CN116043209A - Corrosion fault repairing method for aviation titanium alloy part, composite coating and application - Google Patents

Corrosion fault repairing method for aviation titanium alloy part, composite coating and application Download PDF

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Publication number
CN116043209A
CN116043209A CN202211688857.8A CN202211688857A CN116043209A CN 116043209 A CN116043209 A CN 116043209A CN 202211688857 A CN202211688857 A CN 202211688857A CN 116043209 A CN116043209 A CN 116043209A
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titanium alloy
tungsten carbide
cold spraying
coating
powder
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董脉鸣
李羿含
李星彤
王亮
赵阳
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Hubei Super Aviation Technology Co ltd
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Hubei Super Aviation Technology Co ltd
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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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/341—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one carbide layer
    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention relates to a corrosion fault repairing method for aviation titanium alloy parts, a composite coating and application thereof, comprising the following steps: cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, and recovering the size of the part after the supplementary cutting processing; and thermally spraying tungsten carbide powder to form a tungsten carbide coating. By combining the cold spraying technology and the hot spraying technology, the advantages of the two technologies are maximized, the characteristics of low porosity and high bonding strength of the sprayed coating of the cold spraying technology are fully utilized, the phenomena of falling blocks or granular falling in the using process are reduced, the safe use of the part is ensured, and the surface size and the precision after repair meet the requirements; the thermal spraying technology sprays tungsten carbide powder, and the tungsten carbide powder is chemically combined with the surface of the matrix under the action of high temperature to be deposited on the matrix, so that a compact coating can be formed, the repaired part has the advantages of corrosion resistance and friction resistance, and the surface modification treatment of the repaired area is not needed after repair.

Description

Corrosion fault repairing method for aviation titanium alloy part, composite coating and application
Technical Field
The invention relates to the field of aviation, in particular to a method for repairing corrosion faults of aviation titanium alloy parts, a composite coating and application thereof.
Background
At present, in the flight process of the aircraft in a damp and hot environment and a marine environment, the body structure can be severely corroded under the conditions of atmospheric salt mist, water vapor and self working stress. When various types of aircraft are overhauled, the surface of the aircraft body is severely corroded, the size of the aircraft body is thinned after surface corrosives are cleaned, the corroded area is uneven, and the strength, the rigidity and the surface aerodynamic properties of the aircraft body cannot meet the use requirements. An aviation titanium alloy part with serious corrosion defects is repaired, and a repair method which can ensure the size of the recovered part and is more corrosion-resistant after repair is needed, so that the problem of large-area corrosion defect repair and later preventive corrosion prevention of an aircraft body structure is solved.
In the related art, the repairing method is mainly a laser material-increasing repairing process, and the laser material-increasing repairing process is a method of heating a metal material to a molten or semi-molten state by taking high-energy beam laser as a heat source and spraying the metal material to the surface of a pretreated workpiece at a high speed to form a firmly-adhered surface layer. Although the influence on the temperature of the base material is small, larger deformation cannot be generated, but the porosity of the coating is higher, the bonding strength is lower, the phenomenon of falling blocks or particles in the reuse process is easy to occur, and the safe use of the part is influenced.
Disclosure of Invention
The embodiment of the invention provides a corrosion fault repairing method for an aviation titanium alloy part, a composite coating and application thereof, which are used for solving the problems that the coating in the related art has higher porosity and lower bonding strength, and is easy to cause the phenomenon of falling blocks or granular falling in the reuse process, and the safe use of the part is affected.
In a first aspect, a method for repairing corrosion faults of an aviation titanium alloy part is provided, which comprises the following steps: cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, and recovering the size of the part after the supplementary cutting processing; and thermally spraying tungsten carbide powder to form a tungsten carbide coating.
In some embodiments, before cold spraying the titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, the method further comprises: and (3) preprocessing the defect part of the part, wherein the preprocessing comprises polishing and cleaning surface floating ash.
In some embodiments, the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body and recovering the part size after the supplemental cutting processing, the pressure range of the cold spraying gas is 4.5Mpa-5.0Mpa, and the temperature range of the cold spraying is 800 ℃ to 900 ℃.
In some embodiments, the step of cold spraying titanium alloy powder which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body and recovering the part size after the supplemental cutting process adopts nitrogen or helium as the gas, the particle size of the powder is 15-30 μm and the microhardness value of the powder is 70-120 HV.
In some embodiments, after cold spraying the titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body and restoring the part size after the supplementary cutting processing, the method further comprises the following steps: and polishing the surface of the additive.
In some embodiments, in the step of forming the high-density tungsten carbide coating by thermally spraying tungsten carbide powder, the porosity of the tungsten carbide coating is less than 0.1%, and the thickness is in the range of 0.02mm-0.03mm.
In some embodiments, after the step of thermally spraying tungsten carbide powder to form a tungsten carbide coating, the method further comprises the steps of: and carrying out surface treatment on the surface of the repaired part.
In some embodiments, in the step of performing surface treatment on the surface of the repaired part, the treatment method includes machining, polishing, and sandblasting.
In a second aspect, a composite coating applied to the method for repairing corrosion faults of an aviation titanium alloy part is provided, which comprises the following steps: the material adding body is arranged at the part of the aviation titanium alloy part where the material is worn or the corrosion material is missing; and the tungsten carbide coating is arranged on the material adding body.
In a third aspect, there is provided the use of the composite coating for repairing wear failure of an aerospace titanium alloy part.
The technical scheme provided by the invention has the beneficial effects that:
the embodiment of the invention provides a corrosion fault repairing method, a composite coating and application of an aviation titanium alloy part, which are characterized in that the advantages of the cold spraying technology and the hot spraying technology are maximized by combining the two technologies, the characteristics of low porosity and high bonding strength of the sprayed coating of the cold spraying technology are fully utilized, the phenomena of falling blocks or particles falling off in the using process are reduced, the safe use of the part is ensured, and the surface size and the precision after repairing meet the requirements; the thermal spraying technology sprays tungsten carbide powder, and the tungsten carbide powder is chemically combined with the surface of the matrix under the action of high temperature to be deposited on the matrix, so that a compact coating can be formed, the repaired part has the advantages of corrosion resistance and friction resistance, and the surface modification treatment of the repaired area is not needed after repair.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a process flow diagram of an aviation titanium alloy part corrosion fault repair method provided by an embodiment of the invention.
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 of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. 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.
The embodiment of the invention provides a corrosion fault repairing method for an aviation titanium alloy part, a composite coating and application, which can solve the problems that in the related art, the coating has higher porosity and lower bonding strength, and the phenomenon of falling blocks or granular falling easily occurs in the reuse process, so that the safe use of the part is affected.
Referring to fig. 1, the method for repairing corrosion failure of an aviation titanium alloy part provided by the embodiment of the invention can include the following steps:
s1, cold spraying titanium alloy powder material which is the same as the part material at the defect part of an aviation titanium alloy part to form an additive body, and recovering the size of the part after supplementing cutting processing;
s2, thermally spraying tungsten carbide powder to form a tungsten carbide coating.
In the embodiment, by combining the cold spraying technology and the hot spraying technology, the advantages of the two technologies are maximized, the characteristics of low porosity and high bonding strength of the sprayed coating of the cold spraying technology are fully utilized, the phenomenon of falling blocks or particles falling off in the using process is avoided, the safe use of parts is ensured, and the surface size and the precision after repair meet the requirements; the thermal spraying technology sprays tungsten carbide powder, and the tungsten carbide powder is chemically combined with the surface of the matrix under the action of high temperature to be deposited on the matrix, so that a compact coating can be formed, the repaired part has the advantages of corrosion resistance and friction resistance, and the surface modification treatment of the repaired area is not needed after repair.
Referring to fig. 1, in some embodiments, before cold spraying the titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, the method further comprises: the part defect is pretreated, the pretreatment comprises polishing and cleaning surface floating ash, and in the embodiment, the part defect is pretreated before cold spraying, so that the surface of the part defect is smooth and clean, and the adhesive force of a coating is increased.
Referring to fig. 1, in some embodiments, the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body and recovering the size of the part after the complementary cutting processing is performed, the pressure of the cold spraying gas ranges from 4.5Mpa to 5.0Mpa, the temperature of the cold spraying is 800 ℃ to 900 ℃, and in this embodiment, the bonding strength of the coating is further increased and the porosity of the coating is reduced by ensuring the pressure and the temperature of the cold spraying gas.
Referring to fig. 1, in some embodiments, the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aeronautical titanium alloy part to form an additive body and recovering the part size after the supplemental cutting processing is performed, wherein the gas adopted by the cold spraying is nitrogen or helium, the granularity of the powder is 15 μm-30 μm, and the microhardness value of the powder is 70HV-120HV, and in this embodiment, the deposition efficiency of spraying can be ensured by adopting the nitrogen or helium for cold spraying; the strength of the coating is further ensured by ensuring the particle size and hardness of the powder.
Referring to fig. 1, in some embodiments, after cold spraying the titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body and restoring the part size after the complementary cutting process, the method further comprises the following steps: polishing treatment is carried out on the surface of the additive, and in the embodiment, the surface of the additive is smooth and clean by polishing treatment on the surface of the cold sprayed additive, so that the adhesive force of the hot sprayed coating is increased.
Referring to fig. 1, in some embodiments, in the step of forming the high-density tungsten carbide coating by thermally spraying tungsten carbide powder, the porosity of the tungsten carbide coating is less than 0.1%, and the thickness range is 0.02mm-0.03mm, and in this embodiment, by ensuring the porosity and thickness of the tungsten coating, the bonding strength, corrosion resistance, wear resistance and other properties of the coating can be ensured.
Referring to fig. 1, in some embodiments, after the step of thermally spraying tungsten carbide powder to form a tungsten carbide coating, the method may further include the steps of: the surface of the repaired part is subjected to surface treatment, and in the embodiment, the repaired part is better in corrosion resistance and friction resistance through the surface treatment.
Referring to fig. 1, in some embodiments, in the step of performing surface treatment on the surface of the repaired part, the treatment method includes machining, polishing and sand blasting, and in this embodiment, the surface property, corrosion resistance and friction resistance of the coating layer are better by fusing the coating layer with the part itself through machining, polishing and sand blasting.
In a second aspect, an embodiment of the present invention provides a composite coating applied to the method for repairing corrosion failure of an aviation titanium alloy part, which may include: the material adding body is arranged at the part of the aviation titanium alloy part where the material is worn or the material is corroded, so that the part size foundation of the part worn part is restored, and a foundation repairing surface is formed at the part worn part; the tungsten carbide coating is arranged on the material adding body. The basic repairing surface can only comprise the surface of the additive body, and can also comprise the surface of the additive body and the surface of the machine body near the edge of the surface of the additive body, namely the surface of the aviation titanium alloy part.
Table 1 comparison of the properties of the different coatings
Figure BDA0004020468040000051
According to the method, the titanium-composite coating is adopted, titanium in the composite coating is used as a main additive body, additive reinforcement and shape repair of the defective part of the corroded part are achieved, and the tungsten carbide coating is arranged on the surface layer, has good corrosion resistance, and can achieve improvement of the service life of the part.
In a third aspect, the application provides an application of the composite coating, which is used for repairing wear faults of aviation titanium alloy parts, and not only can realize defect repair of corrosion parts, but also ensures the overall strength and corrosion resistance of the repaired parts.
In the description of the present invention, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
It should be noted that in the present invention, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The foregoing is only a specific embodiment of the invention to enable those skilled in the art to understand or practice the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (10)

1. The method for repairing the corrosion fault of the aviation titanium alloy part is characterized by comprising the following steps of:
cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, and recovering the size of the part after the supplementary cutting processing;
and thermally spraying tungsten carbide powder to form a tungsten carbide coating.
2. The method for repairing corrosion failure of an aircraft titanium alloy part according to claim 1, further comprising, before cold spraying titanium alloy powder of the same material as the part material at a defective portion of the aircraft titanium alloy part to form an additive body:
and (3) preprocessing the defect part of the part, wherein the preprocessing comprises polishing and cleaning surface floating ash.
3. The method for repairing corrosion failure of an aerospace titanium alloy part according to claim 1, wherein the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aerospace titanium alloy part to form an additive body and recovering the size of the part after the supplemental cutting process is performed, wherein the pressure of cold spraying gas is in the range of 4.5Mpa to 5.0Mpa, and the temperature of cold spraying is in the range of 800 ℃ to 900 ℃.
4. The method for repairing corrosion failure of an aerospace titanium alloy part according to claim 1, wherein the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aerospace titanium alloy part to form an additive body and recovering the size of the part after the cutting process is supplemented, wherein the gas adopted by the cold spraying is nitrogen or helium, the particle size of the powder is 15-30 μm and the microhardness value of the powder is in the range of 70-120 HV.
5. The method for repairing corrosion failure of an aviation titanium alloy part according to claim 1, wherein the step of cold spraying titanium alloy powder material which is the same as the part material at the defect part of the aviation titanium alloy part to form an additive body, and after the step of recovering the part size after the supplemental cutting process, further comprises the steps of:
and polishing the surface of the additive.
6. The method for repairing corrosion failure of an aerospace titanium alloy part according to claim 1, wherein in the step of forming the high-density tungsten carbide coating by thermally spraying tungsten carbide powder, the porosity of the tungsten carbide coating is less than 0.1%, and the thickness is in the range of 0.02mm-0.03mm.
7. The method for repairing corrosion failure of an aircraft titanium alloy part according to claim 1, wherein after the step of forming a tungsten carbide coating by thermally spraying tungsten carbide powder, further comprising the steps of:
and carrying out surface treatment on the surface of the repaired part.
8. The method for repairing corrosion failure of an aircraft titanium alloy part according to claim 7, wherein in the step of surface treating the surface of the repaired part, the treating method comprises machining, polishing and sand blasting.
9. A composite coating for use in the method of corrosion failure repair of an aerospace titanium alloy part according to any one of claims 1 to 8, comprising:
the material adding body is arranged at the part of the aviation titanium alloy part where the material is worn or the corrosion material is missing;
and the 0 tungsten carbide coating is arranged on the material adding body.
10. Use of the composite coating according to claim 9 for repairing wear failure of an aeronautical titanium alloy part.
CN202211688857.8A 2022-12-27 2022-12-27 Corrosion fault repairing method for aviation titanium alloy part, composite coating and application Pending CN116043209A (en)

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