CN103307109A - Method for manufacturing wear-resistant bearing bush - Google Patents
Method for manufacturing wear-resistant bearing bush Download PDFInfo
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- CN103307109A CN103307109A CN2013102635442A CN201310263544A CN103307109A CN 103307109 A CN103307109 A CN 103307109A CN 2013102635442 A CN2013102635442 A CN 2013102635442A CN 201310263544 A CN201310263544 A CN 201310263544A CN 103307109 A CN103307109 A CN 103307109A
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000004519 manufacturing process Methods 0.000 title abstract description 4
- 239000000956 alloy Substances 0.000 claims abstract description 46
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 45
- 239000011248 coating agent Substances 0.000 claims abstract description 28
- 238000000576 coating method Methods 0.000 claims abstract description 28
- 229910052761 rare earth metal Inorganic materials 0.000 claims abstract description 22
- 150000002910 rare earth metals Chemical class 0.000 claims abstract description 17
- 238000009718 spray deposition Methods 0.000 claims abstract description 16
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 48
- 239000010949 copper Substances 0.000 claims description 45
- 229910052802 copper Inorganic materials 0.000 claims description 42
- 239000000843 powder Substances 0.000 claims description 31
- 239000011159 matrix material Substances 0.000 claims description 30
- 238000002360 preparation method Methods 0.000 claims description 20
- 239000007921 spray Substances 0.000 claims description 20
- 239000002245 particle Substances 0.000 claims description 17
- 239000002994 raw material Substances 0.000 claims description 16
- 239000001996 bearing alloy Substances 0.000 claims description 15
- 238000002156 mixing Methods 0.000 claims description 15
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 11
- 238000002844 melting Methods 0.000 claims description 11
- 230000008018 melting Effects 0.000 claims description 11
- 230000008569 process Effects 0.000 claims description 11
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 10
- 238000007499 fusion processing Methods 0.000 claims description 10
- 239000007789 gas Substances 0.000 claims description 10
- 239000011812 mixed powder Substances 0.000 claims description 10
- 238000005507 spraying Methods 0.000 claims description 10
- 238000005303 weighing Methods 0.000 claims description 10
- 230000015572 biosynthetic process Effects 0.000 claims description 7
- 229910052684 Cerium Inorganic materials 0.000 claims description 6
- 229910052777 Praseodymium Inorganic materials 0.000 claims description 6
- 229910010413 TiO 2 Inorganic materials 0.000 claims description 6
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 229910052746 lanthanum Inorganic materials 0.000 claims description 6
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims description 6
- PUDIUYLPXJFUGB-UHFFFAOYSA-N praseodymium atom Chemical compound [Pr] PUDIUYLPXJFUGB-UHFFFAOYSA-N 0.000 claims description 6
- 229910052779 Neodymium Inorganic materials 0.000 claims description 5
- 238000000889 atomisation Methods 0.000 claims description 5
- 230000004927 fusion Effects 0.000 claims description 5
- 238000003754 machining Methods 0.000 claims description 5
- 238000002663 nebulization Methods 0.000 claims description 5
- QEFYFXOXNSNQGX-UHFFFAOYSA-N neodymium atom Chemical compound [Nd] QEFYFXOXNSNQGX-UHFFFAOYSA-N 0.000 claims description 5
- 229910052757 nitrogen Inorganic materials 0.000 claims description 5
- 238000010107 reaction injection moulding Methods 0.000 claims description 5
- 239000004576 sand Substances 0.000 claims description 5
- 238000003756 stirring Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 abstract description 28
- 230000008901 benefit Effects 0.000 abstract description 5
- 229910000881 Cu alloy Inorganic materials 0.000 abstract description 4
- WMOHXRDWCVHXGS-UHFFFAOYSA-N [La].[Ce] Chemical compound [La].[Ce] WMOHXRDWCVHXGS-UHFFFAOYSA-N 0.000 abstract 1
- 229910000906 Bronze Inorganic materials 0.000 description 12
- 239000010974 bronze Substances 0.000 description 12
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 12
- 230000000694 effects Effects 0.000 description 11
- 229910001369 Brass Inorganic materials 0.000 description 10
- 239000010951 brass Substances 0.000 description 10
- 239000002131 composite material Substances 0.000 description 10
- 239000000853 adhesive Substances 0.000 description 7
- 230000001070 adhesive effect Effects 0.000 description 7
- 239000011133 lead Substances 0.000 description 7
- 239000000835 fiber Substances 0.000 description 6
- 229910052790 beryllium Inorganic materials 0.000 description 5
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 5
- 230000035882 stress Effects 0.000 description 5
- 229910000611 Zinc aluminium Inorganic materials 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- 238000005266 casting Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 238000005728 strengthening Methods 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 229910000570 Cupronickel Inorganic materials 0.000 description 2
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 239000003082 abrasive agent Substances 0.000 description 2
- 230000032683 aging Effects 0.000 description 2
- YOCUPQPZWBBYIX-UHFFFAOYSA-N copper nickel Chemical compound [Ni].[Cu] YOCUPQPZWBBYIX-UHFFFAOYSA-N 0.000 description 2
- 238000011161 development Methods 0.000 description 2
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- 238000005461 lubrication Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 229910052725 zinc Inorganic materials 0.000 description 2
- 239000011701 zinc Substances 0.000 description 2
- 208000002874 Acne Vulgaris Diseases 0.000 description 1
- 229910001181 Manganese brass Inorganic materials 0.000 description 1
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 206010000496 acne Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- HXFVOUUOTHJFPX-UHFFFAOYSA-N alumane;zinc Chemical compound [AlH3].[Zn] HXFVOUUOTHJFPX-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
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- 239000002783 friction material Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
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Abstract
The invention relates to a method for manufacturing a wear-resistant bearing bush. The method comprises the steps of: firstly, adding a copper alloy material to lanthanum-cerium mixed rare-earth metal; manufacturing a bearing bush alloy body by spray deposition; and then preparing a coating material and finishing the coating by a plasma jet method. Compared with the traditional cast copper alloy, the wear-resistant bearing bush has the advantages that the wear-resisting property of the wear-resistant bearing bush is obviously improved; the wear rate is greatly reduced; and the corresponding coating has excellent tribological property.
Description
Technical field
The present invention relates to a kind of preparation method of high-abrasive material, relate in particular to a kind of preparation method of abrasion-proof bearing bush.
Background technique
Copper is human discovery and uses one of metal the earliest, is characterized in having very high conduction, heat-conducting property and good plasticity, is only second to gold and silver and occupies the 3rd at these aspect of performances.Although its life-span is long, aspect metallurgy of copper, still make progress continuing.Fine copper has the face-centered cubic character, no allotropic transformation, and plasticity height and intensity is low should not directly be used as structural material, many raw materials as the preparation Cuprum alloys.
The intensity of fine copper is not high, therefore will satisfy the requirement of structural member, must carry out the alloyage of copper.The purpose of the alloyage of copper mainly is in order to realize that solution strengthening, ageing strengthening and surplus strengthen mutually, thereby obtains high strength copper alloy.According to traditional sorting technique, usually by the in addition rough segmentation of red copper, brass, bronze, copper-nickel alloy four big series.Red copper is fine copper and adds a small amount of other element, be called brass with zinc as the Cuprum alloy of main added elements, add elements such as Al, Fe, Si, Mn, Pb, Ni on the basis of binary brass and form special brass, be called aluminium brass, iron brass, silicon brass, manganese brass, lead brass, nickel brass by adding the second main difference of adding element.Be not the bronze that is called of main added elements with zinc, can be divided into tin bronze, aluminum bronze, lead bronze, beryllium bronze etc. again by the difference of main added elements, they have the intensity higher than basis brass, hardness, corrosion resistance and advantages of good casting.Be the copper-nickel alloy that is called of main added elements with nickel.Copper and Cuprum alloy become one of important foundation material of modern industry with good heat transfer electric conductivity, high corrosion resisting property, advantages of good casting and mechanical property and suitable intensity, occupy critical role in national economy.Cuprum alloy is stranded and has the performance of high strength and high conductivity heat conduction and wear-and corrosion-resistant and become the indispensable metallic material of modern industry.
Along with the development that modern science and technology are maked rapid progress, modern industry is to the demands for higher performance of Cuprum alloy, as highi degree of accuracy, high-performance and all many-sides such as economical and practical.At present, the research of zinc-aluminum based alloy (ZA) is used and obtained gratifying achievement, and its superior mechanical property and good casting technique performance and machinability attract people's attention, and is disconnected in high strength alloy side, and the trend that replaces Cuprum alloy is gradually arranged.But this alloy is the same with any alloy series, part also comes with some shortcomings, wherein some is because the person's character of alloy determines, should not improve, as: easily produce gravity segregation, certain shrinkage porosite tendency is arranged, easily produce during sand casting process and pull defective, thermal expansion coefficient is bigger, aging potential risk etc. is arranged, and the problem that the ZA alloy is used for the conductive plate material is poorly conductive, and the application of ZA alloy will mainly concentrate on oneself part of knowing of the wearing piece that regularly replaces and easily damaged parts or some other length of service from now on.Thereby the ZA alloy still can not replace Cuprum alloy fully in some aspects, over a period to come, still is necessary to develop the new copper alloy.
The copper based wear-resistant alloy is traditionally based on all kinds of bronze, brass, with they be processed into section bar or cast product is used.Plate, band, pipe, rod, wire rod good combination property as beryllium bronze, thermal conductivity is good, after the heat treatment, intensity is even, wear resistant corrosion resistant, castability is good, be suitable for making various wear parts and at a high speed, bearing, the lining of working under high pressure and the high temperature, but the public hazards that beryllium bronze is expensive because of it, beryllium is malicious and yield rate are low the production of this alloy and use are restricted.The BeO powder that beryllium bronze is emitted in operations such as melting, processing has very big harm to human body, and environmental protection equipment also will carry out investment.Titan bronze also has good advantages such as wear resistance, and as high elasticity, high strength, the various electronic components of high abrasion, small-sized precision gear and various bearing, but Ti metal is also comparatively expensive.The crystallization range of aluminum bronze is very little, good fluidity, and dense structure, but its linear shrinkage ratio is big, unreasonable if pouring system arranges, can crack.
Because copper base alloy raising to intensity when keeping electric-conductivity heat-conductivity high has certain limit, and complex intensifying can be brought into play the synergy of matrix electric-conductivity heat-conductivity high and reinforcing material simultaneously, has very big design freedom again.Therefore in recent ten years, developed countries such as U.S., day are very active to the development of this class material, and China's starting is then later relatively.Complex intensifying can obviously not reduce the conductivity of copper matrix, and can also improve room temperature and the high-temperature behavior of matrix.Its basic principle is: according to the requirement of material design performance, select for use suitable reinforcing phase (one or more) to add matrix, when keeping the matrix high conductivity, give full play to the invigoration effect of reinforcing phase, make the conductivity of material and intensity reach good coupling.According to the form of reinforcing phase, can be divided into the high-strength high conductivity heat-conducting copper-based composite material: granule reinforced copper base composite material and fiber reinforcement Cu-base composites.Particulate reinforced composite refers to generate the second phase particle that disperse distributes artificially or by certain technology original position in the copper matrix.The second phase particle has hindered the motion of dislocation, thereby has improved the intensity of material, as A1203/Cu composite material, TiC/Cu composite material.The fiber reinforcement Cu-base composites refers to the fiber that the adding rule oriented is arranged in the copper matrix artificially or the second phase fiber that generates directed proper alignment between homogeneous phase by certain technology original position, fiber increases the dislocation motion resistance, thereby metallic matrix is strengthened, as C/Cu, Fe/Cu original position deformed composite material.The compound sharp material of copper base also can be used for various friction conditions and the occasion of high strength and high conductivity heat conduction requirement is arranged, as the electrode brush etc.The shortcoming of Cu-base composites is exactly to need special equipment, because the wettability of fiber and copper matrix is relatively poor, thereby preparation process's difficulty, cost is higher.
Usually the wearing and tearing of material are categorized as by wearing and tearing mechanism: 1. adhesive wear, 2. abrasive wear, 3. fatigue wear, 4. corrosive wear.
The adhesive wear of material lost efficacy and referred in friction process, produce in the state on friction pair material surface: given birth to the adhesion shearing effect, make inefficacy that friction material surface comes off or that cause to the transfer of antithesis surface, it is characterized in that sending out spread friction pair material by a surface to another surface or the migration of asking each other, adhesion node intensity is more high, it is more dark to shear the degree of depth, and it is more serious to wear and tear, until adhesion wear takes place.The possibility that the adhesive wear inefficacy takes place is relevant with the material of friction pair material.The easier generation adhesive wear of friction pair that the elastoplastic material that chemical property is similar, intersolubility is good (as metal of the same race) constitutes; Adhesive wear owing to do not form as yet at starting moment oil film, very likely takes place and lost efficacy in the heavy-duty machinery of some liquid hydrodynamic lubrications.Improve lubricatedly, especially adopt the solid lubricant that self-lubricating property is arranged. or to mate friction pair material again be prevention or the main path of avoiding adhesive wear to lose efficacy.
Abrasive wear lost efficacy refer to by extraneous grit or even part table and the friction table that in friction process, causes of hard protrusion thing and material is cut and is come off or inefficacy that plastic deformation causes; cause the wearing and tearing of component failure to come from abrasive particle to the plow effect on friction pair material surface and the extrusion-deformation of kniting the brows property, exist the hard abrasive well to produce tangible abrasive particle at friction surface and scratch the necessary condition that vestige is the judgement abrasive wear.The wear out failure of this form extensively is present in the more abominable machinery of all kinds of environmental conditionss, sometimes be not be owing to the design on reason, having certain sporadicly, is to reduce the main path that sporadic abrasive wear lost efficacy by the maintenance of strengthening equipment and lubricating management.
Fatigue wear lost efficacy and to refer to surface of friction pair under the contact stress effect of circulation change, because fatigue of materials is peeled off and formed pit and cause inefficacy.In general, even under good lubricating condition, the fatigue wear of surface of friction pair lost efficacy still inevitable, but showed as the Surface fatigue wearing and tearing of non-expansivity mostly.The Surface fatigue wearing and tearing that the fatigue wear of parts lost efficacy and mainly comes from expansivity, its process comprises because the effect (containing rolling friction) of periodically variable normal load and tangent direction friction power, at friction pair subsurface stress raiser germinating microscopic crack, crackle expands to the surface, forms wearing and tearing.It is characterized in that existing at friction surface the pit of acne spot shape.The wearing and tearing of this form and load character and forms of motion have substantial connection.Impurity in the friction pair material, hole, dislocation and internal stress etc. owing to destroyed the continuity of matrix, under the effect of cyclic stress, form stress raiser, are easy to generate fatigue crack and cause wearing and tearing.
Corrosive wear was lost efficacy and was referred in friction process, chemistry or electrochemistry watt effect have mutually taken place with environment in friction pair material, this effect aggravation, the wear process of material and the inefficacy that causes, it is characterized in that chemical corrosion and mechanical wear exist simultaneously and promotion mutually, depositing aggressive medium between the friction pair is the necessary condition that corrosive wear was lost efficacy, and the abrasive dust of formation should be the product of friction pair material and medium chemical action.
At present, the formation of bearing high-abrasive material tissue mainly is distributed on the hard matrix by soft dispersed network phase, improve the wear-resisting property of material, must improve particle size and the distribution of dispersed network phase, improve the performance of matrix simultaneously, existing alloy also exists organizes not enough refinement, the shortcoming that matrix strength is lower, the working life of having limited internal-combustion engine middle (center) bearing material.The working environment of bearing also requires the more excellent coating of wear-resisting property simultaneously.
Summary of the invention
The object of the present invention is to provide a kind of preparation method of abrasion-proof bearing bush.
The present invention is achieved by the following technical solutions: a kind of abrasion-proof bearing bush, it is characterized in that it comprises alloy body and wear resistant coating, and wherein the alloy body is made up of following components in weight percentage:
Copper 76 ~ 83 wt%
Rare earth metal 0.6 ~ 1.9 wt%
Tin 5.5 ~ 7.8 wt%
Surplus is plumbous;
Wherein, the weight percent of described rare earth metal consists of:
Cerium 46 ~ 49 wt%
Lanthanum 17 ~ 31 wt%
Praseodymium 4 ~ 7 wt%
Neodymium 11 ~ 18 wt%
Surplus is other rare earth elements;
The following components in weight percentage of wear resistant coating is formed:
TiO
2 25~55wt.%
NiCrBSiFe 9~27wt.%
Cr
2O
3 20~38wt.%
C-Ni 10 ~ 15wt.%, wherein the Ni weight content is 60 ~ 75%
The powder diameter of above-mentioned each component is 20 ~ 80 μ m;
The preparation method of above-mentioned abrasion-proof bearing bush may further comprise the steps:
A, preparation bearing alloy body
(1) said ratio according to the alloy body takes by weighing each raw material components;
(2) outside the preceding copper removal of melting, other object that need put into body of heater all toasts about 1 hour to prevent bringing steam at fusion process at 200 ℃ of baking ovens;
(3) baking expects to finish electrolytic copper, tin and lead are put into intermediate frequency furnace, earlier with small-power heating 3 ~ 5 minutes, add then and high-powerly add rare earth metal again after making above-mentioned raw materials fusing, melting 20 ~ 30min under 1150 ~ 1250 ℃ temperature then, fusion process stirs 3 ~ 5 times, mixes to reach fully;
(4) adopt the reaction-injection moulding device, after above-mentioned alloy was melted again, carry out the supersonic airstream spray deposition process of alloy with ultrasonic nebulization jet nozzle: atomization gas was nitrogen, gas flow 650L/min; The distance of spray deposition is 40cm, and spray deposition finishes to make the copper based wear-resistant alloy;
(5) make the bearing alloy body through machining as requested;
B, preparation wear resistant coating
(6) said ratio according to wear resistant coating takes by weighing each raw material components;
(7) the said components powder is carried out mechanical mixing, the powder mixing machine time was not less than 30 minutes;
(8) sand blast is carried out on the surface of bearing alloy body;
(9) powder after the above-mentioned mechanical mixing is sprayed as feeding, form the high temperature and high speed plasma jet by plasma gun, select Ar throughput 39L/min, H
2Throughput 9L/min, electric current 600A, spray power is about 42Kw, spray distance 100mm, after powder feeding rate 40g/min powder feeding air-flow promotion mixed powder entered plasma jet, mixed powder was heated to fusion or semi-molten state rapidly, and is accelerated by plasma jet, the spraying particle bundle of matrix surface is flown in formation, and particle beam strikes through matrix surface; Each spraying blanking time is 10min at least, and each coating thickness is not higher than 50 μ m, treats that the matrix surface temperature is lower than 200 ℃ and sprays next time again;
(10) spray the coating that finally obtains about 200 μ m repeatedly, make abrasion-proof bearing bush at last.
Technique effect of the present invention and advantage are: at first, the invention provides high-performance copper based wear-resistant alloy body, this alloy is owing to added rare earth metals such as cerium, lanthanum, praseodymium, and after having adopted this preparation process's preparation of jet deposition, its matrix strength, hardness and self lubricity further improve, be significantly improved at wear-resisting property thereby compare traditional casting copper base alloy, wear rate then significantly reduces.Secondly, cladding material of the present invention has comprised ceramic matrix TiO
2, less and the Cr with extreme hardness, wear resistance of particle
2O
3As strengthening particle, can improve the self-fluxing alloy NiCrBSiFe of adhesive strength between the composite material, toughness, have the lubriation material C-Ni of good solid lubrication effect, can significantly improve abrasion property, cohesion strength, resistance to cracking, and reduce the friction factor of coating effectively.
Embodiment
For technological means, creation characteristic that the present invention is realized, reach purpose and effect is easy to understand, below in conjunction with specific embodiment, further set forth the present invention.
Embodiment 1:
A, preparation bearing alloy body
(1) take by weighing each raw material components of alloy body according to following proportioning,
Copper 76 wt%
Rare earth metal 0.6 wt%
Tin 7.8 wt%
Surplus is plumbous;
Wherein, the weight percent of described rare earth metal consists of:
Cerium 46 wt%
Lanthanum 17 wt%
Praseodymium 4 wt%
Neodymium 18 wt%
Surplus is other rare earth elements;
(2) outside the preceding copper removal of melting, other object that need put into body of heater all toasts about 1 hour to prevent bringing steam at fusion process at 200 ℃ of baking ovens;
(3) baking expects to finish electrolytic copper, tin and lead are put into intermediate frequency furnace, earlier with small-power heating 3 minutes, add then and high-powerly add rare earth metal again after making the above-mentioned raw materials fusing, then melting 30min under 1150 ℃ temperature, fusion process stirs 5 times, mixes to reach fully;
(4) adopt the reaction-injection moulding device, after above-mentioned alloy was melted again, carry out the supersonic airstream spray deposition process of alloy with ultrasonic nebulization jet nozzle: atomization gas was nitrogen, gas flow 650L/min; The distance of spray deposition is 40cm, and spray deposition finishes to make the copper based wear-resistant alloy;
(5) make the bearing alloy body through machining as requested;
B, preparation wear resistant coating
(6) take by weighing each raw material components of wear resistant coating according to following proportioning;
TiO
2 25wt.%
NiCrBSiFe 9wt.%
Cr
2O
3 20wt.%
C-Ni 15wt.%, wherein the Ni weight content is 60%
The powder diameter of above-mentioned each component is 20 ~ 80 μ m;
(7) the said components powder is carried out mechanical mixing, the powder mixing machine time was not less than 30 minutes;
(8) sand blast is carried out on the surface of bearing alloy body;
(9) powder after the above-mentioned mechanical mixing is sprayed as feeding, form the high temperature and high speed plasma jet by plasma gun, select Ar throughput 39L/min, H
2Throughput 9L/min, electric current 600A, spray power is about 42Kw, spray distance 100mm, after powder feeding rate 40g/min powder feeding air-flow promotion mixed powder entered plasma jet, mixed powder was heated to fusion or semi-molten state rapidly, and is accelerated by plasma jet, the spraying particle bundle of matrix surface is flown in formation, and particle beam strikes through matrix surface; Each spraying blanking time is 10min at least, and each coating thickness is not higher than 50 μ m, treats that the matrix surface temperature is lower than 200 ℃ and sprays next time again;
(10) spray the coating that finally obtains about 200 μ m repeatedly, make abrasion-proof bearing bush at last.
Embodiment 2
A, preparation bearing alloy body
(1) take by weighing each raw material components of alloy body according to following proportioning,
Copper 79 wt%
Rare earth metal 1.2 wt%
Tin 6.3 wt%
Surplus is plumbous;
Wherein, the weight percent of described rare earth metal consists of:
Cerium 47 wt%
Lanthanum 21 wt%
Praseodymium 5 wt%
Neodymium 15 wt%
Surplus is other rare earth elements;
(2) outside the preceding copper removal of melting, other object that need put into body of heater all toasts about 1 hour to prevent bringing steam at fusion process at 200 ℃ of baking ovens;
(3) baking expects to finish electrolytic copper, tin and lead are put into intermediate frequency furnace, earlier with small-power heating 4 minutes, add then and high-powerly add rare earth metal again after making the above-mentioned raw materials fusing, then melting 25min under 1200 ℃ temperature, fusion process stirs 4 times, mixes to reach fully;
(4) adopt the reaction-injection moulding device, after above-mentioned alloy was melted again, carry out the supersonic airstream spray deposition process of alloy with ultrasonic nebulization jet nozzle: atomization gas was nitrogen, gas flow 650L/min; The distance of spray deposition is 40cm, and spray deposition finishes to make the copper based wear-resistant alloy;
(5) make the bearing alloy body through machining as requested;
B, preparation wear resistant coating
(6) take by weighing each raw material components of wear resistant coating according to following proportioning;
TiO
2 35wt.%
NiCrBSiFe 13wt.%
Cr
2O
3 25wt.%
C-Ni 13wt.%, wherein the Ni weight content is 69%
The powder diameter of above-mentioned each component is 20 ~ 80 μ m;
(7) the said components powder is carried out mechanical mixing, the powder mixing machine time was not less than 30 minutes;
(8) sand blast is carried out on the surface of bearing alloy body;
(9) powder after the above-mentioned mechanical mixing is sprayed as feeding, form the high temperature and high speed plasma jet by plasma gun, select Ar throughput 39L/min, H
2Throughput 9L/min, electric current 600A, spray power is about 42Kw, spray distance 100mm, after powder feeding rate 40g/min powder feeding air-flow promotion mixed powder entered plasma jet, mixed powder was heated to fusion or semi-molten state rapidly, and is accelerated by plasma jet, the spraying particle bundle of matrix surface is flown in formation, and particle beam strikes through matrix surface; Each spraying blanking time is 10min at least, and each coating thickness is not higher than 50 μ m, treats that the matrix surface temperature is lower than 200 ℃ and sprays next time again;
(10) spray the coating that finally obtains about 200 μ m repeatedly, make abrasion-proof bearing bush at last.
Embodiment 3
A, preparation bearing alloy body
(1) take by weighing each raw material components of alloy body according to following proportioning,
Copper 83 wt%
Rare earth metal 1.9 wt%
Tin 5.5 wt%
Surplus is plumbous;
Wherein, the weight percent of described rare earth metal consists of:
Cerium 49 wt%
Lanthanum 31 wt%
Praseodymium 7 wt%
Neodymium 11 wt%
Surplus is other rare earth elements;
(2) outside the preceding copper removal of melting, other object that need put into body of heater all toasts about 1 hour to prevent bringing steam at fusion process at 200 ℃ of baking ovens;
(3) baking expects to finish electrolytic copper, tin and lead are put into intermediate frequency furnace, earlier with small-power heating 5 minutes, add then and high-powerly add rare earth metal again after making the above-mentioned raw materials fusing, then melting 20min under 1250 ℃ temperature, fusion process stirs 3 ~ 5 times, mixes to reach fully;
(4) adopt the reaction-injection moulding device, after above-mentioned alloy was melted again, carry out the supersonic airstream spray deposition process of alloy with ultrasonic nebulization jet nozzle: atomization gas was nitrogen, gas flow 650L/min; The distance of spray deposition is 40cm, and spray deposition finishes to make the copper based wear-resistant alloy;
(5) make the bearing alloy body through machining as requested;
B, preparation wear resistant coating
(6) take by weighing each raw material components of wear resistant coating according to following proportioning;
TiO
2 55wt.%
NiCrBSiFe 9wt.%
Cr
2O
3 38wt.%
C-Ni 10wt.%, wherein the Ni weight content is 75%
The powder diameter of above-mentioned each component is 20 ~ 80 μ m;
(7) the said components powder is carried out mechanical mixing, the powder mixing machine time was not less than 30 minutes;
(8) sand blast is carried out on the surface of bearing alloy body;
(9) powder after the above-mentioned mechanical mixing is sprayed as feeding, form the high temperature and high speed plasma jet by plasma gun, select Ar throughput 39L/min, H
2Throughput 9L/min, electric current 600A, spray power is about 42Kw, spray distance 100mm, after powder feeding rate 40g/min powder feeding air-flow promotion mixed powder entered plasma jet, mixed powder was heated to fusion or semi-molten state rapidly, and is accelerated by plasma jet, the spraying particle bundle of matrix surface is flown in formation, and particle beam strikes through matrix surface; Each spraying blanking time is 10min at least, and each coating thickness is not higher than 50 μ m, treats that the matrix surface temperature is lower than 200 ℃ and sprays next time again;
(10) spray the coating that finally obtains about 200 μ m repeatedly, make abrasion-proof bearing bush at last.
Above-mentioned a plurality of embodiments are tested, and the present invention makes the dry friction and wear rate of bearing shell body less than 15 * 10
-12m
3/ m, the coating average microhardness reaches 680Mpa.
Above-mentioned example only is explanation technical conceive of the present invention and characteristics, and its purpose is to allow the people who is familiar with this technology can understand content of the present invention and enforcement according to this, can not limit protection scope of the present invention with this.All spirit essence is done according to the present invention equivalent transformation or modification all should be encompassed within protection scope of the present invention.
Claims (1)
1. the preparation method of an abrasion-proof bearing bush is characterized in that, comprises following steps:
A, preparation bearing alloy body
(1) take by weighing each raw material components of alloy body according to following proportioning,
Copper 76 ~ 83 wt%
Rare earth metal 0.6 ~ 1.9 wt%
Tin 5.5 ~ 7.8 wt%
Surplus is plumbous;
Wherein, the weight percent of described rare earth metal consists of:
Cerium 46 ~ 49 wt%
Lanthanum 17 ~ 31 wt%
Praseodymium 4 ~ 7 wt%
Neodymium 11 ~ 18 wt%
Surplus is other rare earth elements;
(2) outside the preceding copper removal of melting, other object that need put into body of heater all toasts about 1 hour to prevent bringing steam at fusion process at 200 ℃ of baking ovens;
(3) baking expects to finish electrolytic copper, tin and lead are put into intermediate frequency furnace, earlier with small-power heating 3 ~ 5 minutes, add then and high-powerly add rare earth metal again after making above-mentioned raw materials fusing, melting 20 ~ 30min under 1150 ~ 1250 ℃ temperature then, fusion process stirs 3 ~ 5 times, mixes to reach fully;
(4) adopt the reaction-injection moulding device, after above-mentioned alloy was melted again, carry out the supersonic airstream spray deposition process of alloy with ultrasonic nebulization jet nozzle: atomization gas was nitrogen, gas flow 650L/min; The distance of spray deposition is 40cm, and spray deposition finishes to make the copper based wear-resistant alloy;
(5) make the bearing alloy body through machining as requested;
B, preparation wear resistant coating
(6) take by weighing each raw material components of wear resistant coating according to following proportioning;
TiO
2 25~55wt.%
NiCrBSiFe 9~27wt.%
Cr
2O
3 20~38wt.%
C-Ni 10 ~ 15wt.%, wherein the Ni weight content is 60 ~ 75%
The powder diameter of above-mentioned each component is 20 ~ 80 μ m;
(7) the said components powder is carried out mechanical mixing, the powder mixing machine time was not less than 30 minutes;
(8) sand blast is carried out on the surface of bearing alloy body;
(9) powder after the above-mentioned mechanical mixing is sprayed as feeding, form the high temperature and high speed plasma jet by plasma gun, select Ar throughput 39L/min, H
2Throughput 9L/min, electric current 600A, spray power is about 42Kw, spray distance 100mm, after powder feeding rate 40g/min powder feeding air-flow promotion mixed powder entered plasma jet, mixed powder was heated to fusion or semi-molten state rapidly, and is accelerated by plasma jet, the spraying particle bundle of matrix surface is flown in formation, and particle beam strikes through matrix surface; Each spraying blanking time is 10min at least, and each coating thickness is not higher than 50 μ m, treats that the matrix surface temperature is lower than 200 ℃ and sprays next time again;
(10) spray the coating that finally obtains about 200 μ m repeatedly, make abrasion-proof bearing bush at last.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104889690A (en) * | 2015-06-01 | 2015-09-09 | 陈鹏 | Bearing bush of internal combustion engine |
| CN104907771A (en) * | 2015-06-01 | 2015-09-16 | 陈鹏 | Motor bearing bush |
| CN107904542A (en) * | 2017-12-08 | 2018-04-13 | 青岛铸辉铜业有限公司 | A kind of copper surface high abrasion coating and preparation method thereof |
| CN108130501A (en) * | 2017-12-14 | 2018-06-08 | 中国人民解放军陆军装甲兵学院 | A kind of preparation method of the copper-based bearing shell copper coating of steel back |
| CN111250708A (en) * | 2020-03-23 | 2020-06-09 | 广西科技大学 | Wear-resistant bushing for excavator and preparation method thereof |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104889690A (en) * | 2015-06-01 | 2015-09-09 | 陈鹏 | Bearing bush of internal combustion engine |
| CN104907771A (en) * | 2015-06-01 | 2015-09-16 | 陈鹏 | Motor bearing bush |
| CN107020485A (en) * | 2015-06-01 | 2017-08-08 | 陈鹏 | A kind of manufacture method of internal combustion engine bearing |
| CN107100936A (en) * | 2015-06-01 | 2017-08-29 | 陈鹏 | A kind of motor bearing and its manufacture method |
| CN107100936B (en) * | 2015-06-01 | 2019-03-12 | 德州亚特电机有限公司 | A kind of motor bearing and its manufacturing method |
| CN107904542A (en) * | 2017-12-08 | 2018-04-13 | 青岛铸辉铜业有限公司 | A kind of copper surface high abrasion coating and preparation method thereof |
| CN108130501A (en) * | 2017-12-14 | 2018-06-08 | 中国人民解放军陆军装甲兵学院 | A kind of preparation method of the copper-based bearing shell copper coating of steel back |
| CN108130501B (en) * | 2017-12-14 | 2020-02-21 | 中国人民解放军陆军装甲兵学院 | Preparation method of steel backing copper-based bearing copper coating |
| CN111250708A (en) * | 2020-03-23 | 2020-06-09 | 广西科技大学 | Wear-resistant bushing for excavator and preparation method thereof |
| CN111250708B (en) * | 2020-03-23 | 2021-12-24 | 广西科技大学 | Wear-resistant bushing for excavator and preparation method thereof |
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