CN115058665B - Alloy material and air gun surface repairing method - Google Patents

Alloy material and air gun surface repairing method Download PDF

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Publication number
CN115058665B
CN115058665B CN202210706864.XA CN202210706864A CN115058665B CN 115058665 B CN115058665 B CN 115058665B CN 202210706864 A CN202210706864 A CN 202210706864A CN 115058665 B CN115058665 B CN 115058665B
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air gun
alloy material
percent
laser cladding
alloy
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CN115058665A (en
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谷文举
王金强
王友峰
左江成
郭学良
刘长辉
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China Oilfield Services Ltd
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China Oilfield Services Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/34—Ferrous alloys, e.g. steel alloys containing chromium with more than 1.5% by weight of silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/42—Ferrous alloys, e.g. steel alloys containing chromium with nickel with copper
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/60—Ferrous alloys, e.g. steel alloys containing lead, selenium, tellurium, or antimony, or more than 0.04% by weight of sulfur
    • 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
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
    • 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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  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The application relates to the technical field of alloy materials, in particular to an alloy material and an air gun surface repairing method, wherein the alloy material comprises the following components in percentage by mass: 0.07 to 0.1 percent of carbon, 0.02 to 0.04 percent of phosphorus, 0.02 to 0.055 percent of sulfur, 0.309 to 1.2 percent of molybdenum, 4.7 to 5.1 percent of nickel, 0.4 to 0.45 percent of niobium, 0.15 to 0.2 percent of tantalum, 0.65 to 0.85 percent of manganese, 10 to 16 percent of chromium, 0.8 to 1.8 percent of silicon, 0.2 to 0.4 percent of copper and the balance of iron. By means of the mode, the alloy material provided by the application can ensure the material hardness of the air gun after repairing the abrasion surface of the air gun, so that the overall structural strength of the air gun is improved, and the secondary service life of the air gun is prolonged.

Description

Alloy material and air gun surface repairing method
Technical Field
The application relates to the technical field of alloy materials, in particular to an alloy material and an air gun surface repairing method.
Background
The air gun is widely applied to seismic exploration operations in areas such as oceans, lakes and rivers as a seismic source, and along with the development of seismic exploration technology, the air gun with large seismic source and large capacity is used more and more frequently.
The large vibration source and the large-capacity air gun generate strong vibration when excited, so the interaction force among all the components is large, the hardware in the air gun is easy to damage, and the air gun is high in cost and replacement cost.
Disclosure of Invention
In view of the above problems, the application provides an alloy material and a method for repairing the surface of an air gun, wherein the alloy material can ensure the hardness of the repaired air gun after repairing the worn surface of the air gun, so that the overall structural strength of the air gun is improved, and the secondary service life of the air gun is prolonged.
According to an aspect of the present application, there is provided an alloy material comprising, in mass percent: 0.07 to 0.1 percent of carbon, 0.02 to 0.04 percent of phosphorus, 0.02 to 0.055 percent of sulfur, 0.309 to 1.2 percent of molybdenum, 4.7 to 5.1 percent of nickel, 0.4 to 0.45 percent of niobium, 0.15 to 0.2 percent of tantalum, 0.65 to 0.85 percent of manganese, 10 to 16 percent of chromium, 0.8 to 1.8 percent of silicon, 0.2 to 0.4 percent of copper and the balance of iron.
According to the application, the inventor finds that the hardness of the prepared alloy material is high by adopting 0.07% -0.1% of carbon, 0.02% -0.04% of phosphorus, 0.02% -0.055% of sulfur, 0.309% -1.2% of molybdenum, 4.7% -5.1% of nickel, 0.4% -0.45% of niobium, 0.15% -0.2% of tantalum, 0.65% -0.85% of manganese, 10% -16% of chromium, 0.8% -1.8% of silicon and 0.2% -0.4% of copper, and the balance of iron, so that the hardness requirement of an air gun can be fully met when the alloy material is applied to surface repair of the air gun, and the secondary service life of the air gun is prolonged.
In an alternative, the niobium content is 0.42% to 0.45%. The structure can be refined by increasing the content of niobium to 0.42% -0.45%, so that the hardness of the alloy material is further increased under the condition that other properties of the alloy material are not affected.
In an alternative, the tantalum content is 0.18% to 0.2%. By increasing the tantalum content to 0.18% -0.2%, the hardness of the alloy material can be further increased under the condition that other properties of the alloy material are not affected.
In an alternative, the molybdenum content is 1% to 1.2%. By improving the content of molybdenum to 1% -1.2%, the surface wear resistance and corrosion resistance of the alloy material can be obviously improved.
In an alternative, the chromium content is 14% -16%. By increasing the chromium content to 14% -16%, the elongation and the area shrinkage of the alloy material can be increased, and the surface wear resistance of the alloy material can be further improved.
In an alternative, the silicon content is 1.5% to 1.8%. The hardness of the alloy material can be further improved by increasing the silicon content to 1.5% -1.8%.
In an alternative, the alloy material further comprises 0.9% -0.94% boron. By adding 0.9% -0.94% of boron into the alloy material, the compactness and hot rolling performance of the alloy material can be improved, and the hardness of the alloy material can be further improved.
In an alternative, the phosphorus content is 0.03% to 0.04%, and the sulfur content is 0.03% to 0.055%. The hardness, the surface wear resistance and the corrosion resistance of the alloy material can be further improved by improving the content of phosphorus to be 0.03-0.04% and the content of sulfur to be 0.03-0.055%.
In an alternative, the carbon content is 0.1%. By increasing the carbon content to 0.1%, the hardness, surface wear resistance and corrosion resistance of the alloy material can be further improved.
According to another aspect of the present application, there is provided a method of repairing a surface of an air gun, comprising: treating the damaged surface of the air gun to expose the normal tissue of the matrix of the air gun; measuring the repair thickness between the exposed normal tissue of the substrate and the normal surface of the air gun; determining a laser cladding thickness according to the repair thickness, wherein the laser cladding thickness is larger than or equal to the repair thickness; and (3) carrying out laser cladding on the normal tissue of the matrix by adopting the alloy powder prepared from the alloy material in any one of the above steps, and repairing the damaged surface of the air gun.
The foregoing description is only an overview of the present application, and is intended to be implemented in accordance with the teachings of the present application in order that the same may be more clearly understood and to make the same and other objects, features and advantages of the present application more readily apparent.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:
FIG. 1 is a flow chart of a method for repairing a surface of an air gun according to an embodiment of the present application.
Detailed Description
Embodiments of the technical scheme of the present application will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present application, and thus are merely examples, and are not intended to limit the scope of the present application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising" and "having" and any variations thereof in the description of the application and the claims and the description of the drawings above are intended to cover a non-exclusive inclusion.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
The air gun, also called air gun source, is a device shaped like a gun, which is used for obtaining earthquake effect by pressing high-pressure gas into a gun chamber and releasing the high-pressure gas at a gun muzzle instantaneously so as to form strong impulsive force. The air gun is widely applied to seismic exploration operations in water areas such as oceans, lakes, rivers and the like.
Along with the rapid development of the seismic exploration technology, the large-focus and large-capacity air guns are applied more and more frequently, and because the large-focus and large-capacity air guns can generate strong vibration when being excited, the acting force among all hardware in the air guns is large, so that the situation that all hardware is easy to wear and the like and has functional failure is caused, and the situation specifically comprises the abrasion of gun bodies and gun head edges, the abrasion of positioning keys and positioning groove surfaces, the abrasion of clamp surfaces and the like, and the stability of the integral structure of the air guns is affected.
When the surface of the air gun is worn, the air gun is generally repaired by adopting a metal material electroplating mode, and the secondary service life of the air gun after electroplating repair is shorter because the strength of the electroplated metal material is lower and the fatigue strength of a hardware matrix is greatly influenced by an electroplating process.
Based on the above, the application provides an alloy material, and the two elements of 0.4-0.45% of niobium and 0.15-0.2% of tantalum are added, so that the effects of refining the structure and increasing the hardness of the alloy material can be achieved, and when the alloy material is adopted for repairing the abrasion surface of an air gun, the surface hardness of the air gun can be remarkably improved, and the secondary service life of the air gun can be prolonged.
The alloy material provided by the application comprises, by mass, 0.07% -0.1% of carbon, 0.02% -0.04% of phosphorus, 0.02% -0.055% of sulfur, 0.309% -1.2% of molybdenum, 4.7% -5.1% of nickel, 0.4% -0.45% of niobium, 0.15% -0.2% of tantalum, 0.65% -0.85% of manganese, 10% -16% of chromium, 0.8% -1.8% of silicon, 0.2% -0.4% of copper and the balance of iron.
According to the application, the inventor finds that the hardness of the prepared alloy material is high by adopting 0.07% -0.1% of carbon, 0.02% -0.04% of phosphorus, 0.02% -0.055% of sulfur, 0.309% -1.2% of molybdenum, 4.7% -5.1% of nickel, 0.4% -0.45% of niobium, 0.15% -0.2% of tantalum, 0.65% -0.85% of manganese, 10% -16% of chromium, 0.8% -1.8% of silicon and 0.2% -0.4% of copper, and the balance of iron, so that the hardness requirement of an air gun can be fully met when the alloy material is applied to surface repair of the air gun, and the secondary service life of the air gun is prolonged.
In some embodiments, the niobium content is 0.42% -0.45%.
The structure can be refined by increasing the content of niobium to 0.42% -0.45%, so that the hardness of the alloy material is further increased under the condition that other properties of the alloy material are not affected.
In some embodiments, the tantalum is present in an amount of 0.18% to 0.2%.
By increasing the tantalum content to 0.18% -0.2%, the hardness of the alloy material can be further increased under the condition that other properties of the alloy material are not affected.
In some embodiments, the molybdenum content is 1% -1.2%.
By improving the content of molybdenum to 1% -1.2%, the surface wear resistance and corrosion resistance of the alloy material can be obviously improved.
In some embodiments, the chromium content is 14% -16%.
By increasing the chromium content to 14% -16%, the elongation and the area shrinkage of the alloy material can be increased, and the surface wear resistance of the alloy material can be further improved.
In some embodiments, the silicon content is 1.5% -1.8%.
The hardness of the alloy material can be further improved by increasing the silicon content to 1.5% -1.8%.
In some embodiments, the alloy material further includes 0.9% -0.94% boron.
By adding 0.9% -0.94% of boron into the alloy material, the compactness and hot rolling performance of the alloy material can be improved, and the hardness of the alloy material can be further improved.
In some embodiments, the phosphorus content is 0.03% -0.04%.
The hardness, the surface wear resistance and the corrosion resistance of the alloy material can be further improved by improving the content of phosphorus to be 0.03-0.04% and the content of sulfur to be 0.03-0.055%.
In some embodiments, the carbon content is 0.1%.
By increasing the carbon content to 0.1%, the hardness, surface wear resistance and corrosion resistance of the alloy material can be further improved.
In accordance with another aspect of the present application, there is also provided a method for repairing a surface of an air gun, referring specifically to fig. 1, as shown in the drawings, the method for repairing a surface of an air gun includes:
step 110: the damaged surface of the air gun is treated to expose the normal tissue of the matrix of the air gun.
In the step, the worn surface and corroded parts of the air gun can be initially removed by turning, and the surface of the normal tissue of the exposed substrate of the final air gun needs to be polished and leveled during turning.
Step 120: the repair thickness between the exposed normal tissue of the substrate and the normal surface of the air gun was measured.
In the step, the micrometer can be used for measuring the size in the normal tissue area of the matrix, specifically, four corners can be measured in different directions, data are recorded, the repair thickness between the normal tissue of the matrix and the normal surface of the air gun is finally obtained, the thickness of the single-layer laser cladding layer is generally controlled within 0.05-0.2mm, the effect of subsequent laser cladding is influenced easily due to overlarge, and finally, the laser cladding layer is formed through a plurality of single-layer laser cladding layers.
Step 130: and determining the laser cladding thickness according to the repair thickness, wherein the laser cladding thickness is larger than or equal to the repair thickness.
In this step, the laser cladding thickness is set to be greater than or equal to the repair thickness to ensure that the surface at the laser cladding can be flush with or exceed the normal surface of the air gun. For the mode that the surface of the laser cladding part exceeds the normal surface, after laser cladding, the part of the laser cladding part exceeding the normal surface can be ground by adopting a grinding process, so that the part is flush with the normal surface of surrounding air guns, and the dimensional accuracy of the repaired air guns is ensured.
Step 140: the alloy powder made of the alloy material in any embodiment is subjected to laser cladding at the normal tissue of the matrix according to the laser cladding thickness, so that the damaged surface of the air gun is repaired.
In the step, the coaxial powder feeding technology can be adopted to reduce the influence of laser cladding energy on the normal tissue of the matrix, and the energy can be controlled to be 20% to act in a repairing area (namely the normal tissue of the matrix), so that the heat affected zone of a workpiece is ensured to be less than or equal to 1mm, the bonding strength of a laser cladding layer and the normal tissue of the matrix is ensured to be more than or equal to 700Mpa, and the mechanical property of the repaired air gun is ensured to meet the use requirement.
The inventor finds in the study that when the interlayer temperature is higher than 150 ℃ during cladding, the thermal stress at the normal tissue of the matrix on the air gun is larger, the radial deformation exceeds 0.1mm, and moving parts in the air gun are blocked, so that the normal use of the air gun is affected. Therefore, in the cladding process, the interlayer temperature can be controlled to be less than or equal to 150 ℃ so as to reduce the radial deformation of the air gun and ensure the normal use of the air gun in the later period.
In step 140, a continuous high-power fiber laser can be adopted to generate a fiber laser beam to carry out laser cladding on the normal tissue of the matrix on the air gun, the power is controlled to be 2800W-3200W, the speed is controlled to be 400 mm/min, the laser beam is protected by inert gas, the normal tissue of the matrix is instantaneously heated to be molten by the laser beam during cladding, and the alloy powder prepared from the alloy material is automatically fed to a molten pool through a coaxial powder feeding technology at the moment, so that a metallurgically bonded cladding layer is formed at the normal tissue of the matrix, the cladding time is extremely short, the heat affected zone of a workpiece is ensured to be less than or equal to 1mm, and the cladding layer tissue is fine and has no defects such as crack air holes. If the heat affected zone of the workpiece is larger than 1mm, hidden dangers such as coarse grains, cracks and the like of the cladding layer can be caused.
Specifically, the spraying device of the automatic powder feeder and the inert gas protection device can be assembled and installed on the laser cladding head, the automatic powder feeder and the inert gas protection device are firmly fixed through a clamp, the flow control valves are arranged on the spraying device of the automatic powder feeder and the inert gas protection device, the powder feeding speed is controlled to be 2-5g/min, the powder feeding speed is controlled to be 4-6L/min, the inert gas speed is controlled to be 10-15L/min, the thickness of single-layer laser cladding is controlled to be 0.1-0.2mm, the multi-layer cladding is completed, and finally the cladding layer and normal tissues of a substrate are metallurgically bonded, so that the hardness of the formed cladding layer is HRC30-35.
With continued reference to FIG. 1, in an alternative embodiment, the air gun surface remediation method further comprises:
step 150: the laser cladding layer is inspected by using X-rays.
In this step, cracks, impurities, and fusion conditions of the laser cladding layer can be specifically checked to ensure that the laser cladding layer satisfies performance requirements.
Further, with continued reference to FIG. 1, in an alternative embodiment, the air gun surface remediation method further comprises:
step 160: and (3) at the ageing temperature of 610-630 ℃, preserving the heat of the repaired air gun for four hours, and then cooling the air gun at normal temperature.
The hardness of the air gun can reach more than or equal to 300HB.
Further, referring to fig. 1, in an alternative manner, in step 140, a machining allowance of 0.1-0.2mm is left for the thickness of the laser cladding layer formed after laser cladding.
In the step, the thickness of the laser cladding layer is kept to be 0.1-0.2mm, namely, the laser cladding layer protrudes from the normal surface of the air gun by 0.1-0.2mm.
The air gun surface repair method further comprises the following steps:
step 170: grinding the surface of the laser cladding layer to enable the laser cladding layer to be flush with the surrounding normal surface;
step 180: and performing secondary inspection on the grinding area by adopting X-rays.
The following examples are given by way of illustration:
example 1
Treating the damaged surface of the air gun to expose the normal tissue of the matrix of the air gun;
measuring the repair thickness between the exposed normal tissue of the substrate and the normal surface of the air gun;
determining a laser cladding thickness according to the repair thickness, wherein the laser cladding thickness is larger than or equal to the repair thickness;
and (3) carrying out laser cladding on the normal tissue of the matrix by adopting other alloy powder to repair the damaged surface of the air gun, wherein the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 0.309%, nickel 4.9%, niobium 0.296%, manganese 0.75%, chromium 10%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 2
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 0.309%, nickel 4.9%, niobium 0.4%, tantalum 0.15%, manganese 0.75%, chromium 10%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 3
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 0.309%, nickel 4.7%, niobium 0.42%, tantalum 0.18%, manganese 0.85%, chromium 10%, silicon 0.8%, copper 0.4%, and the balance iron.
Example 4
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 0.309%, nickel 5.1%, niobium 0.45%, tantalum 0.2%, manganese 0.65%, chromium 10%, silicon 0.8%, copper 0.2%, and the balance iron.
Example 5
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 10%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 6
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 10%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 7
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 14%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 8
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 0.8%, copper 0.3%, and the balance iron.
Example 9
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.5%, copper 0.3%, and the balance iron.
Example 10
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.8%, copper 0.3%, and the balance iron.
Example 11
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.8%, boron 0.9%, copper 0.3%, and the balance iron.
Example 12
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.02%, sulfur 0.02%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.8%, boron 0.94%, copper 0.3%, and the balance iron.
Example 13
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.03%, sulfur 0.03%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.8%, boron 0.94%, copper 0.3%, and the balance iron.
Example 14
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: carbon 0.07%, phosphorus 0.04%, sulfur 0.055%, molybdenum 1.2%, nickel 4.9%, niobium 0.45%, tantalum 0.2%, manganese 0.75%, chromium 16%, silicon 1.8%, boron 0.94%, copper 0.3%, and the balance being iron.
Example 15
The process flow is the same as that of the embodiment 1, and alloy powder prepared from the alloy materials is adopted, and the alloy powder comprises the following materials in percentage by mass: 0.1% of carbon, 0.04% of phosphorus, 0.055% of sulfur, 1.2% of molybdenum, 4.9% of nickel, 0.45% of niobium, 0.2% of tantalum, 0.75% of manganese, 16% of chromium, 1.8% of silicon, 0.94% of boron, 0.3% of copper and the balance of iron.
The surface hardness of the laser cladding layer on the air gun in each test piece in examples 1 to 15 was measured by HXD-1000TMC/LCD micro Vickers hardness tester, and the results are shown in Table 1 below:
TABLE 1
As can be seen from comparison of examples 1 and examples 2, 3 and 4 in Table 1, the surface hardness of the laser cladding layer can be effectively improved by increasing the niobium content to 0.4% -0.45% and adding 0.15% -0.2% of tantalum, the hardness is increased to 320.6HB from the original 269.4HB, and the secondary service life of the air gun can be further prolonged. As is clear from comparison of examples 8 and examples 9 and 10, the silicon content was increased to 1.5% -1.8%, and the surface hardness of the laser cladding layer was increased from the original 320.6HB to 326.4HB, thereby further increasing the surface hardness of the laser cladding layer. As is clear from comparison of examples 10 with examples 11 and 12, when boron is added in an amount of 0.9% -0.94%, the surface hardness of the laser cladding layer can be further improved up to 327.0HB. As can be seen from comparison of examples 12 and examples 13 and 14, the surface hardness of the laser cladding layer is further improved up to 328.9HB after the content of phosphorus is increased to 0.03% -0.04% and the content of sulfur is increased to 0.03% -0.055%. As can be seen from the comparison between the embodiment 14 and the embodiment 15, the carbon content is increased to 0.1%, so that the surface hardness of the laser cladding layer can be increased again to 330.7HB, the structural strength of the repaired air gun can be sufficiently increased, the secondary service life of the air gun can be prolonged, and the cost can be reduced.
The alloy materials prepared by the component proportions in examples 1 to 15 were subjected to elongation and reduction of area detection tests, and the results are shown in the following table 2:
TABLE 2
As can be seen from comparison of examples 6 and examples 7 and 8 in table 2, by increasing the chromium content from 10% to 14% -16%, the elongation of the alloy material is increased from 11 to 15 and 18, and the reduction of area is increased from 42 to 47 and 53, so that the shaping of the alloy material is improved and the alloy material is not easily damaged.
The surface hardness of the laser cladding layer on the air gun in each test piece in examples 1 to 15 was subjected to abrasion resistance analysis, and the abrasion loss of the material in the abrasion resistance detection test was obtained by mass change, which was referred to as mass abrasion loss, i.e., Δm=mb-Ma, where Δm is mass abrasion loss in mg; mb is the mass before abrasion in mg; ma is the mass after abrasion in mg. The wear rate is expressed as the amount of wear per unit time, i.e., iw=Δm/Δt, where Iw is the wear rate; Δt is the wear time in s. The wear resistance is expressed as the reciprocal of the wear rate under certain friction conditions, i.e. rw=1/iw=Δt/Δm, where Rw is the wear resistance in s/mg. From the above calculation, it is known that the abrasion resistance is inversely proportional to the abrasion rate in the case where the test piece is fixed, that is, the smaller the abrasion amount, the better the abrasion resistance.
The abrasion resistance was specifically tested as shown in Table 3 below:
TABLE 3 Table 3
As is clear from comparison of example 4 with examples 5 and 6 in Table 3, the content of molybdenum was increased to 1% -1.2%, and the abrasion loss per unit time of the laser cladding layer was reduced to a minimum of 0.153mg. As can be seen from comparison of examples 12 and examples 13 and 14, the phosphorus content is increased to 0.03% -0.04%, and the sulfur content is increased to 0.03% -0.055%, so that the abrasion loss of the laser cladding layer in unit time is reduced to 0.125mg, and the abrasion resistance of the laser cladding layer is further improved. As can be seen from the comparison between the embodiment 14 and the embodiment 15, the carbon content is further increased to 0.1%, so that the abrasion loss per unit time of the laser cladding layer can be continuously reduced to 0.110mg, the abrasion resistance of the laser cladding layer is fully improved, and the secondary service life of the air gun is prolonged.
Based on the environmental characteristics of air gun operation, the salt spray test is adopted to detect the corrosion resistance of the material of the laser cladding layer on the air gun, and the specific test method is as follows: a saline spray tester was used to attach a sodium chloride solution in spray form to the air gun maintenance sample surface. The test conditions were: the concentration of the sodium chloride solution is 50-60g/L; the pH value is 6.7-7.0; the pressure of the pressure barrel is controlled to be 19-2.1kgf/cm 2 And continuously testing; the spraying amount is 1-2ml/80cm 2 Collecting once in 16 hours; the test temperature was 34-36℃and the spraying time was 96 hours. The test results are shown in Table 4 below:
TABLE 4 Table 4
As can be seen by comparing examples 1-4 with examples 5-12, the corrosion resistance of the laser cladding layer can be fully improved by increasing the molybdenum content to 1% -1.2%, and the defect area is as low as 0.12%, so that the repaired air gun can be operated for a longer time in a corrosive environment. As is clear from comparison of examples 12 and examples 13 to 14, the corrosion resistance of the laser cladding layer can be further improved by increasing the phosphorus content to 0.03% -0.04% and the sulfur content to 0.03% -0.055%, and the defect area can be as low as 0.08%. As is clear from the comparison between example 14 and example 15, the corrosion resistance of the laser cladding layer can be improved again by increasing the carbon content to 0.1%, and the defect area can be increased to 0.06%.
In the process of continuously optimizing and improving the component proportion of the alloy material, the inventor initially increases the carbon content to 0.2%, the phosphorus content to 0.06% and the silicon content to 2.2% silicon in order to improve the hardness of the air gun, and through experimental detection, the hardness and wear resistance of the alloy material are improved, but the toughness of the alloy material is reduced greatly, so that the air gun is easy to corrode and crack after being repaired by the alloy material, and the secondary service life of the air gun is influenced.
Based on the above problems, the above teaching and training is absorbed in the aspect of alloy material proportion of air gun repair, the alloy component material proportion is adjusted again, the carbon component is controlled to be about 0.07-0.1%, the phosphorus is controlled to be 0.02-0.04%, the sulfur is controlled to be 0.02-0.055%, the molybdenum is controlled to be 0.309-1.2%, the nickel is controlled to be 4.7-5.1%, the niobium is controlled to be 0.4-0.45%, the tantalum is controlled to be 0.15-0.2%, the manganese is controlled to be 0.65-0.85%, the chromium is controlled to be 10-16%, the silicon is controlled to be 0.8-1.8%, and the copper is controlled to be 0.2-0.4%, so that the normal use of the functions of the air gun after repair is ensured, the durability of the air gun is improved, the service life of the air gun is prolonged, and the purpose of repairing the air gun surface is achieved.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; while the application has been described in detail with reference to the foregoing embodiments, those skilled in the art will appreciate that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the application, and are intended to be included within the scope of the appended claims and description. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.

Claims (4)

1. An alloy material, characterized by comprising, in mass percent: 0.07% -0.1% carbon, 0.03% -0.04% phosphorus, 0.03% -0.055% sulfur, 0.309% -1.2% molybdenum, 4.7% -5.1% nickel, 0.42% -0.45% niobium, 0.18% -0.2% tantalum, 0.65% -0.85% manganese, 10% -16% chromium, 1.5% -1.8% silicon, 0.2% -0.4% copper, and 0.9% -0.94% boron, the balance being iron;
wherein, the alloy material can guarantee the hardness of the material of the air gun after repairing the abrasion surface of the air gun.
2. Alloy material according to claim 1, characterized in that the molybdenum content is 1%.
3. Alloy material according to claim 1 or 2, characterized in that the chromium content is 14%.
4. A method of repairing a surface of an air gun, comprising:
treating the damaged surface of the air gun to expose normal tissues of a matrix of the air gun;
measuring the repair thickness between the exposed normal tissue of the substrate and the normal surface of the air gun;
determining a laser cladding thickness according to the repair thickness, wherein the laser cladding thickness is greater than or equal to the repair thickness;
an alloy powder made of the alloy material according to any one of claims 1 to 3 is laser-clad at the normal tissue of the matrix according to the laser cladding thickness, repairing the damaged surface of the air gun.
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2270245A1 (en) * 2009-06-16 2011-01-05 Daido Tokushuko Kabushiki Kaisha Hot work tool steel and steel product using the same
US20180009031A1 (en) * 2016-07-06 2018-01-11 Seiko Epson Corporation Metal powder for powder metallurgy, compound, granulated powder, and sintered body
CN109023358A (en) * 2018-10-16 2018-12-18 宁夏昀启昕机械再制造有限公司 A kind of the laser melting coating restorative procedure and reparation powder of mine hydraulic support

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2270245A1 (en) * 2009-06-16 2011-01-05 Daido Tokushuko Kabushiki Kaisha Hot work tool steel and steel product using the same
US20180009031A1 (en) * 2016-07-06 2018-01-11 Seiko Epson Corporation Metal powder for powder metallurgy, compound, granulated powder, and sintered body
CN109023358A (en) * 2018-10-16 2018-12-18 宁夏昀启昕机械再制造有限公司 A kind of the laser melting coating restorative procedure and reparation powder of mine hydraulic support

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