CN110616395A - High-temperature micro-motion resistant coating for micro-texturing of sawtooth crown surface of gas turbine blade and preparation method thereof - Google Patents
High-temperature micro-motion resistant coating for micro-texturing of sawtooth crown surface of gas turbine blade and preparation method thereof Download PDFInfo
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- CN110616395A CN110616395A CN201910084203.6A CN201910084203A CN110616395A CN 110616395 A CN110616395 A CN 110616395A CN 201910084203 A CN201910084203 A CN 201910084203A CN 110616395 A CN110616395 A CN 110616395A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
- B22F2009/0824—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid with a specific atomising fluid
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- Chemical & Material Sciences (AREA)
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- Chemical Kinetics & Catalysis (AREA)
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- Mechanical Engineering (AREA)
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- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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Abstract
The invention provides a high-temperature micro-motion resistant coating for micro-texturing of a sawtooth crown surface of a gas turbine blade and a preparation method thereof, wherein the method comprises the following steps: pretreating the crown surface of the blade sawtooth, and then processing a micro-pit texture on the crown surface of the blade sawtooth; cleaning the sawtoothed crown surface of the blade with the processed micro-pit texture, and then preparing a nickel-chromium-molybdenum-aluminum alloy coating on the surface of the sawtoothed crown surface; and finally, processing the bar-shaped groove microtexture on the surface of the alloy coating to obtain the high-temperature micro-motion resistant coating with the microtexture on the sawtooth crown surface of the gas turbine blade and the preparation method thereof. The gas turbine blade sawtooth crown surface adopts a texture and coating composite structure, and the strip-shaped groove texture on the surface of the coating is utilized to enable adjacent sawtooth crown surfaces in close contact to be meshed, so that the gas turbine blade sawtooth crown surface has the characteristics of high bonding strength, difficult peeling and self-lubrication, and plays roles in preventing the oxidation of a substrate blade crown, reducing local fatigue damage and avoiding fretting wear.
Description
Technical Field
The invention relates to a high-temperature micro-motion resistant coating for micro-texturing of a sawtooth crown surface of a gas turbine blade and a preparation method thereof, which are applied to the mutual close contact surface of the sawtooth crown surface of the gas turbine blade.
Background
The blade of the gas turbine works in a high-temperature environment, the rigidity of the blade is enhanced mostly by adopting a sawtooth-shaped blade crown of a turbine blade of the gas turbine engine, the sawtooth-shaped crown surface of the adjacent blade is of a dry friction damping structure, the working surface of the blade crown adopts a tightness design, and the damping surfaces of the adjacent blade crown keep close contact; in actual working conditions, when the contact surface between the engine blades rotates at high speed in the turbine of the gas turbine, the axial cyclic load generated by the centrifugal force of the blades and the high-frequency vibration generated by gas impact enable the damping surfaces of the adjacent blade shrouds in 'close contact' to generate micro-motion, so that micro-motion abrasion and local contact fatigue are generated; the damping surface generates large-area grinding spots and pits, and the abrasion is aggravated along with the generation of abrasive dust, so that the contact surface of adjacent blade shrouds generates gaps and gradually increases, the dynamic characteristic of the blade is changed, the vibration stress is enhanced, the root part of the blade is cracked, and the blade tenon is cracked seriously. Meanwhile, the local contact fatigue of the damping working surface of the blade shroud induces the initiation and early expansion of fatigue cracks, and further expansion occurs under the action of periodic rotation and alternating load; fretting wear and localized fatigue failure of blade serration crowns over long periods of operation are among the important causes of aeroengine turbine blade failure.
The gas turbine blade is mainly made of alloy materials with a large friction coefficient and low wear resistance, such as titanium alloy and magnesium alloy; at present, the main methods for the aspect comprise the steps of preparing a soft coating or a thermal barrier coating on a contact surface, adopting shot blasting to cause residual stress on the surface, roughening the surface and the like; however, in actual conditions, because the turbine blade has high rotating speed and high generated vibration frequency, the coating is easy to peel off from the contact surface by the traditional surface coating processing mode, measures for enhancing the fatigue strength such as shot blasting and the like do not fundamentally solve the problem of friction and wear, and the surface texturing technology only improves the probability of preventing fretting damage from occurring for fretting wear and has contingency.
The tribology research finds that the non-smooth surface with the rough structure arranged according to a certain rule shows better wear resistance and viscosity reduction performance than the smooth surface, and has certain drag reduction and lubrication functions.
Disclosure of Invention
The invention provides a high-temperature fretting-resistant coating with textured sawtooth crown surfaces of a gas turbine blade and a preparation method thereof, aiming at solving the problem that the sawtooth crown surfaces of the gas turbine blade are easy to generate high-temperature fretting friction wear during working to cause the sawtooth crown surfaces to lose effectiveness, processing a pit-shaped micro-texture on the sawtooth crown surface of the gas turbine blade to be combined with the high-temperature wear-resistant alloy coating, processing a strip-shaped groove-shaped micro-texture on the surface of the high-temperature wear-resistant alloy coating, increasing the combination area of the high-temperature wear-resistant alloy coating and the substrate by utilizing the substrate micro-texture to enhance the combination capability with the substrate, and when high-frequency vibration caused by axial cyclic load generated by the centrifugal force of the blade is generated, the stripe-shaped texture on the surface of the high-temperature wear-resistant alloy coating can play roles in mutual meshing, fretting wear prevention, local fatigue generation prevention, collection, storage and grinding, and the coating can play roles in resisting wear and preventing oxidation of a substrate. The above structures are coupled in a synergistic manner, and can effectively reduce friction wear, control fretting wear and enhance surface fatigue characteristics to protect the substrate. The reliability of the sawtooth crown surface of the gas turbine blade is obviously improved, and the service life of the blade is prolonged.
The technical scheme of the invention is as follows: the high-temperature micro-motion resistant coating for micro-texturing of the sawtooth crown surface of the gas turbine blade is characterized in that: processing a pit-shaped micro-texture on the sawtooth crown surface of the gas turbine blade to obtain the sawtooth crown surface of the gas turbine blade with the micro-texture, preparing a high-temperature wear-resistant alloy coating on the sawtooth crown surface of the gas turbine blade with the micro-texture, and preparing a strip-shaped groove-shaped micro-texture on the surface of the high-temperature wear-resistant coating to obtain a high-temperature micro-motion resistant coating with the micro-texture on the sawtooth crown surface of the gas turbine blade; the pit-shaped micro-texture is formed by performing laser processing on the sawtooth crown surface of the blade to form regularly arranged pit-shaped textures; the high-temperature wear-resistant alloy coating is formed by spraying nickel-chromium-molybdenum-aluminum alloy powder on a sawtooth crown surface of a gas turbine blade with a microtexture; the strip-shaped groove-shaped micro-texture is formed by performing laser processing on the surface of the high-temperature wear-resistant alloy coating to form regularly arranged strip-shaped groove-shaped textures so as to realize the microcosmic meshing state of the contact of adjacent sawtooth crown surfaces and prevent fretting wear; the high-temperature fretting-resistant coating is 135-140 mu m thick.
A high-temperature micro-motion resistant coating for micro-texturing of a sawtooth crown surface of a gas turbine blade and a preparation method thereof comprise the following steps:
(1) polishing the sawtoothed crown surface of the blade to obtain a surface roughness of about Ra0.8, and cleaning with absolute ethyl alcohol;
(2) carrying out pit-shaped micro-texture processing on the contact surface of the blade shroud, wherein a pulse Nd: YAG laser processing system, wherein the wavelength of the laser is 355nm, the average power is 3W, the pulse width is 15ns, the processing pulse frequency is 30-35 kHz, and the scanning speed is 35-55 mm/s, so as to obtain the microtextured gas turbine blade sawtooth crown surface;
(3) cleaning the sawtooth crown surface of the microtextured gas turbine blade again, drying and preheating, preparing a high-temperature wear-resistant alloy coating, pre-grinding the surface of the high-temperature wear-resistant alloy coating, cleaning until the surface roughness is about Ra3.2, and then performing microtexture processing on the strip-shaped groove, wherein pulse Nd: the YAG laser processing system has the laser wavelength of 355nm, the average power of 3W, the pulse width of 15ns, the processing pulse frequency of 35-45 kHz and the scanning speed of 25-30 mm/s, and the high-temperature micro-motion resistant coating with the micro-texturing sawtooth crown surface of the gas turbine blade is obtained.
The cleaning method in the step (1) comprises the following steps: ultrasonic cleaning is carried out for 15-20 min;
the micro texture shape of the step (2) is as follows: the micro-texture comprises one or more than two of circular pits, square pits and strip-shaped groove micro-textures, wherein the size parameters are that the diameter or width is 25-30 mu m, the depth is 18-20 mu m, and the distance between every two adjacent pits is 50 mu m;
the raw material of the high-temperature wear-resistant alloy coating in the step (3) is nickel-chromium-molybdenum-aluminum alloy powder with the diameter of 20-25 mu m, and the powder comprises the following components: ni: 40-50%, Cr: 20% -25%, Mo: 15% -18%, and the balance of Al; the preparation method of the high-temperature wear-resistant alloy coating powder is vacuum melting.
The preparation method of the high-temperature wear-resistant alloy coating powder in the step (3) comprises the following steps: vacuum melting nickel, chromium, molybdenum and aluminum metal powder; feeding nickel, chromium, molybdenum and aluminum metal powder into a crucible of a vacuum smelting furnace in proportion, and heating to be molten by adopting a high-frequency power supply in an induction manner. Filling helium into the atomization powder making furnace, making molten alloy flow down through a flow guide pipe, crushing metal liquid flow into fine liquid drops by using high-pressure and high-purity helium gas with the pressure of more than 6MPa, cooling and solidifying the liquid drops to form spherical powder, screening the powder with the particle size of 20-25 mu m, and collecting and vacuum-storing the powder;
the cleaning method in the step (3) comprises the following steps: carrying out ultrasonic cleaning on absolute ethyl alcohol for 8-10 minutes; the preheating temperature is 60-80 ℃; the preparation method of the high-temperature wear-resistant alloy coating in the step (3) comprises the following steps: carrying out supersonic flame spraying on the sawtooth crown surface of the microtextured gas turbine blade, feeding nickel-chromium-molybdenum-aluminum alloy powder through a powder feeder, and spraying by using a spray gun; the parameters are as follows: the air pressure is 110-120 Psi, the gas pressure is 65-75 Psi, the powder feeding gas flow is 7-8L/h, the powder feeding amount is 80g/min, the moving speed of a spray gun is 800-850 mm/s, the spraying angle is 90 degrees, the spraying distance is 135-150 mm, and the protective gas is argon; the thickness of the high-temperature wear-resistant alloy coating in the step (3) is 135-140 microns;
the strip-shaped groove microtexture in the step (3): processing the alloy coating surface, distributing the gas turbine blade sawtooth crown end face array, wherein the width of the strip texture is 100 mu m, the depth of the strip texture is 40 mu m, and the distance between adjacent dents is also 100 mu m;
compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the bonding strength between the sawtooth crown surface of the gas turbine blade and the high-temperature wear-resistant alloy coating can be effectively improved by carrying out micro-texture processing on the contact surface of the blade crown, the bonding area between the textured substrate surface and the high-temperature wear-resistant alloy coating is increased, and the increased residual stress of a processing area has a certain adsorption effect on the high-temperature wear-resistant alloy coating;
2. the high-temperature wear-resistant alloy coating sprayed on the textured surface can effectively reduce friction and wear, enhance the surface hardness, reduce the friction coefficient and prevent the abrasion and oxidation of a substrate material; and Mo-oxidized oxides precipitated on the selected material at high temperature have a lubricating effect, prevent local fatigue and have a self-lubricating effect;
3. according to the invention, the strip-shaped micro-pit micro-texture is machined on the surface of the high-temperature wear-resistant alloy coating again, the width of the micro-texture is the same as the space between adjacent textures, so that mutual occlusion can be generated between saw-tooth crown surfaces which are in contact with each other, and fretting wear is prevented;
4. according to the invention, the strip-shaped groove microtexture is processed on the surface of the blade sawtooth crown, and is distributed in an array mode perpendicular to the end face of the blade sawtooth crown of the gas turbine, so that the meshing probability of the adjacent surface microtexture is greatly improved when high-frequency vibration is caused by axial cyclic load generated by centrifugal force of the blade, and the characteristic of preventing fretting wear is ensured;
5. the method for manufacturing the blade sawtooth crown surface through the high-temperature wear-resistant alloy coating has the advantages that the micro-texture incomplete meshing gap is machined on the surface of the high-temperature wear-resistant alloy coating again, abrasive dust can be stored, further abrasive wear is prevented, and therefore the influence of the abrasive dust on close contact between the sawtooth crown surfaces of the blade is avoided.
Drawings
FIG. 1 is a schematic view of a high temperature micro-motion resistant coating for micro-texturing the crown surface of a serration of a gas turbine blade according to the present invention. In the figure, 1 is the surface microtexture of the high-temperature wear-resistant alloy coating, 2 is the high-temperature wear-resistant alloy coating, 3 is the blade sawtooth crown microtexture, and 4 is the base of the sawtooth crown of the gas turbine blade.
FIG. 2 is a schematic view of the mutual engagement of the blade sawtooth crown surface contact processing area and the strip-shaped groove-shaped microtexture on the surface of the alloy coating.
FIG. 3 is a schematic diagram of the surface stripe-shaped dent texture of the high-temperature anti-fretting coating for the micro-texturing of the sawtooth crown surface of the gas turbine blade.
Claims (7)
1. A high-temperature anti-fretting coating with a microtexture on a sawtooth crown surface of a gas turbine blade is characterized in that a pit-shaped microtexture is processed on the sawtooth crown surface of the gas turbine blade to obtain the sawtooth crown surface of the gas turbine blade with the microtexture, a high-temperature wear-resistant alloy coating is prepared on the sawtooth crown surface of the gas turbine blade with the microtexture, a strip-shaped groove-shaped microtexture is prepared on the surface of the high-temperature wear-resistant coating to obtain the high-temperature anti-fretting coating with the microtexture, the pit-shaped microtexture is formed by carrying out laser processing on the sawtooth crown surface of the blade to form regularly arranged pit-shaped textures, the high-temperature wear-resistant alloy coating is formed by spraying nickel-chromium-molybdenum powder on the sawtooth crown surface of the gas turbine blade with the microtexture, the strip-shaped groove microtexture is processed on the surface of the high-temperature wear-resistant alloy coating and is distributed perpendicular to the end surface array of the sawtooth crown surface of the gas turbine blade to realize the microcosmic meshing state of the adjacent sawtooth crown surfaces to prevent fretting wear, the micro-wear, the formed complete meshing gaps can play a role in storing grinding chips and further.
2. A high-temperature micro-motion resistant coating for micro-texturing of a sawtooth crown surface of a gas turbine blade and a preparation method thereof are characterized by comprising the following steps:
(1) polishing the sawtoothed crown surface of the blade to obtain a surface roughness of about Ra0.8, and cleaning with absolute ethyl alcohol;
(2) carrying out pit-shaped micro-texture processing on the sawtooth crown surface of the blade, wherein a pulse Nd-YAG laser processing system is adopted, the wavelength of the laser is 355nm, the average power is 3W, the pulse width is 15ns, the processing pulse frequency is 30 ~ 35kHz, and the scanning speed is 35 ~ 55mm/s, so that the sawtooth crown surface of the blade of the micro-textured gas turbine is obtained;
(3) cleaning the saw-tooth crown surface of the microtextured gas turbine blade again, drying in the air, preheating, preparing a high-temperature wear-resistant alloy coating, pre-grinding the surface of the high-temperature wear-resistant alloy coating to reach the surface roughness of about Ra3.2, cleaning, and then carrying out strip-shaped groove microtexture processing, wherein a pulse Nd-YAG laser processing system is adopted, the wavelength of the laser is 355nm, the average power is 3W, the pulse width is 15ns, the processing pulse frequency is 35 ~ 45kHz, and the scanning speed is 25 ~ 30mm/s, so that the microtexture high-temperature micro-motion resistant coating of the saw-tooth crown surface of the gas turbine blade is obtained.
3. The high-temperature fretting-resistant coating for the micro texturing of the sawtooth crown surface of the gas turbine blade as claimed in claim 2, wherein the dimple-shaped micro texture in the step (2) is the combined morphology of one or more than two of a circular dimple, a square dimple and a strip-shaped groove micro texture, the dimensional parameters are that the diameter or width is 25 ~ 30 μm, the depth is 18 ~ 20 μm, and the distance between adjacent dimples is 50 μm.
4. The high-temperature fretting-resistant coating for the micro texturing of the crown surface of the sawtooth of the gas turbine blade as claimed in claim 2 is characterized in that the raw material of the high-temperature wear-resistant alloy coating in the step (3) is nickel-chromium-molybdenum-aluminum alloy powder with the diameter of 20 ~ 25 μm, the powder comprises the following components of 40% of Ni ~ 50%, 20% of Cr ~ 25%, 15% of Mo ~ 18%, and the balance of Al, and the preparation method of the alloy powder is vacuum melting.
5. The high-temperature fretting-resistant coating with the microtextured sawtooth crown surface of the gas turbine blade as claimed in claim 2 and the preparation method thereof are characterized in that the preparation method of the high-temperature wear-resistant alloy coating in the step (3) is supersonic flame spraying, nickel-chromium-molybdenum-aluminum alloy powder is fed in through a powder feeder and sprayed by using a spray gun, and the parameters are that the air pressure is 110 ~ 120Psi, the gas pressure is 65 ~ 75Psi, the powder feeding gas flow is 7 ~ 8L/h, the powder feeding amount is 80g/min, the spray gun moving speed is 800 ~ 850mm/s, the spraying angle is 90 degrees, the spraying distance is 135 ~ 150mm, and the protective gas is argon.
6. The high-temperature micro-motion resistant coating for micro-texturing of the sawtooth crown surface of the gas turbine blade and the preparation method thereof according to claim 2 are characterized in that: the strip-shaped groove microtexture in the step (3) has the following size parameters: the width of the grooves was 100 μm, the depth was 40 μm, and the pitch between adjacent grooves was 100 μm.
7. The method for preparing the high-temperature micro-motion resistant coating for the micro-texturing of the sawtooth crown surface of the gas turbine blade according to claim 2, wherein the method comprises the following steps: and (4) processing the strip-shaped groove microtexture on the surface of the high-temperature wear-resistant alloy coating in the step (3) and distributing the microtexture perpendicular to the end face array of the sawtooth crown of the gas turbine blade.
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