1 hour to remove oil stains from the surface of the workpieces to be plated, and acid washing with a 0.15 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides from the surface of the workpieces to be plated, resulting in a clean FGH51 high-temperature alloy surface.

[0068] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0069] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.15 mol / L to obtain the dilute hydrochloric acid solution.

[0070] S2. Coating: The cleaned FGH51 high-temperature alloy from S1 is placed in a mixed solution of potassium perrhenate and sulfuric acid for 5 hours for coating. The coating temperature is controlled at 70℃, the pulse on-time is 0.008ms, the pulse off-time is 40ms, and the average current density is 8A / dm³. 2 A coated FGH51 high-temperature alloy was obtained; among which,

[0071] Potassium perrhenate solution needs to be prepared on-site. Specifically, potassium perrhenate (KReO4) needs to be weighed and prepared into a 0.15 mol / L solution.

[0072] Sulfuric acid solution needs to be prepared on-site; specifically, it is obtained by diluting sulfuric acid to 0.20 mol / L.

[0073] S3. Overall heat treatment: The coated FGH51 high-temperature alloy obtained in S2 is subjected to annealing heat treatment. The annealing heat treatment is annealing in an argon atmosphere at 700℃ for 10h, and finally FGH51 high-temperature alloy with a Re coating thickness of 0.5μm with improved high-temperature service performance is obtained.

[0074] The oxidation performance of the FGH51 superalloy with a Re coating thickness of 0.5 μm prepared in this embodiment was tested at 900 °C for 200 h. Its oxidation weight gain was approximately 0.96 mg / cm³. 2 Only the matrix (1.44 mg / cm³) 2 2 / 3 of ). According to the test method for determining the oxidation resistance of steel and high-temperature alloys (National Standard 5258-2000), the national standard can determine that its oxidation resistance reaches the level of complete oxidation resistance.

[0075] High-temperature creep tests were conducted on the FGH51 high-temperature alloy with a Re coating thickness of 0.5 μm prepared in this embodiment. Creep elongation-time curves at 900℃ and 100 MPa were obtained for the alloy before and after Re coating treatment. The creep elongation-time curves show that the creep fracture time after Re coating treatment is 236.6 h, which is greater than the 180.5 h of the untreated alloy, representing an improvement of 31.08%.

[0076] The high-temperature fatigue performance of the FGH51 high-temperature alloy with a Re coating thickness of 0.5 μm prepared in this embodiment was tested. Under low-cycle fatigue conditions of 900℃ and a total strain amplitude of 0.8-1.2%, when the total strain amplitude was 0.8%, the fatigue life of the coated sample was 1.36 times that of the substrate; when the total strain amplitude was 1%, the fatigue life of the coated sample was 1.18 times that of the substrate; and when the total strain amplitude was 1.2%, the fatigue life of the coated sample was 1.29 times that of the substrate.

[0077] In this embodiment, a Re coating was prepared on FGH51 high-temperature alloy using the aforementioned electroplating technology. Oxidation / creep / fatigue tests at 900℃ demonstrated that this new method effectively reduces the oxidation weight gain of FGH51 high-temperature alloy and improves creep life and fatigue life. This enhances the high-temperature oxidation resistance, creep resistance, and fatigue resistance of FGH51 alloy.

[0078] Example 2

[0079] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is K213 alloy, and the specific steps of the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys are as follows:

[0080] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: Rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the specimens were subjected to alkaline washing with a 0.2 mol / L alkaline solution at 65℃ for 1 hour to remove oil stains from the surface of the workpieces to be plated, and acid washing with a 0.10 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides from the surface of the workpieces to be plated, resulting in a clean K213 high-temperature alloy.

[0081] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0082] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.10 mol / L to obtain the dilute hydrochloric acid solution.

[0083] S2. Coating: A 500nm thick Ru coating is grown on the clean K213 high-temperature alloy surface of S1 using high-temperature magnetron sputtering technology. The Ru coating growth temperature is 500℃ and the deposition rate is 5nm / min, resulting in a K213 high-temperature alloy with a coating.

[0084] S3. Overall heat treatment: The K213 high-temperature alloy with coating from S2 was annealed in an argon atmosphere at 650℃ for 10h to finally obtain a K213 high-temperature alloy with a Ru coating thickness of 0.5μm.

[0085] The oxidation performance of the K213 superalloy with a Ru coating thickness of 0.5 μm prepared in this embodiment was tested at 800 °C for 200 h. Its oxidation weight gain was approximately 0.59 mg / cm³. 2 Only the matrix (0.93 mg / cm³) 2 63.44% of the total. According to the test method for determining the oxidation resistance of steel and high-temperature alloys (National Standard 5258-2000), the national standard can determine that its oxidation resistance reaches the level of complete oxidation resistance.

[0086] High-temperature creep tests were conducted on the K213 high-temperature alloy with a Ru coating thickness of 0.5 μm prepared in this embodiment. Creep elongation-time curves at 850℃ and 100 MPa were obtained for the alloy before and after Ru plating. The creep elongation-time curves show that the creep fracture time after Ru plating was 150.2 h, which is greater than the 96.8 h of the untreated alloy, representing an improvement of 55.16%.

[0087] The high-temperature fatigue performance of the K213 high-temperature alloy with a Ru coating thickness of 0.5 μm prepared in this embodiment was tested. Under low-cycle fatigue conditions of 850℃ and a total strain amplitude of 0.8-1.2%, the fatigue life was 1.17 times that of the substrate when the total strain amplitude was 0.8%, 1.2 times that of the substrate when the total strain amplitude was 1%, and 1.28 times that of the substrate when the total strain amplitude was 1.2%.

[0088] In this embodiment, a Ru coating was prepared on K213 superalloy using the aforementioned magnetron sputtering technique. Oxidation / creep / fatigue tests at 900℃ demonstrated that this new method effectively reduces the oxidation weight gain of K213 superalloy and improves creep life and fatigue life. This enhances the high-temperature oxidation resistance, creep resistance, and fatigue resistance of the K213 alloy.

[0089] Example 3

[0090] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is GH4169 alloy, and the specific steps of the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys are as follows:

[0091] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: Rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the specimens were subjected to alkaline washing with a 0.2 mol / L alkaline solution at 65℃ for 1 hour to remove oil stains from the surface of the workpieces to be plated, and acid washing with a 0.10 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides from the surface of the workpieces to be plated, resulting in a clean GH4169 high-temperature alloy.

[0092] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0093] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.10 mol / L to obtain the dilute hydrochloric acid solution.

[0094] S2. Coating: The cleaned GH4169 high-temperature alloy from S1 was placed in a 1:1 mixture of 0.25 mol / L hydroxylamine hydrochloride solution and 0.008 mol / L dinitrosodiammonium platinum solution. The mixture was heated in a water bath at 45°C for 2 hours. During heating, hydrazine hydrate was added to achieve a concentration of hydrazine hydrate above 0.15 mol / L. Ammonia was added to adjust the pH to above 9, resulting in a coated GH4169 high-temperature alloy.

[0095] The hydroxylamine hydrochloride solution needs to be prepared on-site. Specifically, hydroxylamine hydrochloride needs to be weighed and prepared into an aqueous solution with a concentration of 0.25 mol / L.

[0096] The dinitrosodiamineplatinum solution needs to be prepared on-site. Specifically, dinitrosodiamineplatinum needs to be weighed and prepared into an aqueous solution with a concentration of 0.008 mol / L.

[0097] Ammonia solution needs to be prepared on-site, specifically by diluting ammonia solution to a 1 mol / L concentration.

[0098] S3, Overall Heat Treatment

[0099] The S2 coated nickel-based superalloy was annealed in an argon atmosphere at 600℃ for 10 h, resulting in a GH4169 superalloy with a Pt coating thickness of 1.0 μm and improved high-temperature service performance. The oxidation performance of the nickel-based superalloy prepared in this example was tested, and oxidation kinetics curves were obtained after oxidation at 900℃ for 200 h with and without Pt treatment. The oxidation weight gain after Pt treatment was approximately 0.86 mg / cm³. 2 Only the matrix (1.24 mg / cm³) 2 69.35% of that. For example... Figure 4 As shown.

[0100] High-temperature creep tests were conducted on the GH4169 high-temperature alloy with a Pt coating thickness of 1.0 μm prepared in this embodiment. Creep elongation-time curves at 900℃ and 25 MPa were obtained for the alloy before and after Pt plating. The creep elongation-time curves show that the creep rupture time after Pt plating was 191.25 h, which is longer than the 146.59 h of the untreated alloy. Figure 7 As shown.

[0101] The high-temperature fatigue performance of the GH4169 high-temperature alloy with a Pt coating thickness of 1.0 μm prepared in this embodiment was tested. Under low-cycle fatigue conditions of 850℃ and a total strain amplitude of 0.8-1.2%, the fatigue life was 1.22 times that of the substrate when the total strain amplitude was 0.8%, 1.12 times that of the substrate when the total strain amplitude was 1%, and 1.29 times that of the substrate when the total strain amplitude was 1.2%.

[0102] Furthermore, the surface SEM morphology of GH4169 alloy after Pt treatment is as follows: Figure 2 As shown, the XRD results of GH4169 alloy after Pt treatment are as follows: Figure 3 As shown in the figure. The surface SEM morphology of GH4169 alloy after Pt treatment and oxidation at 900℃ for 200 hours is shown in the figure. Figure 5 As shown in the figure, the cross-sectional SEM morphology of GH4169 alloy after Pt treatment and oxidation at 900℃ for 200 h is as follows. Figure 6 As shown.

[0103] In this embodiment, a Pt coating was prepared on GH4169 superalloy using the aforementioned chemical plating technique. A high-temperature oxidation / creep experiment was conducted at 900℃, demonstrating that this new method can effectively reduce oxidation weight gain and increase creep rupture time. This improves the high-temperature oxidation and creep resistance of nickel-based superalloys.

[0104] Example 4

[0105] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is RR1000 alloy, and the specific steps of the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys are as follows:

[0106] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the surface of the workpieces was removed by alkaline washing with a 0.2 mol / L alkaline solution at 65℃ for 1 hour to remove oil stains, and by acid washing with a 0.10 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides, resulting in a clean RR1000 high-temperature alloy.

[0107] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0108] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.10 mol / L to obtain the dilute hydrochloric acid solution.

[0109] S2. Coating: A 1.0 μm thick Re coating is grown on the clean RR1000 high-temperature alloy surface of S1 using high-temperature magnetron sputtering technology. The Re coating growth temperature is 650℃ and the deposition rate is 10 nm / min, resulting in an RR1000 high-temperature alloy with a coating.

[0110] S3. Overall heat treatment: The RR1000 high-temperature alloy with coating S2 was annealed in an argon atmosphere at 550℃ for 10h to finally obtain an RR1000 high-temperature alloy with a Re coating thickness of 1.0μm and improved high-temperature service performance.

[0111] The oxidation performance of the RR1000 superalloy with a Re coating thickness of 1.0 μm prepared in this embodiment was tested, and the oxidation kinetic curves of the alloy after oxidation at 900℃ for 3000 h with / without Re treatment were obtained. The weight gain after Re treatment was approximately 3.5 mg / cm³. 2 Only the matrix (10.2 mg / cm³) 2 34.3% of ).

[0112] High-temperature creep tests were conducted on the RR1000 high-temperature alloy with a Re coating thickness of 1.0 μm prepared in this embodiment. Creep elongation-time curves at 900℃ and 25 MPa were obtained for the alloy before and after Re coating treatment. The creep elongation-time curves show that the creep fracture time after Re coating treatment is 336.9 h, which is greater than the 280.8 h of the untreated alloy, representing an improvement of 19.97%.

[0113] The high-temperature fatigue performance of the RR1000 high-temperature alloy with a Re coating thickness of 1.0 μm prepared in this embodiment was tested. Under low-cycle fatigue conditions of 900℃ and a total strain amplitude of 0.8-1.2%, when the total strain amplitude was 0.8%, the fatigue life of the coated sample was 1.16 times that of the substrate; when the total strain amplitude was 1%, the fatigue life of the coated sample was 1.38 times that of the substrate; and when the total strain amplitude was 1.2%, the fatigue life of the coated sample was 1.39 times that of the substrate.

[0114] In this embodiment, a Re coating was prepared on the RR1000 high-temperature alloy using the aforementioned magnetron sputtering technique. Long-term oxidation / creep / fatigue tests were conducted at 900℃, demonstrating that this new method can effectively reduce the oxidation weight gain of the RR1000 high-temperature alloy and improve creep life and fatigue life. This enhances the high-temperature oxidation resistance, creep resistance, and fatigue resistance of the RR1000 alloy.

[0115] Example 5

[0116] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is 0Cr25Ni20MoWV alloy, and the specific steps of the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys are as follows:

[0117] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the specimens were subjected to alkaline washing with a 0.2 mol / L alkaline solution at 65℃ for 1 hour to remove oil stains from the surface of the workpieces to be plated, and acid washing with a 0.10 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides from the surface of the workpieces to be plated, resulting in a clean 0Cr25Ni20MoWV high-temperature alloy.

[0118] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0119] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.10 mol / L to obtain the dilute hydrochloric acid solution.

[0120] S2. Coating: A 2.0 μm thick Pt coating is grown on the clean 0Cr25Ni20MoWV high-temperature alloy surface of S1 using high-temperature magnetron sputtering technology. The Pt coating growth temperature is 700℃ and the deposition rate is 8 nm / min, resulting in a 0Cr25Ni20MoWV high-temperature alloy with a coating.

[0121] S3. Overall heat treatment: The 0Cr25Ni20MoWV high-temperature alloy with coating in S2 is annealed in an argon atmosphere at 600℃ for 5 hours, and finally a 0Cr25Ni20MoWV high-temperature alloy with a Pt coating thickness of 2.0μm with improved high-temperature service performance is obtained.

[0122] The oxidation performance of the 0Cr25Ni20MoWV superalloy with a Pt coating thickness of 2.0 μm prepared in this embodiment was tested, and the oxidation kinetic curves of the alloy after oxidation at 900℃ for 300 h with and without Re treatment were obtained. The weight gain after Re treatment was approximately 0.5 mg / cm³. 2 Only the matrix (1.2 mg / cm³) 2 41.6% of ).

[0123] High-temperature creep tests were conducted on the 0Cr25Ni20MoWV superalloy with a Pt coating thickness of 2.0 μm prepared in this embodiment. Creep elongation-time curves at 900℃ and 25 MPa were obtained for the alloy before and after Pt plating. The creep elongation-time curves show that the creep fracture time after Pt plating was 142.2 h, which is greater than the 115.6 h of the untreated alloy, representing an improvement of 23.01%.

[0124] The high-temperature fatigue performance of the 0Cr25Ni20MoWV high-temperature alloy with a Pt coating thickness of 2.0 μm prepared in this embodiment was tested. Under low-cycle fatigue conditions of 900℃ and a total strain amplitude of 0.8-1.2%, when the total strain amplitude was 0.8%, the fatigue life of the coated sample was 1.36 times that of the substrate; when the total strain amplitude was 1%, the fatigue life of the coated sample was 1.40 times that of the substrate; and when the total strain amplitude was 1.2%, the fatigue life of the coated sample was 1.42 times that of the substrate.

[0125] In this embodiment, a Pt coating was prepared on the 0Cr25Ni20MoWV superalloy using the aforementioned magnetron sputtering technique. Long-term oxidation / creep / fatigue tests were conducted at 900℃, demonstrating that this novel method effectively reduces the oxidation weight gain of the 0Cr25Ni20MoWV superalloy and improves its creep life and fatigue life. This enhances the high-temperature oxidation resistance, creep resistance, and fatigue resistance of the 0Cr25Ni20MoWV superalloy.

[0126] Example 6

[0127] A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, wherein the nickel-based superalloy is Inconel 617 alloy, and the specific steps of the surface treatment technology for improving the high-temperature service performance of nickel-based superalloys are as follows:

[0128] S1. Surface pretreatment: First, according to the national standard size of anodized 20×10×2mm... 3 Cut test specimens: rod-shaped specimens were cut according to the national standard dimensions for creep and fatigue. Then, the specimens were subjected to alkaline washing with a 0.2 mol / L alkaline solution at 65℃ for 1 hour to remove oil stains from the surface of the workpieces to be plated, and acid washing with a 0.10 mol / L dilute hydrochloric acid solution for 3 minutes to remove oxides from the surface of the workpieces to be plated, resulting in a clean Inconel 617 high-temperature alloy.

[0129] The alkaline solution needs to be prepared on-site. Specifically, sodium hydroxide is weighed using an electronic balance (accurate to 0.0001) to prepare a 0.2 mol / L alkaline solution.

[0130] The dilute hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid needs to be diluted to 0.10 mol / L to obtain the dilute hydrochloric acid solution.

[0131] S2. Coating: The cleaned Inconel 617 high-temperature alloy from S1 is placed in a mixed solution of triammonium octachlorodiruthenium(IV) diazoate solution and hydrochloric acid solution for 1 hour. Hydrochloric acid is added to adjust the pH to below 3. The coating temperature is controlled at 70℃, the pulse on-time is 0.008ms, the pulse off-time is 50ms, and the average current density is 2A / dm³. 2 This yields a coated Inconel 617 high-temperature alloy; wherein,

[0132] The triammonium octachloro-2-ruthenium(IV)-2-carboxylic acid solution needs to be prepared on-site. Specifically, weigh out the triammonium octachloro-2-ruthenium(IV)-2-carboxylic acid solution (K3[Ru2NCl8(H2O)2]) and prepare it into a 0.15 mol / L solution.

[0133] The hydrochloric acid solution needs to be prepared on-site. Specifically, the hydrochloric acid is diluted to 0.10 mol / L to obtain a sulfuric acid solution.

[0134] S3. Overall heat treatment: The Inconel 617 high-temperature alloy with coating from S2 was annealed in an argon atmosphere at 650℃ for 10 hours to finally obtain an Inconel 617 high-temperature alloy with a Ru coating thickness of 0.5μm and improved high-temperature service performance.

[0135] The oxidation performance of the Inconel 617 superalloy with a Ru coating thickness of 0.5 μm prepared in this embodiment was tested, and the oxidation kinetics curves of the alloy after oxidation at 850℃ for 300 h with / without Ru treatment were obtained. Its oxidation weight gain was approximately 0.7 mg / cm³. 2 Only the matrix (1.42 mg / cm³) 249.29% of the total. According to the test method for determining the oxidation resistance of steel and high-temperature alloys (National Standard 5258-2000), the national standard can determine that its oxidation resistance reaches the level of complete oxidation resistance.

[0136] High-temperature creep tests were conducted on the Inconel 617 high-temperature alloy with a Ru coating thickness of 0.5 μm prepared in this embodiment. Creep elongation-time curves at 850℃ and 25 MPa were obtained for the alloy before and after Ru plating. The creep elongation-time curves show that the creep fracture time after Ru plating was 42.1 h, which is greater than the 55.3 h of the untreated alloy, representing an improvement of 31.35%.

[0137] High-temperature fatigue performance tests were conducted on the Inconel 617 high-temperature alloy with a Ru coating thickness of 0.5 μm prepared in this embodiment. Under low-cycle fatigue conditions of 850℃ and a total strain amplitude of 0.8-1.2%, when the total strain amplitude was 0.8%, the fatigue life of the coated sample was 1.36 times that of the substrate; when the total strain amplitude was 1%, the fatigue life of the coated sample was 1.40 times that of the substrate; and when the total strain amplitude was 1.2%, the fatigue life of the coated sample was 1.42 times that of the substrate.

[0138] In this embodiment, a Ru coating was prepared on Inconel 617 superalloy using the aforementioned electroplating technique. Long-term oxidation / creep / fatigue tests at 850°C were conducted, demonstrating that this new method effectively reduces the oxidation weight gain of Inconel 617 superalloy and improves creep life and fatigue life. This enhances the high-temperature oxidation resistance, creep resistance, and fatigue resistance of Inconel 617 superalloy.

[0139] The above-described surface treatment technology of the present invention, which improves the high-temperature service performance of nickel-based superalloys, can solve the technical problems existing in the prior art, such as the easy cracking failure of brittle oxides during long-term service at temperatures above 850°C, the weakening effect of high-temperature oxidation on creep and fatigue performance, the continuous expansion and deterioration of structural defects in the coating under long-term service conditions above 850°C, significant weight gain due to oxidation, and low reliability of materials under high-temperature conditions.

[0140] The precious metal coating technology used in this invention can effectively avoid the defects of existing coating components that are prone to forming brittle Al2O3 and Cr2O3 oxides, which can lead to coating cracking and peeling; at the same time, it can synergistically improve the material's oxidation resistance, creep resistance and fatigue resistance.

[0141] The Pt, Ru, and Re noble metal coatings used in this invention are thin, inexpensive, easy to operate, and suitable for workpieces with complex shapes.

[0142] In the coating of this invention, the noble metal elements can diffuse into the generated oxide during high-temperature service, thereby improving its plasticity and mitigating the decline in room temperature strength and plasticity of the alloy after long-term oxidation.

[0143] This invention promotes the stable formation of oxides under service conditions by performing heat treatment after coating, significantly improving high-temperature oxidation resistance, reducing oxidation weight gain, and further improving high-temperature creep resistance and fatigue resistance.

[0144] In summary, compared with traditional high-temperature alloy coating structures and preparation techniques, the method of this invention employs surface pretreatment, coating plating, and overall heat treatment of nickel-based high-temperature alloys to further improve their oxidation resistance, creep resistance, and fatigue resistance in high-temperature service environments without affecting their room temperature strength and plasticity. This method is simple, easy to operate, low in cost, and highly efficient, and can achieve a synergistic improvement in oxidation resistance, creep resistance, and fatigue resistance under long-term service conditions at 850℃, which is conducive to large-scale industrial application and promotion.

[0145] It should be understood that the term "and / or" 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, or B existing alone. A and B can be singular or plural. Additionally, the character " / " in this article generally indicates an "or" relationship between the preceding and following related objects, but it can also represent an "and / or" relationship. Please refer to the context for a more accurate understanding.

[0146] In this invention, "at least one" means one or more, and "more than one" means two or more. "At least one of the following" or similar expressions refer to any combination of these items, including any combination of a single item or a plurality of items. For example, at least one of a, b, or c can represent: a, b, c, ab, ac, bc, or abc, where a, b, and c can be a single item or multiple items.

[0147] It should be understood that, in various embodiments of the present invention, the order of the above-mentioned process numbers does not imply the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0148] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A surface treatment technology for improving the high-temperature service performance of nickel-based superalloys, characterized in that, The surface treatment technology includes: firstly, pretreating the surface of the nickel-based superalloy; then, depositing a coating on the pretreated surface; and finally, performing overall heat treatment on the coated nickel-based superalloy to obtain a coated nickel-based superalloy with high oxidation resistance, high creep resistance, and high fatigue resistance.

2. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 1, characterized in that, The surface treatment technology specifically includes the following steps: S1. Surface pretreatment: The surface of the nickel-based superalloy is pretreated to remove oil and oxides, resulting in a clean nickel-based superalloy. S2. Coating: The surface of the clean nickel-based superalloy obtained in S1 is coated with a coating that has high oxidation resistance, high creep resistance and high fatigue resistance in a high-temperature environment by electroplating, chemical plating or magnetron sputtering, to obtain a coated nickel-based superalloy. S3. Overall heat treatment: The coated nickel-based superalloy obtained in S2 is heat-treated to obtain a nickel-based superalloy with improved high-temperature service performance.

3. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, The pretreatment of S1 includes: alkaline washing with hot alkaline solution to remove oil stains from the surface of the nickel-based superalloy, and acid washing with dilute hydrochloric acid solution to remove oxides from the surface of the nickel-based superalloy.

4. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, S1 nickel-based superalloys include wrought superalloys, cast superalloys, powder metallurgy superalloys, and oxide dispersion strengthened alloys.

5. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, The coating chemical composition in S2 is at least one of Pt, Re, and Ru, and the coating thickness is 0.1-10 μm.

6. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, In S2, electroplating, electroless plating, or magnetron sputtering are selected for coating based on the coating composition and the shape and roughness of the substrate surface; the coating will decompose and disperse in the oxides generated during the high-temperature service of the nickel-based superalloy.

7. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, The heat treatment in S3 is annealing, which is carried out in an argon atmosphere at a temperature of 400-750℃ for 2-24 hours.

8. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, The nickel-based superalloy with improved high-temperature service performance in S3 showed reduced oxidation weight gain compared to the matrix at 900℃ and 200h, improved creep life under creep conditions of 900℃ and 25MPa, and improved creep life under creep conditions of 900℃ and 50MPa.

9. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 8, characterized in that, In S3, the oxidation weight gain at 900℃ for 200h was reduced by at least 67% in the nickel-based superalloy containing the Re coating compared to the substrate; Under creep conditions of 900℃ and 25MPa, the creep life of nickel-based superalloys with Pt coating can be increased by up to 23.01% compared with the substrate; the creep life of the substrate is 115.6h, and the creep life of the treated workpiece is 142.2h. In nickel-based superalloys with Re coating, under creep conditions of 900℃ and 50MPa, the creep life of the substrate is 64.8h, and the creep life of the treated workpiece is 75.5h.

10. The surface treatment technology for improving the high-temperature service performance of nickel-based superalloys according to claim 2, characterized in that, The S3 nickel-based superalloy with Ru coating exhibits the following fatigue life under low-cycle fatigue conditions at 900℃ and a total strain amplitude of 0.8-1.2%: when the total strain amplitude is 0.8%, the fatigue life is 1.17 times that of the substrate; when the total strain amplitude is 1%, the fatigue life is 1.2 times that of the substrate; and when the total strain amplitude is 1.2%, the fatigue life is 1.28 times that of the substrate.

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