CN116676553A - Spray coating WC-NiCr-Cr 3 C 2 Coating method and aircraft engine blade tenon - Google Patents

Spray coating WC-NiCr-Cr 3 C 2 Coating method and aircraft engine blade tenon Download PDF

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Publication number
CN116676553A
CN116676553A CN202310641768.6A CN202310641768A CN116676553A CN 116676553 A CN116676553 A CN 116676553A CN 202310641768 A CN202310641768 A CN 202310641768A CN 116676553 A CN116676553 A CN 116676553A
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China
Prior art keywords
spraying
nicr
coating
sprayed
spray
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Inventor
陈焕涛
赵利
邓春明
况敏
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Institute of New Materials of Guangdong Academy of Sciences
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Institute of New Materials of Guangdong Academy of Sciences
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Priority to CN202310641768.6A priority Critical patent/CN116676553A/en
Publication of CN116676553A publication Critical patent/CN116676553A/en
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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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
    • C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
    • C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
    • C22C29/067—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds comprising a particular metallic binder
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

The invention discloses a spray coating WC-NiCr-Cr 3 C 2 A coating method and an aero-engine blade tenon belong to the technical field of coating spraying, and comprise the following steps: cleaning and sand blasting the spraying surface of the substrate to be sprayed; preheating the spraying surface of the base material to be sprayed, and spraying WC-NiCr-Cr on the spraying surface of the base material to be sprayed for 1-3 times by adopting a supersonic flame spraying method after preheating 3 C 2 A powder; cooling to form WC-NiCr-Cr 3 C 2 A coating; the WC-NiCr-Cr 3 C 2 The coating has high hardness, strong binding force with a matrix and good wear resistance, and is applied to aviationThe rigidity and wear resistance of the blade tenon of the engine can be effectively improved, and the service life of the blade tenon is prolonged.

Description

Spray coating WC-NiCr-Cr 3 C 2 Coating method and aircraft engine blade tenon
Technical Field
The invention relates to the technical field of coating spraying, in particular to a spray coating WC-NiCr-Cr 3 C 2 A coating method and an aero-engine blade tenon.
Background
The tenon of the blade of the aeroengine is connected with the turbine disc by the tenon (blade root), the tenon is a place with larger load in the engine, the centrifugal force born by the tenon of 1 blade of the engine is 100-150 kN generally, the tenon works at high temperature, and the mechanical property of materials is greatly reduced, so that the tenon is easy to break down in use.
The tenon and mortise of the blade of the aeroengine is connected and matched; there is often a slight relative slip of the bonding surfaces, and fretting damage to the surfaces is a frequent occurrence.
When the aeroengine blade works, when the rotating speed changes, the whole blade can vibrate, and the vibration phenomenon comprises a joint of a blade tenon and a tenon groove. The joint of the tenon and the mortise of the blade of the aeroengine often has tiny relative sliding between the joint surfaces, and is easy to cause surface damage.
When the rotation speed of the engine is repeatedly increased and decreased, the blade vibrates, and the tenon and mortise joint vibrates along with the rotation speed, and when the vibration amplitude exceeds the intensity born by the blade; the contact of the tenon and mortise will break. Serious conditions, which can lead to blade failure; even the whole engine cannot work normally.
The related art discloses a spraying method of a molybdenum coating, which adopts a plasma spraying method to spray the molybdenum coating on the surface of a part for an aeroengine, wherein the bonding strength of the coating is between 37 and 68MPa, and the bonding strength of the coating is still to be improved.
Disclosure of Invention
The invention aims to overcome the defects existing in the prior art and provide a spray coating WC-NiCr-Cr 3 C 2 Coating method, aircraft engine blade tenon, WC-NiCr-Cr 3 C 2 The coating has high hardness, strong binding force with a matrix and good wear resistance, and can effectively improve the hardness and wear resistance of the blade tenon and prolong the service life of the blade tenon when being applied to the blade tenon of an aeroengine.
To achieve the above object, in the present inventionIn a first aspect, the present invention provides a spray coated WC-NiCr-Cr 3 C 2 A method of coating comprising the steps of:
cleaning and sand blasting the spraying surface of the substrate to be sprayed;
preheating the spraying surface of the base material to be sprayed, and spraying WC-NiCr-Cr on the spraying surface of the base material to be sprayed for 1-3 times by adopting a supersonic flame spraying method after preheating 3 C 2 A powder; cooling to form WC-NiCr-Cr 3 C 2 A coating;
wherein, the technological parameters of the supersonic flame spraying are as follows: spraying distance: 130-170 mm, working air flow: 80-100L/min, propylene flow: 80-90L/min, nitrogen flow: 30-40L/min, hydrogen flow: 40-50L/min, powder feeding amount: 110-130 g/min; cooling air pressure: 0.3-0.5 MPa.
As a preferred embodiment of the present invention, the washing step is performed with alcohol or acetone.
As a preferred embodiment of the present invention, the blasting pressure is 0.6 to 0.8MPa.
As a preferred embodiment of the present invention, the blasting treatment gives the surface roughness of the sprayed surface of the substrate to be sprayed of 2.2 to 2.8 μm.
As a preferred embodiment of the present invention, the WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 20-30% WC, 20-30% NiCr, 50-60% Cr 3 C 2 。
As a preferred embodiment of the present invention, the preheating brings the spray face temperature of the substrate to be sprayed to 65 to 80 ℃.
As a preferred embodiment of the invention, the moving speed of the spray gun relative to the spray face of the substrate to be sprayed is 200-400 mm/s in the supersonic flame spraying process.
As a preferred embodiment of the invention, when the temperature of the spraying surface is higher than 200 ℃, stopping spraying, and continuing spraying when the temperature is reduced to below 200 ℃.
As a preferred embodiment of the present invention, the process parameters of the supersonic flame spraying are: spraying distance: 140mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 120g/min; cooling air pressure: 0.4Mpa;
the sand blasting pressure is 0.7Mpa;
the surface roughness of the spraying surface is 2.8 mu m;
the WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 30% WC, 20% NiCr, 50% Cr 3 C 2 ；
The preheating enables the temperature of the spraying surface of the substrate to be sprayed to 80 ℃;
the moving speed of the spraying gun relative to the spraying surface of the substrate to be sprayed is 300mm/s;
and when the temperature of the spraying surface is 120 ℃, spraying. In a second aspect, the present invention provides an aircraft engine blade dovetail comprising a substrate and WC-NiCr-Cr on a surface of the substrate 3 C 2 A coating;
wherein WC-NiCr-Cr 3 C 2 The coating is spray-formed by the spray-coating method described above.
As a preferred embodiment of the present invention, the material of the substrate comprises nickel-base superalloy, stainless steel or medium carbon steel.
The invention has the beneficial effects that: (1) The spray surface of the base material to be sprayed is cleaned, sandblasted, preheated and then sprayed with WC-NiCr-Cr by adopting a supersonic flame spraying method 3 C 2 Powder, thereby forming WC-NiCr-Cr 3 C 2 Coating, the WC-NiCr-Cr 3 C 2 The coating has high hardness, strong binding force with a matrix and good wear resistance, and can effectively improve the hardness and wear resistance of the blade tenon and prolong the service life of the blade tenon when being applied to the blade tenon of an aeroengine.
Drawings
FIG. 1 shows a blade tenon according to example 1 of the present invention coated with WC-NiCr-Cr 3 C 2 Schematic representation of the coating;
FIG. 2 shows a spray coated WC-NiCr-Cr according to example 1 of the present invention 3 C 2 Microstructure of the coating.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the invention, the technical characteristics described in an open mode comprise a closed technical scheme composed of the listed characteristics and also comprise an open technical scheme comprising the listed characteristics.
In the present invention, the numerical ranges are referred to as continuous, and include the minimum and maximum values of the ranges, and each value between the minimum and maximum values, unless otherwise specified. Further, when a range refers to an integer, each integer between the minimum and maximum values of the range is included. Further, when multiple range description features or characteristics are provided, the ranges may be combined. In other words, unless otherwise indicated, all ranges disclosed herein are to be understood to include any and all subranges subsumed therein.
In the present invention, the specific dispersing and stirring treatment method is not particularly limited.
In the present invention, the parts are parts by mass unless specifically stated otherwise.
The reagents or apparatus used in the present invention are conventional products commercially available without the manufacturer's knowledge.
The embodiment of the invention provides a spray coating WC-NiCr-Cr 3 C 2 A method of coating comprising the steps of:
cleaning and sand blasting the spraying surface of the substrate to be sprayed;
spraying the substrate to be sprayedPreheating the surface, and spraying WC-NiCr-Cr on the sprayed surface of the substrate to be sprayed for 1-3 times by adopting a supersonic flame spraying method after preheating 3 C 2 A powder; cooling to form WC-NiCr-Cr 3 C 2 A coating;
wherein, the technological parameters of the supersonic flame spraying are as follows: spraying distance: 130-170 mm, working air flow: 80-100L/min, propylene flow: 80-90L/min, nitrogen flow: 30-40L/min, hydrogen flow: 40-50L/min, powder feeding amount: 110-130 g/min; cooling air pressure: 0.3-0.5 MPa.
The spray surface of the base material to be sprayed is cleaned, sandblasted, preheated and then sprayed with WC-NiCr-Cr by adopting a supersonic flame spraying method 3 C 2 Powder, thereby forming WC-NiCr-Cr 3 C 2 Coating, the WC-NiCr-Cr 3 C 2 The coating has high hardness, strong binding force with a matrix and good wear resistance, and can effectively improve the hardness and wear resistance of the blade tenon and prolong the service life of the blade tenon when being applied to the blade tenon of an aeroengine.
Compared with the existing spraying method, the method for spraying the supersonic flame on the tenon of the blade of the aero-engine can remarkably improve the hardness and the bonding strength, and compared with the existing other methods, the method for spraying the supersonic flame on the tenon of the blade of the aero-engine has the following advantages:
compared to APS plasma spraying: the advantages are high efficiency and compact coating.
Compared with the spraying of relatively active combustion high-speed fuel gas, the method has the advantages that the air leakage is not easy in the spraying process; fuel leaks over the coating.
The coating is easy to peel off, and the pollution of the coating and even the post-spraying coating are caused.
Compared with inner hole spraying, the hardness of the coating is higher, the spraying efficiency is higher, and the coating can be thicker.
The cost is lower than that of a low-pressure plasma LLPS spray gun; the installation and the part spraying of frock are easier.
The invention obviously improves the combination strength, hardness and wear resistance by controlling the technological parameters of the supersonic flame spraying within the range of the invention.
If the spraying distance is too long (more than 170 mm), the coating binding force is reduced; the spraying distance is too short (lower than 130 mm), and a great amount of heat sources are generated at the spraying part, so that thermal stress is easily brought; the hydrogen flow is too high (higher than 50L/min), the power is high, the coating is hard and brittle, the internal stress is high, and the stripping is easy; the hydrogen flow is too low (lower than 40L/min), the coating is loose and is not compact and porous; the powder feeding amount is too large (more than 130 g/min), so that the unmelted powder particles of the coating are much; the powder feeding amount is too small (lower than 110 g/min), the coating is easy to thin, and the deposition efficiency is low; waste resources, high cost, and too high or too low nitrogen flow (higher than 40L/min or lower than 30L/min); affecting flame stability; the jet of the jet particles is easy to be negligent, the propylene flow is too high or too low (higher than 90L/min or lower than 80L/min); the speed of powder particles can be influenced by the flame flow temperature; directly affecting the structural compactness of the coating; the air flow is too high or too low (higher than 90L/min or lower than 80L/min); the stability of the spray gun performance can be affected; too high air flow and insufficient burning of the spray gun chamber; the air flow is too low, so that the spray gun chamber is easy to generate overburning, and the particle fusion state is influenced; the condition of easily generating gun blockage is that the cooling air pressure is too small (lower than 0.3 MPa), and the cooling effect is poor; the cooling air pressure is too high (higher than 0.3 MPa); the deposition state of the molten particles in the coating is easily affected.
Illustratively, during supersonic flame spraying, a Laval nozzle is employed. The Laval nozzle particles are easy to form an emissive spraying state, so that the coating porosity distribution of each layer is kept to be divergent and tiny (the coating porosity distribution of each layer is divergent and tiny; the blade rotates at a high speed when in work, a large amount of heat is generated in the service process of the blade tenon, and tiny micropores are beneficial to heat dissipation).
In some of these embodiments, the washing step is performed with alcohol or acetone.
In some of these embodiments, the blasting pressure is 0.6 to 0.8MPa.
In some of these embodiments, the grit blasting provides the sprayed surface of the substrate to be sprayed with a surface roughness of 2.2 to 2.8 μm.
In some of these embodiments, WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 20-30% WC, 20-30% NiCr, 50-60% Cr 3 C 2 。
In some preferred embodiments, the Cr 3 C 2 The content of (C) is equal to or greater than the sum of the content of WC and NiCr.
In some of these embodiments, the preheating brings the spray face temperature of the substrate to be sprayed to 65-80 ℃. The spraying surface is preheated before spraying, so that greasy dirt and impurities on the surface can be effectively cleaned, and meanwhile, the temperature of the matrix is increased, and the combination of the molten semi-molten powder particles and the interface of the matrix is facilitated; the heat of the cold coating of the matrix is avoided; forming a larger temperature difference; causing peeling of the coating and significantly improving the bonding strength and hardness.
In some of these embodiments, the velocity of movement of the spray gun relative to the spray face of the substrate to be sprayed during the supersonic flame spraying is in the range 200 to 400mm/s. The moving speed has a remarkable influence on the effect, if the moving speed exceeds 400mm/s, the sprayed coating is thin, the deposition efficiency is low, and the erosion effect of the coating can be caused, so that the performance is reduced, and if the moving speed is lower than 200mm/s, powder particles are agglomerated to form loose clusters.
In some embodiments, spraying is stopped when the temperature of the sprayed surface is above 200 ℃, and spraying is continued when the temperature falls below 200 ℃.
In some of these embodiments, the process parameters of the supersonic flame spraying are: spraying distance: 140mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 120g/min; cooling air pressure: 0.4Mpa;
the sand blasting pressure is 0.7Mpa;
the surface roughness of the spraying surface is 2.8 mu m;
the WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 30% WC, 20% NiCr, 50% Cr 3 C 2 ；
The preheating enables the temperature of the spraying surface of the substrate to be sprayed to 80 ℃;
the moving speed of the spraying gun relative to the spraying surface of the substrate to be sprayed is 300mm/s;
and when the temperature of the spraying surface is 120 ℃, spraying.
One embodiment of the invention provides an aircraft engine blade tenon, which comprises a substrate and WC-NiCr-Cr positioned on the surface of the substrate 3 C 2 A coating;
wherein WC-NiCr-Cr 3 C 2 The coating is spray-formed by the spray-coating method described above.
In some embodiments, the substrate comprises a nickel-base superalloy, stainless steel, or medium carbon steel.
Example 1
WC-NiCr-Cr is sprayed on blade tenons (hereinafter called blade tenons) of aero-engine 3 C 2 A method of coating comprising the steps of:
as shown in fig. 1, the blade tenon based on Inconel625 nickel-based superalloy;
firstly, protecting a non-spraying surface of a blade tenon by using a thermal insulation adhesive tape, cleaning the spraying surface (hereinafter referred to as a spraying surface) of the blade tenon by using alcohol, and performing sand blasting treatment (46 # white corundum) after cleaning, wherein the sand blasting pressure is 0.7MPa, so that the surface roughness of the spraying surface reaches 2.7 mu m;
preheating the spraying surface by HVAF supersonic flame to 70 deg.C, spraying WC-NiCr-Cr for 2 times by supersonic flame spraying 3 C 2 The powder is sprayed by a Laval nozzle, and cooled to form WC-NiCr-Cr 3 C 2 A coating;
in the spraying process, the temperature of a spraying surface exceeds 200 ℃; suspending the continuous spraying; and (5) continuing spraying until the temperature returns to below 200 ℃.
Wherein, the technological parameters of each supersonic flame spraying are as follows: spraying distance: 140mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 120g/min; cooling air pressure: in the process of 0.4MPa and supersonic flame spraying, the moving speed of the spraying gun relative to the spraying surface is 300mm/s.
Wherein WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 30% WC, 20% NiCr, 50% Cr 3 C 2 。
Referring to FIG. 1, a block diagram of a blade dovetail is shown in FIG. 1, including a blade dovetail and WC-NiCr-Cr 3 C 2 Coating (coating region), WC-NiCr-Cr 3 C 2 The microstructure of the coating is shown in figure 2.
Example 2
Based on the same Inconel625 nickel-base superalloy blade dovetail as in example 1; the workpiece is preheated by adopting an oven before being sprayed.
Firstly, protecting a non-spraying surface of a blade tenon by using a thermal insulation adhesive tape, cleaning the spraying surface (hereinafter referred to as a spraying surface) of the blade tenon by using alcohol, and performing sand blasting treatment (46 # white corundum) after cleaning, wherein the sand blasting pressure is 0.7MPa, so that the surface roughness of the spraying surface reaches 2.7 mu m;
preheating the spraying surface by an oven to make the spraying surface reach 70 ℃, spraying the spraying surface for 2 times by adopting a supersonic flame spraying method, wherein the spraying surface is coated with WC-NiCr-Cr 3 C 2 The powder is sprayed by a Laval nozzle, and cooled to form WC-NiCr-Cr 3 C 2 A coating;
in the spraying process, the temperature of a spraying surface exceeds 200 ℃; suspending the continuous spraying; and (5) continuing spraying until the temperature returns to below 200 ℃.
Wherein, the technological parameters of each supersonic flame spraying are as follows: spraying distance: 130mm, working air flow: 80L/min, propylene flow: 80L/min, nitrogen flow: 35L/min, hydrogen flow: 40L/min, powder feeding amount: 120g/min; cooling air pressure: in the process of 0.4MPa and supersonic flame spraying, the moving speed of the spraying gun relative to the spraying surface is 300mm/s.
Wherein WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 30% WC, 20% NiCr, 50% Cr 3 C 2 。
The environmental humidity is more than or equal to 70%, and the effect can be better by adopting an oven to preheat the workpiece.
Example 3
WC-NiCr-Cr is sprayed on blade tenons (hereinafter called blade tenons) of aero-engine 3 C 2 A method of coating comprising the steps of:
based on the same Inconel625 nickel-base superalloy blade dovetail as in example 1;
firstly, protecting a non-spraying surface of a blade tenon by using a thermal insulation adhesive tape, cleaning the spraying surface (hereinafter referred to as a spraying surface) of the blade tenon by using alcohol, and performing sand blasting treatment (46 # white corundum) after cleaning, wherein the sand blasting pressure is 0.8MPa, so that the surface roughness of the spraying surface reaches 2.6 mu m;
preheating the spraying surface by HVAF supersonic flame to 70 deg.C, spraying WC-NiCr-Cr for 2 times by supersonic flame spraying 3 C 2 The powder is sprayed by a Laval nozzle, and cooled to form WC-NiCr-Cr 3 C 2 A coating;
in the spraying process, the temperature of a spraying surface exceeds 200 ℃; suspending the continuous spraying; and (5) continuing spraying until the temperature returns to below 200 ℃.
Wherein, the technological parameters of each supersonic flame spraying are as follows: spraying distance: 150mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 115g/min; cooling air pressure: in the process of 0.5MPa and supersonic flame spraying, the moving speed of the spraying gun relative to the spraying surface is 400mm/s.
Wherein WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 25% WC, 25% NiCr, 50% Cr 3 C 2 。
Example 4
In the process ofWC-NiCr-Cr is sprayed on blade tenon of aero-engine (hereinafter called blade tenon) 3 C 2 A method of coating comprising the steps of:
based on the same Inconel625 nickel-base superalloy blade dovetail as in example 1;
firstly, protecting a non-spraying surface of a blade tenon by using a thermal insulation adhesive tape, cleaning the spraying surface (hereinafter referred to as a spraying surface) of the blade tenon by using alcohol, and performing sand blasting treatment (46 # white corundum) after cleaning, wherein the sand blasting pressure is 0.7MPa, so that the surface roughness of the spraying surface reaches 2.4 mu m;
preheating the spraying surface by HVAF supersonic flame to 70 deg.C, spraying WC-NiCr-Cr for 2 times by supersonic flame spraying 3 C 2 The powder is sprayed by a Laval nozzle, and cooled to form WC-NiCr-Cr 3 C 2 A coating;
in the spraying process, the temperature of a spraying surface exceeds 200 ℃; suspending the continuous spraying; and (5) continuing spraying until the temperature returns to below 200 ℃.
Wherein, the technological parameters of each supersonic flame spraying are as follows: spraying distance: 140mm, working air flow: 95L/min, propylene flow: 86L/min, nitrogen flow: 38L/min, hydrogen flow: 35L/min, powder feeding amount: 115g/min; cooling air pressure: in the process of 0.35MPa and supersonic flame spraying, the moving speed of the spraying gun relative to the spraying surface is 250mm/s.
Wherein WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 20% WC, 30% NiCr, 50% Cr 3 C 2 。
Comparative example 1
Comparative example 1 differs from example 1 in that WC-NiCr-Cr of comparative example 1 3 C 2 Mass percent of the powder wherein Cr 3 C 2 More than 50%, and WC and NiCr contents less than 50%, all other being the same as in example 1.
WC-NiCr-Cr is sprayed on blade tenons (hereinafter called blade tenons) of aero-engine 3 C 2 A method of coating comprising the steps of:
based on the same blade tenon of nickel-base superalloy as in example 1;
firstly, protecting a non-spraying surface of a blade tenon by using a thermal insulation adhesive tape, cleaning the spraying surface (hereinafter referred to as a spraying surface) of the blade tenon by using alcohol, and performing sand blasting treatment (46 # white corundum) after cleaning, wherein the sand blasting pressure is 0.7MPa, so that the surface roughness of the spraying surface reaches 2.7 mu m;
preheating the spraying surface by HVAF supersonic flame to 70 deg.C, spraying WC-NiCr-Cr for 2 times by supersonic flame spraying 3 C 2 The powder is sprayed by a Laval nozzle, and cooled to form WC-NiCr-Cr 3 C 2 A coating;
in the spraying process, the temperature of a spraying surface exceeds 200 ℃; suspending the continuous spraying; and (5) continuing spraying until the temperature returns to below 200 ℃. Wherein, the technological parameters of each supersonic flame spraying are as follows: spraying distance: 140mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 120g/min; cooling air pressure: in the process of 0.4MPa and supersonic flame spraying, the moving speed of the spraying gun relative to the spraying surface is 300mm/s.
Wherein WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 20% WC, 20% NiCr, 60% Cr 3 C 2 。
Comparative example 2
Comparative example 2 is different from example 1 in that the moving speed of the spray gun of comparative example 2 with respect to the spray face is 100mm/s, and otherwise is the same as example 1.
Comparative example 3
Comparative example 3 is different from example 1 in that the moving speed of the spray gun of comparative example 3 with respect to the spray face is 500mm/s, and otherwise is the same as example 1.
Comparative example 4
Comparative example 4 is different from example 1 in that comparative example 4 is sprayed at a distance of 100mm, and otherwise is the same as example 1.
Comparative example 5
Comparative example 5 is different from example 1 in that comparative example 5 is sprayed at a distance of 180mm, and otherwise is the same as example 1.
Comparative example 6
Comparative example 6 is different from example 1 in that the hydrogen flow rate of comparative example 7 is 30L/min, and the other is the same as example 1.
Comparative example 7
Comparative example 7 is different from example 1 in that the hydrogen flow rate of comparative example 7 is 60L/min, and otherwise is the same as example 1.
Comparative example 8
Comparative example 8 is different from example 1 in that the propylene flow rate of comparative example 8 is 70L/min, and otherwise is the same as example 1.
Comparative example 9
Comparative example 9 is different from example 1 in that the propylene flow rate of comparative example 9 is 100L/min, and otherwise is the same as example 1.
Test case
The coating bond strength was tested using ASTM C633 standard.
The coating was tested for micro vickers hardness using an ASTM E384 micro vickers durometer.
Table 1 test results
Finally, it should be noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the scope of the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions can be made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention.

Claims (10)

1. Spray coating WC-NiCr-Cr 3 C 2 A method of coating comprising the steps of:
cleaning and sand blasting the spraying surface of the substrate to be sprayed;
preheating the spraying surface of the base material to be sprayed, and spraying WC-NiCr-Cr on the spraying surface of the base material to be sprayed for 1-3 times by adopting a supersonic flame spraying method after preheating 3 C 2 A powder; cooling to form WC-NiCr-Cr 3 C 2 A coating;
wherein, the technological parameters of the supersonic flame spraying are as follows: spraying distance: 130-170 mm, working air flow: 80-100L/min, propylene flow: 80-90L/min, nitrogen flow: 30-40L/min, hydrogen flow: 40-50L/min, powder feeding amount: 110-130 g/min; cooling air pressure: 0.3-0.5 MPa.
2. Spray coating WC-NiCr-Cr according to claim 1 3 C 2 The method for coating is characterized in that the cleaning step adopts alcohol or acetone for cleaning.
3. Spray coating WC-NiCr-Cr according to claim 1 3 C 2 The coating method is characterized in that the sand blasting pressure is 0.6-0.8 Mpa; and/or
The sand blasting treatment enables the surface roughness of the spraying surface of the substrate to be sprayed to be 2.2-2.8 mu m.
4. Spray coating WC-NiCr-Cr according to claim 1 3 C 2 A method of coating, characterized in that the WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 20-30% WC, 20-30% NiCr, 50-60% Cr 3 C 2 。
5. Spray coating WC-NiCr-Cr according to claim 1 3 C 2 The coating method is characterized in that the preheating enables the temperature of the spraying surface of the substrate to be sprayed to 65-80 ℃.
6. According to claim 1The spray coating WC-NiCr-Cr 3 C 2 The coating method is characterized in that the moving speed of the spray gun relative to the spray surface of the substrate to be sprayed is 200-400 mm/s in the ultrasonic flame spraying process.
7. Spray coating WC-NiCr-Cr according to claim 1 3 C 2 The coating method is characterized in that in the spraying process, when the temperature of a spraying surface is higher than 200 ℃, the spraying is stopped, and when the temperature is reduced to below 200 ℃, the spraying is continued.
8. Spray coating WC-NiCr-Cr according to any one of claims 1-7 3 C 2 The coating method is characterized in that the technological parameters of the supersonic flame spraying are as follows: spraying distance: 140mm, working air flow: 90L/min, propylene flow: 85L/min, nitrogen flow: 35L/min, hydrogen flow: 45L/min, powder feeding amount: 120g/min; cooling air pressure: 0.4Mpa;
the sand blasting pressure is 0.7Mpa;
the surface roughness of the spraying surface is 2.8 mu m;
the WC-NiCr-Cr 3 C 2 The powder comprises the following components in percentage by mass: 30% WC, 20% NiCr, 50% Cr 3 C 2 ；
The preheating enables the temperature of the spraying surface of the substrate to be sprayed to 80 ℃;
the moving speed of the spraying gun relative to the spraying surface of the substrate to be sprayed is 300mm/s;
and when the temperature of the spraying surface is 120 ℃, spraying.
9. An aircraft engine blade tenon is characterized by comprising a base material and WC-NiCr-Cr positioned on the surface of the base material 3 C 2 A coating;
wherein WC-NiCr-Cr 3 C 2 The coating is spray-formed by the spray method of any one of claims 1 to 8.
10. An aircraft engine blade tenon according to claim 9 wherein the material of said base material comprises nickel-base superalloy, stainless steel or medium carbon steel.
CN202310641768.6A 2023-05-31 2023-05-31 Spray coating WC-NiCr-Cr 3 C 2 Coating method and aircraft engine blade tenon Pending CN116676553A (en)

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