Wear-resistant sealing coating for aviation rotor engine and preparation method of wear-resistant sealing coating

Abstract

The invention provides a wear-resistant sealing coating for an aviation rotor engine and a preparation method of the wear-resistant sealing coating, the wear-resistant sealing coating comprises a transition layer and a surface layer, and the transition layer covers the molded surface of the rotor engine, specifically, the transition layer is a NiCrAlY phase; the transition layer is covered with the surface layer, the surface layer specifically comprises a NiCr-Cr3C2 bonding hard phase and a Mo (at) Ag (at) Ni metal lubricating phase, and the Mo (at) Ag (at) Ni metal lubricating phase is core-shell structure composite powder with Mo coated with Ag and Ag coated with Ni. By combining the good lubricating effect of the Mo (at) Ag (at) Ni metal lubricating phase of the core-shell structure and the good wear resistance of the NiCr-Cr3C2 metal ceramic-based wear-resistant coating, the wear resistance of a traditional sealing coating under the simulated engine working condition is greatly improved, and the problem of failure of a coating material after variable-temperature and high-load cyclic friction is solved; the wear-resistant service life of the coating is prolonged, a theoretical basis is provided for application of the wear-resistant sealing coating on an engine, and actual requirements can be met.

Description

Technical Field

[0001] The invention belongs to the field of aviation engines, and in particular to a self-lubricating and wear-resistant sealing coating on the end surface of a rotor engine under a simulated aviation rotor engine running state and a preparation method thereof. Background Art

[0002] When the aircraft rotor engine is working at high speed, the sealing plate and the rotor profile rub rapidly, causing serious wear of the rotor profile and the sealing plate. This wear will gradually reduce the sealing performance and may cause leakage or sealing failure, which will seriously affect the working stability and service life of the engine system. In order to reduce the serious wear caused by the friction between the sealing plate and the base material, and thus improve the working stability and service life of the engine system. The researchers proposed to apply a wear-resistant sealing coating on the rotor profile to reduce the friction between the sealing plate and the base, and then protect the base material. Among them, the traditional sealing coating includes NiCrAlY metal-based wear-resistant coating and NiCr-Cr3C2 metal ceramic-based wear-resistant coating. The excellent high-temperature oxidation resistance and wear resistance of NiCrAlY alloy in high-temperature environment make NiCrAlY metal-based wear-resistant coating show certain advantages and applications in dealing with wide temperature range lubrication and wear resistance. NiCr-Cr3C2 is a commonly used metal ceramic powder that combines the advantages of NiCr alloy and Cr3C2 powder, and has excellent comprehensive properties such as wear resistance, corrosion resistance and oxidation resistance at high temperature. However, both types of coatings have certain problems. The mechanical properties of NiCrAlY metal-based wear-resistant coatings are far inferior to those of NiCr-Cr3C2 metal ceramic-based wear-resistant coatings, which also leads to the fact that the wear resistance of NiCrAlY metal-based wear-resistant coatings is far inferior to that of NiCr-Cr3C2 metal ceramic-based wear-resistant coatings. The lubrication performance of pure NiCr-Cr3C2 metal ceramic-based wear-resistant coatings is poor. Therefore, these two types of coatings show problems such as short wear life and poor lubricity when they are in the service environment of variable temperature, high speed and high load of the engine. Therefore, it is urgent to develop a new type of long-life wear-resistant sealing coating to solve the sealing problem of the rotary engine. Summary of the invention

[0003] In order to solve the problems existing in the prior art, the present invention provides a wear-resistant sealing coating for an aviation rotor engine and a preparation method thereof, which combines the good lubrication effect of the Mo@Ag@Ni metal lubricating phase with a core-shell structure and the good wear resistance of the NiCr-Cr3C2 metal ceramic-based wear-resistant coating, greatly improves the wear resistance of traditional sealing coatings under simulated engine working conditions, solves the failure problem of coating materials after temperature change and high-load cyclic friction, and improves the wear-resistant service life of the coating, provides a theoretical basis for the application of such wear-resistant sealing coatings on engines, and can meet actual needs.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a wear-resistant sealing coating for an aviation rotary engine, comprising a transition layer and a surface layer, wherein the transition layer is covered on the rotary engine profile, and is specifically a NiCrAlY phase; the surface layer is covered on the transition layer, and specifically comprises a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase, wherein the Mo@Ag@Ni metal lubricating phase is a core-shell structure composite powder of Ag coating Mo and Ni coating Ag.

[0005] Furthermore, the surface layer contains 20% to 30% of Mo@Ag@Ni metal lubrication phase and 70% to 80% of NiCr-Cr3C2 bonding hard phase in terms of mass percentage.

[0006] Furthermore, in terms of weight percentage, in the Mo@Ag@Ni metal lubricating phase, the content of Mo is 40wt%, the content of Ag is 40wt%, and the content of Ni is 20wt%.

[0007] Furthermore, the thickness of the transition layer is 100 μm to 110 μm, and the thickness of the surface layer is 380 μm to 400 μm.

[0008] Furthermore, the rotor engine profile is made of nickel-based high-temperature alloy.

[0009] The present invention also provides a method for preparing a wear-resistant sealing coating for an aviation rotary engine, and the specific steps are as follows:

[0010] S1 deposits NiCrAlY powder on the rotor engine profile to obtain a transition layer;

[0011] S2: NiCr-Cr3C2 powder and Mo@Ag@Ni powder are mixed and dried to obtain composite powder, and the composite powder is deposited on the transition layer to obtain a surface layer, wherein the Mo@Ag@Ni metal lubricating phase is a composite powder with a core-shell structure of Ag coating Mo and Ni coating Ag;

[0012] The S3 surface layer and the transition layer are combined to obtain a self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines.

[0013] Furthermore, in S1 and S2, NiCrAlY powder is sprayed on the rotor engine surface by plasma spraying technology to deposit a transition layer; and composite powder is sprayed on the transition layer by plasma spraying technology to deposit a surface layer.

[0014] Furthermore, in S2, the surface layer contains 20% to 30% of Mo@Ag@Ni metal lubrication phase and 70% to 80% of NiCr-Cr3C2 bonding hard phase by mass percentage.

[0015] Furthermore, in S2, by weight percentage, in the Mo@Ag@Ni metal lubricating phase, the content of Mo is 40wt%, the content of Ag is 40wt%, and the content of Ni is 20wt%.

[0016] Furthermore, in S1, the thickness of the transition layer is 100 μm to 110 μm; and the thickness of the surface layer in S2 is 380 μm to 400 μm.

[0017] Compared with the prior art, the present invention has at least the following beneficial effects:

[0018] The present invention provides a wear-resistant sealing coating for an aviation rotary engine, comprising a transition layer covering the rotary engine profile and a surface layer covering the transition layer, wherein the transition layer is a NiCrAlY phase, and the transition layer provides a good bonding layer for the surface layer and the substrate, and the surface layer comprises a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase, which can be well matched with the transition layer to improve the bonding force, and the presence of the NiCr-Cr3C2 bonding hard phase can well improve the hardness of the coating, and its hardness is more than 2.3 times that of a traditional wear-resistant coating (NiCrAlY-Mo@Ag@Ni); the Mo@Ag@Ni metal lubricating phase with a core-shell structure can greatly limit the high-temperature dissipation of Ag, greatly improve the high-temperature cyclic tribological properties of the coating, solve the failure problem of the coating material after high-temperature multi-cycle friction, and improve the cyclic wear-resistant lubrication life of the coating, which can meet actual needs.

[0019] Based on the presence of Ag, Mo and NiCr-Cr3C2, the high-temperature wear resistance and lubricity of the coating are greatly improved in the entire test temperature range. Under the simulation of the actual operating conditions of the engine, the lubrication performance of the coating of the present invention is improved by about 0.2 compared with the traditional wear-resistant coating (NiCrAlY-Mo@Ag@Ni), and its wear resistance is improved by about 15 times compared with the traditional wear-resistant coating (NiCrAlY-Mo@Ag@Ni). BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the specific implementation modes of the present invention, the drawings required for use in the description of the specific implementation modes will be briefly introduced below. Obviously, the drawings described below are some implementation modes of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 The cross-sectional morphology A and element distribution (BE) of the composite coating of Example 1.

[0022] Figure 2This is a comparison chart of the friction coefficient curves of the composite coating of Example 1 and the NiCrAlY-Mo@Ag@Ni coating (comparison group 1) under simulated engine environment.

[0023] Figure 3 This is a comparison chart of the wear rates of the composite coating of Example 1 and the NiCrAlY-Mo@Ag@Ni coating (comparison group 1) under a simulated engine environment.

[0024] Figure 4 The friction coefficient of the composite coating of Example 1 after 5 cycles of friction in a simulated engine environment.

[0025] Figure 5 This is the wear rate of the composite coating of Example 1 after 5 cycles of friction in a simulated engine environment. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] The present invention provides a wear-resistant sealing coating for an aviation rotary engine, which comprises a transition layer and a surface layer in sequence, wherein the transition layer is covered on a substrate and is a NiCrAlY phase; the surface layer is covered on the transition layer and comprises a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubrication phase; and the substrate is a rotary engine profile made of a nickel-based high-temperature alloy.

[0028] The thickness of the transition layer is 100 μm to 110 μm, and the thickness of the surface layer is 380 μm to 400 μm.

[0029] Furthermore, in terms of mass percentage, the Mo@Ag@Ni metal lubrication phase accounts for 20% to 30%, and the NiCr-Cr3C2 bonding hard phase accounts for 70% to 80%;

[0030] Furthermore, the Mo@Ag@Ni metal lubricating phase is a composite powder of a core-shell structure of Ag-coated Mo and Ni-coated Ag, wherein Mo accounts for 40wt%, Ag accounts for 40wt%, and Ni accounts for 20wt%.

[0031] The present invention provides a method for preparing a wear-resistant sealing coating for an aviation rotary engine, comprising the following steps:

[0032] Step 1, put NiCr-Cr3C2 powder and Mo@Ag@Ni powder into a three-dimensional mixer and mix them for 12 to 24 hours until they are evenly mixed, and then put them into an oven at 80°C to obtain a composite powder;

[0033] Step 2: On the substrate, the NiCrAlY phase is sprayed by plasma spraying technology, that is, the NiCrAlY phase is deposited on the Inconel718 high temperature alloy by plasma spraying technology. On top, a transition layer is formed;

[0034] Step 3: Spray the composite powder onto the transition layer by plasma spraying technology to form a surface layer comprising a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase, thereby obtaining a densely structured NiCr-Cr3C2-Mo@Ag@Ni composite coating, i.e., a self-lubricating, wear-resistant, sealing multifunctional coating for an aviation rotor engine.

[0035] Preferably, the specific parameters for preparing the transition layer and the surface layer using plasma spraying technology are as follows:

[0036]

[0037] Example 1

[0038] Step 1: According to the mass percentage, 20% Mo@Ag@Ni powder and 80% NiCr-Cr3C2 powder are placed in a three-dimensional mixer and mixed for 24 hours to mix evenly, and then placed in an oven at 80°C to obtain a composite powder;

[0039] Step 2: On the substrate, the NiCrAlY phase is sprayed by plasma spraying technology, that is, the NiCrAlY phase is deposited on the Inconel718 high temperature alloy by plasma spraying technology. On the surface, a transition layer is formed, and the thickness of the transition layer is 107 μm. Figure 1 shown.

[0040] Step 3: Spray the composite powder onto the transition layer by plasma spraying technology to form a surface layer comprising a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase. The thickness of the surface layer is 391 μm, thereby obtaining a densely structured NiCr-Cr3C2-Mo@Ag@Ni composite coating, i.e., a self-lubricating, wear-resistant, sealing multifunctional coating for an aviation rotor engine.

[0041] The performance of the self-lubricating, wear-resistant and sealing multifunctional coating for the obtained aviation rotor engine was tested: the cross-sectional hardness of the coating was 779.52±19.3HV0.2; the bonding strength was 44±2.6Mpa. Figure 1The cross-sectional morphology and element distribution of the composite coating show that the cross-sectional morphology of the coating presents a typical layered structure with fewer holes and unmelted particles. The metal lubricating phase is evenly distributed in the NiCr-Cr3C2 hard bonding phase in the form of lamellae, which is beneficial for the coating to provide continuous lubrication and wear resistance during the friction process.

[0042] Friction test under simulated engine working conditions (temperature change from RT to 800℃, temperature change rate 10℃ / min, ball-on-disk contact, dual ball material Si3N4, rotation radius 5mm, rotation speed 1000prm, load 15N): friction coefficient is stable at about 0.25-0.45, wear rate: 4.04×10 -5 mm3N -1 m -1 The friction coefficient and wear rate of the composite coating are as follows: Figure 2 and Figure 3 As shown. The friction coefficient of the coating remains in the range of 0.25 to 0.45 during the entire friction process. During the entire friction process, the NiCr-Cr3C2 bonding hard phase in the coating and the lubricating glaze film composed of ternary metal oxides formed in the coating at high temperature provide the coating with good wear resistance. At the same time, the presence of lubricating phases such as Ag and Mo in the coating provides the coating with good lubrication performance.

[0043] The obtained self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines was subjected to multi-cycle tribological performance tests: multi-cycle friction test (temperature change from RT to 800 °C (one cycle), temperature change rate 10 °C / min, ball-disc contact, dual ball material Si3N4, rotation radius 5 mm, rotation speed 1000prm, load 15N): friction coefficient 0.25-0.55, wear rate after 5 cycles: 5.88×10 -5 mm 3 N -1 m -1 . Figure 4 The friction coefficient curve of the composite coating under different friction cycles is shown. The friction coefficient curve of the composite coating is relatively stable during the 5-cycle friction test and remains in the range of 0.25 to 0.55. At the same time, the wear rate of the coating after the first and fifth friction cycles ( Figure 5 ), it can be seen that with the increase of cycle number, the wear of the composite coating remains at about 5.88×10 -5 mm 3 N -1 m -1 . Combined Figure 4 and 5 It was found that after multi-cycle friction tests, the NiCr-Cr3C2-Mo@Ag@Ni composite coating has stable multi-cycle lubrication performance, continuous lubrication and excellent wear resistance.

[0044] Example 2

[0045] Step 1: By mass percentage, 30% Mo@Ag@Ni powder and 70% NiCr-Cr3C2 powder were placed in a three-dimensional mixer and mixed for 18 hours until they were evenly mixed, and then placed in an oven at 80°C to obtain a composite powder;

[0046] Step 2: On the substrate, the NiCrAlY phase is sprayed by plasma spraying technology, that is, the NiCrAlY phase is deposited on the Inconel718 high temperature alloy by plasma spraying technology. A transition layer is formed on the substrate, and the thickness of the transition layer is 110 μm.

[0047] Step 3: Spray the composite powder onto the transition layer by plasma spraying technology to form a surface layer comprising a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase. The thickness of the surface layer is 380 μm, thereby obtaining a densely structured NiCr-Cr3C2-Mo@Ag@Ni composite coating, i.e., a self-lubricating, wear-resistant, sealing multifunctional coating for an aviation rotor engine.

[0048] The performance of the obtained self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines was tested: the cross-sectional hardness of the coating was 728.1±17.3HV0.2; the bonding strength was 42±3.1Mpa; the friction test under simulated engine working conditions (RT to 800℃ temperature change, temperature change rate 10℃ / min, ball-disc contact, dual ball material Si3N4, rotation radius 5mm, rotation speed 1000prm, load 15N): the friction coefficient was stable at about 0.21-0.39, and the wear rate was 5.45×10 -5 mm 3 N -1 m -1 .

[0049] The obtained self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines was subjected to multi-cycle tribological performance tests: multi-cycle friction test (temperature change from RT to 800 °C (one cycle), temperature change rate of 10 °C / min, ball-disc contact, dual ball material Si3N4, rotation radius of 5 mm, rotation speed of 1000prm, load of 15N): friction coefficient 0.21-0.46, wear rate after 5 cycles: 7.45×10 -5 mm 3 N -1 m -1 .

[0050] Example 3

[0051] Step 1: According to the mass percentage, 25% Mo@Ag@Ni powder and 75% NiCr-Cr3C2 powder are placed in a three-dimensional mixer and mixed for 12 hours, and then placed in an oven at 80°C to obtain a composite powder;

[0052] Step 2: On the substrate, the NiCrAlY phase is sprayed by plasma spraying technology, that is, the NiCrAlY phase is deposited on the Inconel718 high temperature alloy by plasma spraying technology. A transition layer is formed on the substrate, and the thickness of the transition layer is 100 μm.

[0053] Step 3: Spray the composite powder onto the transition layer by plasma spraying technology to form a surface layer comprising a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase. The thickness of the surface layer is 400 μm, thereby obtaining a densely structured NiCr-Cr3C2-Mo@Ag@Ni composite coating, i.e., a self-lubricating, wear-resistant, sealing multifunctional coating for an aviation rotor engine.

[0054] The performance of the obtained self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines was tested: the cross-sectional hardness of the coating was 790.52±19.3HV0.2; the bonding strength was 47±1.5Mpa; the friction test under simulated engine working conditions (RT to 800℃ temperature change, temperature change rate 10℃ / min, ball-disc contact, dual ball material Si3N4, rotation radius 5mm, rotation speed 1000prm, load 15N): the friction coefficient was stable at about 0.35-0.66, and the wear rate was 3.26×10 -5 mm 3 N -1 m -1 .

[0055] The obtained self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines was subjected to multi-cycle tribological performance tests: multi-cycle friction test (temperature change from RT to 800 °C (one cycle), temperature change rate 10 °C / min, ball-disc contact, dual ball material Si3N4, rotation radius 5 mm, rotation speed 1000prm, load 15N): friction coefficient 0.35-0.76, wear rate after 5 cycles: 5.26×10 -5 mm 3 N -1 m -1 .

[0056] Comparative experiment: Example 1 (NiCrAlY is selected as the bonding phase in the comparative experiment)

[0057] Step 1: According to the mass percentage, 20% Mo@Ag@Ni powder and 80% NiCrAlY powder are placed in a three-dimensional mixer and mixed for 24 hours to be uniform, and then placed in an oven at 80° C. to obtain a composite powder;

[0058] Step 2: On the substrate, the NiCrAlY phase is sprayed by plasma spraying technology, that is, the NiCrAlY phase is deposited on the Inconel 718 high temperature alloy by plasma spraying technology. A transition layer is formed.

[0059] Step 3: Spray the composite powder on the transition layer by plasma spraying technology to form a surface layer containing NiCrAlY bonding phase and Mo@Ag@Ni metal lubrication phase, that is, to obtain a dense NiCrAlY-Mo@Ag@Ni composite coating.

[0060] The performance of the obtained NiCrAlY-Mo@Ag@Ni composite coating (comparative experiment) was tested: the surface hardness of the coating was 332.2±17.5HV0.2; the bonding strength was 44.0±2.2Mpa; the friction test under simulated engine working conditions (RT to 800℃ temperature change, temperature change rate 10℃ / min, ball-disc contact, dual ball material Si3N4, rotation radius 5mm, rotation speed 1000prm, load 15N): the friction coefficient was in the range of 0.35-0.65, and the wear rate was 64.0×10 -5 mm 3 N -1 m -1 ,like Figure 3 shown.

[0061] By comparing the tribological properties of NiCrAlY-Mo@Ag@Ni composite coating and NiCr-Cr3C2-Mo@Ag@Ni composite coating, it is found that the presence of NiCr-Cr3C2 bonding hard phase greatly improves the mechanical properties and wear resistance of the coating. This also enables the NiCr-Cr3C2-Mo@Ag@Ni composite coating to maintain good lubrication and wear resistance after multiple friction cycles, greatly extending the lubrication and wear life of the coating.

[0062] Finally, it should be noted that the above-described embodiments are only specific implementations of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention is described in detail with reference to the above-described embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-described embodiments within the technical scope disclosed by the present invention, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A wear-resistant sealing coating for an aviation rotary engine, characterized in that: It includes a transition layer and a surface layer. The transition layer covers the rotor engine surface and is specifically a NiCrAlY phase. The surface layer covers the transition layer and specifically includes a NiCr-Cr3C2 bonding hard phase and a Mo@Ag@Ni metal lubricating phase. The Mo@Ag@Ni metal lubricating phase is a core-shell structure composite powder of Ag coating Mo and Ni coating Ag.

2. The wear-resistant sealing coating for an aircraft rotary engine according to claim 1, characterized in that: Calculated by mass percentage, the surface layer contains 20% to 30% of Mo@Ag@Ni metal lubrication phase and 70% to 80% of NiCr-Cr3C2 bonding hard phase.

3. A wear-resistant sealing coating for an aircraft rotary engine according to claim 1 or 2, characterized in that: In terms of weight percentage, in the Mo@Ag@Ni metal lubricating phase, the content of Mo is 40wt%, the content of Ag is 40wt%, and the content of Ni is 20wt%.

4. The wear-resistant sealing coating for an aircraft rotary engine according to claim 1, characterized in that: The thickness of the transition layer is 100 μm to 110 μm, and the thickness of the surface layer is 380 μm to 400 μm.

5. The wear-resistant sealing coating for an aircraft rotary engine according to claim 1, characterized in that: The rotor engine profile is made of nickel-based high-temperature alloy.

6. A method for preparing a wear-resistant sealing coating for an aviation rotary engine, characterized in that: The specific steps are as follows: S1 deposits NiCrAlY powder on the rotor engine profile to obtain a transition layer; S2: NiCr-Cr3C2 powder and Mo@Ag@Ni powder are mixed and dried to obtain composite powder, and the composite powder is deposited on the transition layer to obtain a surface layer, wherein the Mo@Ag@Ni metal lubricating phase is a composite powder with a core-shell structure of Ag coating Mo and Ni coating Ag; The S3 surface layer and the transition layer are combined to obtain a self-lubricating, wear-resistant and sealing multifunctional coating for aviation rotor engines.

7. The method for preparing a wear-resistant sealing coating for an aircraft rotary engine according to claim 6, characterized in that: In S1 and S2, NiCrAlY powder is sprayed on the rotor engine surface by plasma spraying technology to deposit a transition layer; and composite powder is sprayed on the transition layer by plasma spraying technology to deposit a surface layer.

8. The method for preparing a wear-resistant sealing coating for an aircraft rotary engine according to claim 6, characterized in that: In S2, the surface layer contains 20% to 30% of Mo@Ag@Ni metal lubricating phase and 70% to 80% of NiCr-Cr3C2 bonding hard phase by mass percentage.

9. The method for preparing a wear-resistant sealing coating for an aircraft rotary engine according to claim 6, characterized in that: In S2, by weight percentage, in the Mo@Ag@Ni metal lubricating phase, the content of Mo is 40wt%, the content of Ag is 40wt%, and the content of Ni is 20wt%.

10. The method for preparing a wear-resistant sealing coating for an aircraft rotary engine according to claim 1, characterized in that: In S1, the thickness of the transition layer is 100 μm to 110 μm; in S2, the thickness of the surface layer is 380 μm to 400 μm.

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