CN104525860A - Engine tappet and production method thereof - Google Patents

Engine tappet and production method thereof Download PDF

Info

Publication number
CN104525860A
CN104525860A CN201410658061.7A CN201410658061A CN104525860A CN 104525860 A CN104525860 A CN 104525860A CN 201410658061 A CN201410658061 A CN 201410658061A CN 104525860 A CN104525860 A CN 104525860A
Authority
CN
China
Prior art keywords
engine prop
tic
prop column
matrix
engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201410658061.7A
Other languages
Chinese (zh)
Other versions
CN104525860B (en
Inventor
许云华
赵娜娜
卢正欣
钟黎声
梁淑华
燕映霖
叶芳霞
王娟
邹军涛
肖鹏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xian University of Technology
Original Assignee
Xian University of Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Xian University of Technology filed Critical Xian University of Technology
Priority to CN201410658061.7A priority Critical patent/CN104525860B/en
Publication of CN104525860A publication Critical patent/CN104525860A/en
Application granted granted Critical
Publication of CN104525860B publication Critical patent/CN104525860B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D18/00—Pressure casting; Vacuum casting
    • B22D18/06—Vacuum casting, i.e. making use of vacuum to fill the mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • 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
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/60—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using solids, e.g. powders, pastes
    • C23C8/62—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using solids, e.g. powders, pastes only one element being applied
    • C23C8/64—Carburising
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01L—CYCLICALLY OPERATING VALVES FOR MACHINES OR ENGINES
    • F01L1/00—Valve-gear or valve arrangements, e.g. lift-valve gear
    • F01L1/12—Transmitting gear between valve drive and valve
    • F01L1/14—Tappets; Push rods
    • F01L1/16—Silencing impact; Reducing wear

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention discloses an engine tappet. The inner cavity surface of the engine tappet is provided with a carbide coating, the body of the engine tappet is made of carbon steel. The invention also provides a production method of the engine tappet. The production method comprises the following steps: fixing an external carbon source to the outer wall of the core of the engine tappet, winding a titanium plate to be close to graphite paper at the outer wall of the core of the austenitic stainless steel engine tappet, casting molten carbon steel matrix steel in a sand mold, carrying out heat treatment on the cast engine tappet, carrying out furnace cooling to room temperature, and forming the carbide coating on the inner cavity surface of the engine tappet. The matrix of the engine tappet body is also the carbon steel matrix, and the carbide coating includes a quasi monocrystalline TiC ceramic layer, and further comprises a micrometer TiC dense ceramic layer and a TiC-matrix fusion layer. The carbide coating and the matrix are metallurgically bonded, and the bonding force is strong, so the problems of weak bonding force between present hard particles and the metal matrix, and easy shedding of the particles are overcome, and the wear resistance of the work surface of the engine tappet is greatly improved.

Description

Engine prop column and preparation method thereof
Technical field
The present invention relates to one and there is wear-resistant coating hybrid engine tappet and preparation method thereof, particularly relate to a kind of hybrid engine tappet with wear resistant carbide coating and preparation method thereof, be specifically related to a kind of wear resistant carbide coating hybrid engine tappet being applied to steel surface and preparation method thereof.
Background technology
Tappet is the chief component being widely used in valve actuating mechanism in the engine heart components such as automobile, engineering machinery, tractor.One end of tappet and cam contact, the other end and valve contacts, its effect is that the thrust of cam is passed to valve.Due to running up and the impact of camshaft and wearing and tearing of engine, require that the bottom surface of tappet (with the contact surface of camshaft) has high rigidity, high-wearing feature.Along with automobile engine is constantly to high speed, high power future development, inevitably increase the spring force of valve actuating mechanism and the sliding speed of contact surface, thus the lubricating condition between cam-tappet is made to become harsher, so extend cam-tappet become one of important topic of development engine service life.This friction pair of cam-tappet damages form and is broadly divided into: scratch, pit and wearing and tearing.Cam-tappet is three to one of main friction pair in internal combustion engine, and condition of work is severe, and problem is a lot.Domestic majority adopts chilled cast iron tappet before, but the life-span is extreme.Certain factor affecting the life-span is many-sided, and as structural design, lubricating condition, machining accuracy and regular maintenance etc., but the selection of material and improvement are very important importances.
The coating of carbide material uses more a kind of material at present stage, and hardness is high, abrasion resistance properties is superior feature that it has, covers with coating way wearability and the life-span that the parts prepared by matrix material can be improved in alloy base surface.Wherein TiC is a kind of common coating material, and it has following advantageous features:
(1) combination property of the excellences such as density is low, intensity is high, elastic modelling quantity is high, wear-resisting, corrosion-resistant, anti-oxidant is possessed;
(2) its particle is generally in spherical shape, and its lattice structure is face-centred cubic structure, has very high heat endurance and hardness;
(3) be convenient to machining, welding, forging, and process thermal deformation is little, and there is the cold and hot working performance of common steel-smelting.
Therefore, TiC coating is widely used as chipless cold/hot metal machining tool, cutting tool, various mould, the anti-corrosion piece surface of antiwear heat resisting etc.
Metal current material surface coating technology has: laser cladding, self-propagating high-temperature sintering technology, PM technique, material vapor deposition technique (comprising: chemical vapour deposition (CVD) (CVD), physical vapour deposition (PVD) (PVD)) etc., but, there is the deficiencies such as production equipment requirement is harsh, production efficiency is low, anchoring strength of coating is low in these methods.
Therefore the coating of TiC phase how is obtained at engine prop column working surface, and select the preparation method that a kind of production equipment is simple, technological process is short, to obtain with good, the difficult drop-off of basal body binding force and the coating of mechanical property, anti-wear performance excellence is problem demanding prompt solution.
Summary of the invention
The defect existed for above-mentioned prior art and deficiency, the object of the present invention is to provide a kind of hybrid engine tappet, its tappet surface of internal cavity has a kind of wear-resistant coating, and cylinder is still plain steel, this wear-resistant coating is TiC dense ceramic layers, its chemical stability and wearability good, there is low-friction coefficient, high rigidity, low-surface-energy and low thermal conductiv-ity; And further, provide a kind of preparation method for obtaining above-mentioned hybrid engine tappet.
Further, the present invention also provides a kind of hybrid engine tappet, its tappet surface of internal cavity has a kind of gradient composite coating, it is preferably coated on tappet surface of internal cavity, to improve wearability and the fracture toughness on its surface, particularly carbon steel tappet surface of internal cavity, and a kind of preparation method for obtaining above-mentioned coating is provided.
Described engine prop column, within it surface, chamber has wear-resistant coating.This coating favourable guarantee engine prop column working surface has very high hardness and good wearability, and tappet intrinsic silicon has good toughness.
For realizing the object of the invention, present invention employs following technical scheme:
A kind of engine prop column, its surface of internal cavity has wear-resistant coating, and this wear-resistant coating is TiC dense ceramic layers; Preferably, TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, between polycrystalline phase and monocrystalline mutually between, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly.
More preferably, along TiC dense ceramic layers longitudinal profile, its thickness is 70-200 μm, is preferably 100-200 μm, is more preferably 120-200 μm; Preferably, wherein the volume fraction of TiC is greater than 80%, is preferably greater than 90%; Preferably, particle diameter is 8-50 μm, is preferably 10-50 μm.
In addition, the present invention also provides a kind of engine prop column, and its surface of internal cavity has wear-resistant coating, and described gradient composite coating is carbide coating, comprises the fused layer of the TiC dense ceramic layers of distribution gradient successively, micron TiC ceramic layer, TiC and matrix.
Preferably, TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, between polycrystalline phase and monocrystalline mutually between, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly.
More preferably, along TiC dense ceramic layers longitudinal profile, its thickness is 70-200 μm, is preferably 100-200 μm, is more preferably 120-200 μm; Preferably, wherein the volume fraction of TiC is greater than 80%, is preferably greater than 90%; Preferably, particle diameter is 8-50 μm, is preferably 10-50 μm.
Preferred further, along micron TiC ceramic layer longitudinal profile, its thickness is 50-150 μm, is preferably 70-150 μm, is more preferably 80-150 μm; Wherein the volume fraction of TiC is greater than 80%, is preferably greater than 90%, and preferably, TiC particle diameter is 5-15 μm, is preferably 6-12 μm, is preferably 8-10 μm.
Further preferred, along the fused layer longitudinal profile of TiC with matrix, its thickness is 50-200 μm, preferably 100-200 μm; Wherein the volume fraction of TiC is 20-80%, and be preferably 50-85%, preferably, TiC particle diameter is 1-10 μm, is preferably 2-8 μm.
Preferably, gradient composite coating gross thickness is 170-550 μm; Be preferably 300-550 μm.
Described metallic matrix is preferably carbon steel, and plain steel is organized as one or more in pearlite, martensite, ferrite, bainite, austenite and sorbite.
More preferably, engine prop column matrix is according to heat treatment mode one or more that can be divided in pearlite, martensite, ferrite, bainite, austenite and sorbite different; Preferably, this gradient composite coating is applied in steel surface.
The invention provides the preparation method that a kind of surface of internal cavity has the engine prop column of wear-resistant coating, comprise the steps:
1) first prepare a titanium plate, preferably, wherein the purity of titanium should control at 99.7-99.99%, and preferably, the THICKNESS CONTROL of described titanium plate is at 0.2-3mm; Preferably, described titanium plate is first by addition surface treatment;
2) according to engine prop column size, engine prop column evaporative pattern is made with polystyrene foam plastics.
3) according to engine prop column size, sand mold is made; Preferably, CO is used 2waterglass hardened sand, precoated sand, self-hardening resin sand or tide mould sand make sand mold; According to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper is fixed accordingly in sand mold intrinsic motivation tappet core outer wall surface, then by titanium coiled sheet around and be close on the graphite paper of austenitic stainless steel engine prop column core, itself and graphite paper are combined closely;
4) carbon steel base material is smelted for molten steel; Preferably, temperature controls at 1610 DEG C-1630 DEG C;
5) evaporative pattern process for suction casting is adopted, above-mentioned molten steel is poured in the sand mold of the engine prop column core being placed with graphite paper and titanium plate, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix is carbon steel, and engine prop column inner chamber working surface is the complex with titanium plate, preferably, pouring temperature controls at 1610 DEG C-1630 DEG C; More preferably, the duration of pouring, 40-50 was advisable second; Further preferably, after one minute, at hot topping; Preferably, room temperature cooling;
6) the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, finally cools to room temperature with the furnace, thus forms wear-resistant coating at tappet inner surface, and matrix of holding out is still plain steel.
Wherein, wear-resistant coating is TiC dense ceramic layers.
Preferably, by rate-determining steps 6) in temperature retention time, holding temperature obtain this TiC dense ceramic layers; Preferably, TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, between polycrystalline phase and monocrystalline mutually between, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly.
The present invention also provides a kind of surface of internal cavity to have the preparation method of the engine prop column of gradient composite coating, comprises the steps:
1) first prepare a titanium plate, preferably, wherein the purity of titanium should control at 99.7-99.99%, and the THICKNESS CONTROL of described titanium plate is at 0.2-3mm; Preferably, described titanium plate is first by addition surface treatment;
2) according to engine prop column size, engine prop column evaporative pattern is made with polystyrene foam plastics.
3) according to engine prop column size, sand mold is made; Preferably, CO is used 2waterglass hardened sand, precoated sand, self-hardening resin sand or tide mould sand make sand mold; According to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper is fixed accordingly in sand mold intrinsic motivation tappet core outer wall surface, then by titanium coiled sheet around and be close on the graphite paper of austenitic stainless steel engine prop column core, itself and graphite paper are combined closely;
4) carbon steel base material is smelted for molten steel; Preferably, temperature controls at 1610 DEG C-1630 DEG C;
5) evaporative pattern process for suction casting is adopted, above-mentioned molten steel is poured in the sand mold of the engine prop column core being placed with graphite paper and titanium plate, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix is carbon steel, and engine prop column inner chamber working surface is the complex with titanium plate, preferably, pouring temperature controls at 1610 DEG C-1630 DEG C; More preferably, the duration of pouring, 40-50 was advisable second; Further preferably, after one minute, at hot topping; Preferably, room temperature cooling;
6) the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, finally cools to room temperature with the furnace, thus forms wear-resistant coating at tappet inner surface, and matrix of holding out is still plain steel;
7) surface of gained there is gradient composite coating engine prop column by further heat treatment to obtain more suitably matrix.
Preferably, titanium plate thickness is 0.2-3mm; If be less than 0.2mm, then titanium plate 2 just complete reaction in cast recombination process, can not obtain accurate monocrystalline TiC pottery, directly generation Dispersed precipitate TiC, presents the fusion completely of TiC and matrix.Then cause diffusion length to increase more than 3mm, reaction power is not enough.
Preferably, by strict rate-determining steps 6) in holding temperature and the relation of time, obtain described accurate monocrystalline phase TiC dense ceramic layers.This ceramic layer presents comparatively obvious accurate single crystal organization, and show as crystal boundary under light microscope and reduce, affect the dislocation also corresponding minimizing of fracture toughness, the sub boundary in generation increases, and effectively improves the anti-crack ability of this ceramic layer.
Preferably, by rate-determining steps 6) in temperature retention time, holding temperature obtain this gradient composite coating and carbide coating, described carbide coating comprises the fused layer of the accurate monocrystalline phase TiC dense ceramic layers of distribution gradient successively, micron TiC ceramic layer, TiC and matrix.
More preferably, above-mentioned steps 6) in holding temperature, temperature retention time and the gross thickness of gradient composite coating that finally can obtain meet following formula,
L＝kTlogt1/2+b 0
Wherein:
The gross thickness (μm) of L---gradient composite coating,
K---be constant, value is 0-1, k ≠ 0,
T---holding temperature (K),
T---temperature retention time (s),
B 0---reaction original depth (μm), the thickness of the composite bed formed after namely molten steel is poured into a mould and between titanium plate.
To sum up, described gradient composite coating, comprise TiC dense ceramic layers, hardness is high.Described TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, the arrangement of atom unlike monocrystalline there is identical lattice like that, but still there is strict order, present geometry arrangement; Uniform orientation is high, crystal boundary obviously reduces, and atomic arrangement is more orderly.Accurate monocrystalline is between polycrystalline phase with monocrystalline phase, and compared to polycrystalline phase, the crystal boundary of accurate monocrystalline phase obviously reduces, and dislocation density is low, has more sub boundary, and therefore hardness has obvious lifting; And than monocrystalline phase, it requires lower to preparation method, and organize more stable.
Preferably, in step 1) in, surface-treated step is as follows:
First step pickling, selects the hydrogen peroxide of the hydrochloric acid of 300mL/L or the phosphoric acid of 60mL/L or 120mL/L, rear running water;
Second step pickling, selects the hydrogen peroxide of the hydrofluoric acid of 300mL/L or the sulfuric acid of 200mL/L or 240mL/L, rear running water;
3rd step surface finish, selects 800 orders or thinner Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.
More preferably, step 3) in graphite paper be more than three grades, purity 99%, thickness is 0.1-0.35mm;
Preferably, step 6) in, be warming up to 1000-1130 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 4-12h, preferred 6-10h.
Preferably, selected plain steel is mild steel, medium carbon steel and high-carbon steel.
Preferably, protection gas is argon gas or nitrogen, and gas flow is 4-8mL/min.
Wherein, strictly should control holding temperature in above-mentioned scope, temperature is higher than 1130 DEG C, and the liquid phase in course of reaction is too much, and makes accurate monocrystalline TiC, directly generates Dispersed precipitate TiC particle, and can not obtain accurate monocrystalline TiC dense ceramic layers; But temperature is lower than 1000 DEG C, then the solubility of Ti is too low, and reaction cannot be carried out by forward.Same, temperature retention time also should keep a reasonably interval, time is more than 12h, accurate monocrystalline TiC dense ceramic layers disappears, Reaction-diffusion terms generates the fusion of Dispersed precipitate TiC particle and matrix, and lower than 4h, then reacts the TiC of acquisition very little, coating layer thickness is difficult to ensure, best should remain on 6-10h.
More preferably, the engine prop column complex with carbide coating is by further heat treatment to obtain more suitably matrix, and heat treatment step is: heat-treat at about 550-800 DEG C, and matrix is pearlitic structrure; Or heat-treat at 220-450 DEG C, matrix is bainite structure; Or heat-treat below 220 DEG C, matrix is martensitic structure.
Described engine prop column take carbon steel as matrix, and selected plain steel is mild steel, medium carbon steel and high-carbon steel, is preferably: Q275A, Q255AF, 45 steel, T12A, T8, ZG270-450 etc., sees standard GB/T 221-79.Matrix according to heat treatment mode be not all in pearlite, martensite, ferrite, bainite, austenite and sorbite one or more.
After the present invention obtains the engine prop column complex of plain steel and titanium by sand casting, introduce external carbon source, directly carbide coating can be formed at the surface of internal cavity of engine prop column in the mode adding thermal diffusion, carbide coating and holding out between matrix as metallurgical binding, adhesion is very strong, and overcome non-metallurgical binding between existing hard particles and metallic matrix, adhesion is very weak, particle holds caducous problem, has increased substantially the mechanical property of coating.And the method is simple to operate, without the need to complex device, the engine prop column of acquisition is functional.Different heat treatment modes, makes engine prop column have different mechanical properties, meets the requirement of actual production.Due to the formation of the accurate single-crystal ceramic layer of surface compact, this ceramic layer presents comparatively obvious accurate single crystal organization, shows as crystal boundary and reduces, affect the dislocation also corresponding minimizing of fracture toughness under light microscope, the sub boundary in generation increases, and effectively improves the anti-crack ability of this ceramic layer.Therefore the surface of internal cavity of engine prop column has higher hardness 3000-3230HV 0.05, relative wear resistance is 10-22 times of matrix.Described relative wear resistance is defined as: take matrix material as standard specimen, in identical abrasive grain, same load, after disk rotates same number of turns with same rotational speed, tested coating produces the relative wear resistance that ratio that wear extent and standard specimen produce wear extent is called coating, therefore be several times of matrix also referred to as the relative wear resistance of coating, the examination criteria of following identical parameters is identical with it.
This to be as the criterion single crystal organization due to TiC dense ceramic layers wherein, chemical stability and wearability good, there is low-friction coefficient, high rigidity, low-surface-energy and low thermal conductiv-ity.And the hardness of micron TiC ceramic layer on the other side can only reach 2000-2800HV 0.05, its relative wear resistance is 6-10 times of matrix.
Accompanying drawing explanation
Engine prop column preparation technology figure in Fig. 1 the present invention;
In Fig. 2 the present invention, heat treatment rear engine tappet and each several part organize schematic diagram;
Accurate monocrystalline phase TiC ceramic layer micro-organization chart in Fig. 3 the present invention;
TiC ceramic layer polycrystalline phase micro-organization chart in Fig. 4 the present invention.
In figure, 1. graphite paper, 2. titanium plate, 3. block accurate monocrystalline TiC dense ceramic layers, 4. micron TiC dense ceramic layers, the fused layer of 5.TiC and matrix, 6. engine prop column body, 7. sand mold, 8. engine prop column core, 9. engine prop column evaporative pattern.
Detailed description of the invention
Embodiment 1: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.7%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the hydrochloric acid of 300mL/L, rear running water;
Second step pickling, selects the hydrofluoric acid of 300mL/L, rear running water;
3rd step surface finish, selects 800 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 1mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, CO is used 2waterglass hardened sand makes sand mold 7, every case engine prop column, two casees somatotypes.According to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, and fix graphite paper 1 in sand mold 7 intrinsic motivation tappet core 8 outer wall surface accordingly, described graphite paper 1 is more than three grades, purity 99%, thickness is 0.1mm.Then be that the titanium plate 2 of 1mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness, as shown in Figure 1.
4, smelt Q275A base material for molten steel, temperature controls at 1630 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1630 DEG C, and the duration of pouring is be advisable for 40 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is Q275A plain steel, and engine prop column surface of internal cavity is the complex of carbon steel and titanium plate 2;
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1000 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 6h; thus form carbide coating at engine prop column inner surface, and tappet matrix 6 is still Q275A matrix.Described protection gas is argon gas, and gas flow is 5mL/min.
7, the engine prop column with the Q275A matrix of carbide coating of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat below 220 DEG C, and matrix is martensitic structure.
Described carbide coating, comprises TiC dense ceramic layers 3, and be as the criterion monocrystalline phase, presents neat dendritic crystalline tissue along coating longitudinal profile, and its particle diameter is 15 μm; Along coating longitudinal profile, its thickness is 110 μm, and wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 90 μm, and the volume fraction of TiC is 90%, and its particle diameter is 7 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 90 μm, and wherein the volume fraction of TiC is 70%, and its particle diameter is 3 μm.
Now, as shown in Figure 2, described coating can be composite coating, and it comprises TiC dense ceramic layers 3, the fused layer 5 of micron TiC ceramic layer 4 and TiC and matrix is formed, and distribution gradient successively, its gross thickness is 290 μm.Described engine prop column matrix 6 is martensite.The microhardness of described engine prop column carbide surface coating reaches as high as 3000HV 0.05, relative wear resistance is 22 times of matrix.
Embodiment 2: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.8%, and described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, the phosphoric acid of 60mL/L, rear running water;
Second step pickling, the sulfuric acid of 200mL/L, rear running water;
3rd step surface finish, selects 1000 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 1.5mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold 7 is made with precoated sand, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.2mm.Then be that the titanium plate 2 of 1.5mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt Q255AF base material for molten steel, temperature controls at 1630 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel and be placed with in the above-mentioned sand mold 7 adhering to the engine prop column core 8 of graphite paper 1 and titanium plate 2, pouring temperature controls at 1630 DEG C, and the duration of pouring is be advisable for 45 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is Q255AF plain steel, and engine prop column surface of internal cavity is the complex of carbon steel and titanium plate 2;
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1050 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 6h; thus form carbide coating at engine prop column inner surface, and tappet matrix 6 is still Q255AF matrix.Described protection gas is argon gas, and gas flow is 6mL/min.
7, the engine prop column with the Q255AF matrix of carbide coating of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat at about 700 DEG C, and matrix is pearlitic structrure.
Described carbide coating, as shown in Figure 3, comprises TiC dense ceramic layers 3, and be as the criterion monocrystalline phase, presents neat dendritic crystalline tissue along coating longitudinal profile, and its particle diameter is 30 μm; Along coating longitudinal profile, its thickness is 150 μm; Wherein the volume fraction of TiC is 90%.
Further, as shown in Figure 4, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 100 μm, and the volume fraction of TiC is 90%, and its particle diameter is 10 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 100 μm, and wherein the volume fraction of TiC is 65%, and its particle diameter is 4 μm.
To sum up, described coating can be composite coating, and it comprises the fused layer 5 ecto-entad distribution gradient successively of accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix, and its gross thickness is 350 μm.Described engine prop column matrix 6 is pearlite.The hardness of described engine prop column inner surface carbide coating is 3080HV 0.05, wearability is 16 times relative to Q255AF steel matrix.
Embodiment 3: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.8%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, the hydrogen peroxide of 120mL/L, rear running water;
Second step pickling, the hydrogen peroxide of 240mL/L, rear running water;
3rd step surface finish, selects 1000 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 2.5mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold 7 is made with self-hardening resin sand, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.35mm.Then be that the titanium plate 2 of 2.5mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt Q255AF steel substrate for molten steel, temperature controls at 1630 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1630 DEG C, and the duration of pouring is be advisable for 50 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is Q255AF steel, and working surface is the complex with titanium plate 2.
6, evaporative pattern process for suction casting is adopted; the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1100 DEG C; programming rate controls at 7 DEG C/min; temperature retention time is 10h; thus form carbide coating at engine prop column inner surface, and tappet matrix 6 is still Q255AF steel matrix.Described protection gas is argon gas, and gas flow is 6mL/min.
7, the engine prop column of the novel microcosmic composite construction of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat at 700 DEG C, and matrix is pearlitic structrure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, its particle diameter is 40 μm; Along coating longitudinal profile, its thickness is 180 μm; Wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 130 μm, and the volume fraction of TiC is 90%, and its particle diameter is 13 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 160 μm, and wherein the volume fraction of TiC is 50%, and its particle diameter is 8 μm.
To sum up, described coating can be composite coating, can by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix, and its gross thickness is 470 μm, and described Q255AF steel matrix is pearlite.The hardness of engine prop column carbide surface coating is 3120HV 0.05, wearability is 22 times relative to Q255AF steel matrix.
Embodiment 4: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.99%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the phosphoric acid of 60mL/L, rear running water;
Second step pickling, the sulfuric acid of 200mL/L, rear running water;
3rd step surface finish, selects 1200 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 3mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold 7 is made with tide mould sand, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.15mm.Then be that the titanium plate 2 of 3mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt 50 steel substrates for molten steel, temperature controls at 1610 DEG C, and selected plain steel is medium carbon steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1610 DEG C, and the duration of pouring is be advisable for 50 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is 50 steel, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1130 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 12h; thus form carbide coating at engine prop column inner surface, and tappet matrix 6 is still 50 steel matrix.Described protection gas is argon gas, and gas flow is 6mL/min.
7, the engine prop column with 50 steel matrix of carbide coating of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat at about 350 DEG C, and matrix is bainite structure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, present neat dendritic crystalline tissue along coating longitudinal profile, its particle diameter is 45 μm; Along coating longitudinal profile, its thickness is 200 μm; Wherein the volume fraction of TiC is 80%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 150 μm, and the volume fraction of TiC is 80%, and its particle diameter is 15 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 200 μm, and wherein the volume fraction of TiC is 20%, and its particle diameter is 10 μm.
To sum up, described coating can be composite coating, is that its gross thickness is 550 μm by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix.Described 50 steel matrix are bainite.The hardness of described engine prop column carbide surface coating is 3230HV 0.05, wearability is 14 times relative to 50 steel matrix
Embodiment 5: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.7%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the hydrochloric acid of 300mL/L, rear running water;
Second step pickling, the hydrogen peroxide of 240mL/L, rear running water;
3rd step surface finish, selects 800 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 2.5mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, CO is used 2waterglass hardened sand makes sand mold 7, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, and fix graphite paper 1 in sand mold 7 intrinsic motivation tappet core 8 outer wall surface accordingly, described graphite paper 1 is more than three grades, purity 99%, thickness is 0.25mm.Then be that the titanium plate 2 of 2.5mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt T12 steel substrate for molten steel, temperature controls at 1610 DEG C, and selected plain steel is high-carbon steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1610 DEG C, and the duration of pouring is be advisable for 40 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is T12 steel, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1000 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 12h; thus form carbide coating at engine prop column inner surface, and tappet matrix 6 is still T12 matrix.Described protection gas is argon gas, and gas flow is 7mL/min.
7, the engine prop column of the novel microcosmic composite construction of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat at 400 DEG C, and matrix is bainite structure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, present neat dendritic crystalline tissue along coating longitudinal profile, its particle diameter is 30 μm; Along coating longitudinal profile, its thickness is 120 μm; Wherein the volume fraction of TiC is 85%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 110 μm, and the volume fraction of TiC is 85%, and its particle diameter is 9 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 120 μm, and wherein the volume fraction of TiC is 60%, and its particle diameter is 5 μm.
To sum up, described coating can be composite coating, can by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix, and its gross thickness is 350 μm.Described T12 steel matrix is bainite.The hardness of described engine prop column carbide surface coating is 3010HV 0.05, wearability is 10 times relative to T12 steel matrix.
Embodiment 6: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.99%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the hydrogen peroxide of 120mL/L, rear running water;
Second step pickling, the hydrogen peroxide of 240mL/L, rear running water;
3rd step surface finish, selects 1200 object Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 2mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold 7 is made with precoated sand, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.25mm.Then be that the titanium plate 2 of 2mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt T8 steel substrate for molten steel, temperature controls at 1610 DEG C, and selected plain steel is high-carbon steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1610 DEG C, and the duration of pouring is be advisable for 50 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is T8 steel, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, be warming up to 1050 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 12h, finally cool to room temperature with the furnace, obtain the engine prop column that surface has microcosmic composite construction; Described protection gas is argon gas, and gas flow is 8mL/min.
7, the engine prop column of the novel microcosmic composite construction of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat below 220 DEG C, and matrix is martensitic structure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, its particle diameter is 35 μm; Along coating longitudinal profile, its thickness is 170 μm; Wherein the volume fraction of TiC is 85%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 120 μm, and the volume fraction of TiC is 85%, and its particle diameter is 12 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 130 μm, and wherein the volume fraction of TiC is 55%, and its particle diameter is 6 μm.
To sum up, described coating can be composite coating, is that its gross thickness is 420 μm by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix.Described T8 steel matrix is martensite.The microhardness of described engine prop column carbide surface coating is 3100HV 0.05, wearability is 11 times relative to T8 steel matrix.
Embodiment 7: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.9%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the phosphoric acid of 60mL/L, rear running water;
Second step pickling, selects the sulfuric acid of 200mL/L, rear running water,
3rd step surface finish, selects 1000 order Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 1mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold 7 is made with self-hardening resin sand, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.15mm.Then be that the titanium plate 2 of 1mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt ZG270-500 steel substrate for molten steel, temperature controls at 1630 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1630 DEG C, and the duration of pouring is be advisable for 45 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is ZG270-500 steel matrix, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, be warming up to 1100 DEG C, programming rate controls at 7 DEG C/min, temperature retention time is 6h, finally cool to room temperature with the furnace, obtain the engine prop column that surface has microcosmic composite construction, described protection gas is argon gas, and gas flow is 8mL/min;
7, gained ZG270-500 Steel material, by further heat treatment to obtain more suitably matrix, heat-treats below 220 DEG C, and matrix is martensitic structure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, present neat dendritic crystalline tissue along coating longitudinal profile, its particle diameter is 40 μm; Along coating longitudinal profile, its thickness is 160 μm; Wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 110 μm, and the volume fraction of TiC is 90%, and its particle diameter is 11 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 120 μm, and wherein the volume fraction of TiC is 60%, and its particle diameter is 7 μm.
To sum up, described coating can be composite coating, is that its gross thickness is 390 μm by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix.Described ZG270-500 steel matrix is martensite.The hardness of described engine prop column carbide surface coating is 3110HV0.05, and wearability is 19 times relative to ZG270-500 steel matrix.
Embodiment 8: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.9%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the phosphoric acid of 60mL/L, rear running water;
Second step pickling, selects the sulfuric acid of 200mL/L, rear running water;
3rd step surface finish, selects 1000 order Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 1mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, tide mould sand makes sand mold 7, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper 1 is fixed accordingly in sand mold 7 intrinsic motivation tappet core 8 outer wall surface, described graphite paper 1 is more than three grades, purity 99%, and thickness is 0.3mm.Then be that the titanium plate 2 of 1mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt 45 steel substrates for molten steel, temperature controls at 1620 DEG C, and selected plain steel is medium carbon steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1620 DEG C, and the duration of pouring is be advisable for 45 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is 45 steel matrix, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, be warming up to 1130 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 6h, finally cool to room temperature with the furnace, obtain the engine prop column that surface has microcosmic composite construction; Described protection gas is argon gas, and gas flow is 6mL/min.
7, gained 45 Steel material, by further heat treatment to obtain more suitably matrix, heat-treats at about 600 DEG C, and matrix is pearlitic structrure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, its particle diameter is 45 μm; Along coating longitudinal profile, its thickness is 170 μm; Wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 140 μm, and the volume fraction of TiC is 90%, and its particle diameter is 14 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 180 μm, and wherein the volume fraction of TiC is 40%, and its particle diameter is 9 μm.
To sum up, described coating can be composite coating, can by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix, and its gross thickness is 490 μm.Described 45 steel matrix are pearlite.The microhardness of described engine prop column carbide surface coating is 3130HV 0.05, wearability is 13 times relative to 45 steel matrix.
Embodiment 9: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, wherein the purity of titanium should control 99.9%.Described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the phosphoric acid of 60mL/L, rear running water;
Second step pickling, selects the sulfuric acid of 200mL/L, rear running water;
3rd step surface finish, selects 1200 order Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 0.2mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, CO is used 2waterglass hardened sand makes sand mold 7, every case engine prop column, two casees somatotypes, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, and fix graphite paper 1 in sand mold 7 intrinsic motivation tappet core 8 outer wall surface accordingly, described graphite paper 1 is more than three grades, purity 99%, thickness is 0.2mm.Then be that the titanium plate 2 of 0.2mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, smelt 50 steel substrates for molten steel, temperature controls at 1620 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, poured into by above-mentioned molten steel in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, pouring temperature controls at 1620 DEG C, and the duration of pouring is be advisable for 40 seconds, after one minute, at hot topping, after room temperature cooling, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is 50 steel matrix, and working surface is the complex with titanium plate 2.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1000 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 4h; finally cool to room temperature with the furnace, obtain the double carbide coating on described plain steel surface.Described protection gas is nitrogen, and gas flow is 6mL/min.
7, gained carbon steel material, heat-treated at about 650 DEG C to obtain more suitably matrix by further heat treatment, matrix is pearlitic structrure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, present neat dendritic crystalline tissue along coating longitudinal profile, its particle diameter is 10 μm; Along coating longitudinal profile, its thickness is 70 μm; Wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 50 μm, and the volume fraction of TiC is 90%, and its particle diameter is 5 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 50 μm, and wherein the volume fraction of TiC is 80%, and its particle diameter is 1 μm.
To sum up, described coating can be composite coating, can by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix, and its gross thickness is 170 μm.Described 50 steel matrix are pearlite.The hardness of described engine prop column carbide surface coating is 3000HV 0.05, wearability is 11 times relative to 50 steel matrix.
Embodiment 10: the preparation method of engine prop column, comprises the steps:
1, first prepare a titanium plate 2, preferably, wherein the purity of titanium should control 99.8%; More preferably, described titanium plate 2 should first by surface treatment in addition, and step is as follows:
First step pickling, selects the phosphoric acid of 60mL/L, rear running water;
Second step pickling, selects the sulfuric acid of 200mL/L, rear running water;
3rd step surface finish, selects 1000 order Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.The THICKNESS CONTROL of described titanium plate 2 is at 3mm.
2, according to engine prop column size, engine prop column evaporative pattern 9 is made with polystyrene foam plastics.
3, according to engine prop column size, sand mold is made; Preferably, sand mold 7 is made with precoated sand, every case engine prop column, two casees somatotypes.According to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, and fix graphite paper 1 in sand mold 7 intrinsic motivation tappet core 8 outer wall surface accordingly, described graphite paper 1 is more than three grades, purity 99%, thickness is 0.1mm.Then be that the titanium plate 2 of 3mm reels and is close on the graphite paper of austenitic stainless steel engine prop column core 8 by thickness.
4, adopt evaporative pattern process for suction casting, smelt Q255 steel substrate for molten steel, temperature controls at 1630 DEG C, and selected plain steel is mild steel;
5, evaporative pattern process for suction casting is adopted, above-mentioned molten steel is poured in the sand mold 7 of the engine prop column core 8 being placed with above-mentioned attachment graphite paper 1 and titanium plate 2, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix 6 is carbon steel, and working surface is the complex with titanium plate 2; Preferably, pouring temperature controls at 1630 DEG C; More preferably, the duration of pouring is be advisable for 50 seconds, and further preferably, after one minute, at hot topping, room temperature cools.
6, the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere; be warming up to 1050 DEG C, programming rate controls at 7 DEG C/min, and temperature retention time is 4h; finally cool to room temperature with the furnace, obtain the double carbide coating on described plain steel surface.Described protection gas is nitrogen, and gas flow is 6mL/min.
7, the engine prop column with the Q255 steel matrix of carbide coating of gained, by further heat treatment to obtain more suitably matrix, heat treatment step is: heat-treat at 300 DEG C, and matrix is bainite structure.
Described carbide coating, comprise TiC dense ceramic layers 3 and to be as the criterion monocrystalline phase, present neat dendritic crystalline tissue along coating longitudinal profile, its particle diameter is 25 μm; Along coating longitudinal profile, its thickness is 90 μm; Wherein the volume fraction of TiC is 90%.
Further, comprise the micron TiC ceramic layer 4 be positioned under above-mentioned accurate monocrystalline TiC dense ceramic layers 3, along coating longitudinal profile, its thickness is 70 μm, and the volume fraction of TiC is 90%, and its particle diameter is 8 μm.
Further also comprise the fused layer 5 being positioned at TiC under above-mentioned accurate monocrystalline TiC dense ceramic layers 3 and micron TiC ceramic layer 4 and matrix, along coating longitudinal profile, its thickness is 70 μm, and wherein the volume fraction of TiC is 70%, and its particle diameter is 2 μm.
To sum up, described coating can be composite coating, is that its gross thickness is 230 μm by the fused layer 5 ecto-entad distribution gradient successively of described accurate monocrystalline TiC dense ceramic layers 3, micron TiC ceramic layer 4 and TiC and matrix.Described plain steel is pearlite.The microhardness of described engine prop column carbide surface coating is 3020HV0.05, and wearability is 20 times relative to Q255 steel matrix.
Comparative example 1, its preparation method is as follows: with laser cladding directly by the working face of titanium carbide granule cladding at engine prop column, obtain coating, thickness is 30 μm, and volume fraction is 80%, and the hardness of gained coating is 1650HV 0.05, toughness is 4MPa.m 1/2, wearability relative to steel matrix be 2-3 doubly, and surface and matrix in conjunction with poor, cause coming off of surface accumulation layer.
In comparative example, Laser Surface Modification Technology production cost is high, and production efficiency is low, and technological parameter is wayward, and uses bonding agent will cause pore and slag inclusion in use procedure; And there is not accurate monocrystalline TiC dense ceramic layers and micron TiC ceramic layer in composite bed, composite bed thickness and TiC content less, TiC particle diameter is uneven; Simultaneously, recombination process is only that the gap externally added between hard titanium carbide granule is carried out casting and blended and carry out melting, sintering to additional particle, non-metallurgical binding between hard titanium carbide granule and metallic matrix, adhesion is very weak, particle easily comes off or there is oxidation, Inclusion Problem, therefore, its mechanical property is poor.

Claims (21)

1. an engine prop column, has wear-resistant coating at its working face, it is characterized in that: described wear-resistant coating is TiC dense ceramic layers.
2. engine prop column as claimed in claim 1, is characterized in that: TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, between polycrystalline phase with monocrystalline phase, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly.
3. engine prop column as claimed in claim 1 or 2, it is characterized in that: along TiC dense ceramic layers longitudinal profile, its thickness is 70-200 μm, is preferably 100-200 μm, is more preferably 120-200 μm; Preferably, the volume fraction of TiC is greater than 80%, is preferably greater than 90%; TiC dense ceramic layers particle diameter is 8-50 μm, is preferably 10-50 μm.
4. an engine prop column, at its tappet surface of internal cavity, there is gradient composite coating, it is characterized in that: described gradient composite coating is carbide coating, comprise the fused layer of the TiC dense ceramic layers of distribution gradient successively, micron TiC ceramic layer, TiC and matrix.
5. engine prop column as claimed in claim 4, is characterized in that: TiC dense ceramic layers is as the criterion monocrystalline phase, and described accurate monocrystalline refers to mutually, between polycrystalline phase with monocrystalline phase, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly.
6. the engine prop column as described in claim 4 or 5, is characterized in that: along TiC dense ceramic layers longitudinal profile, and its thickness is 70-200 μm, is preferably 100-200 μm, is more preferably 120-200 μm; Preferably, the volume fraction of TiC is greater than 80%, is preferably greater than 90%; TiC dense ceramic layers particle diameter is 8-50 μm, is preferably 10-50 μm.
7. the engine prop column as described in one of claim 4-6, is characterized in that: along micron TiC ceramic layer longitudinal profile, its thickness is 50-150 μm, is preferably 70-150 μm, is more preferably 80-150 μm; Preferably, the volume fraction of TiC is greater than 80%, is preferably greater than 90%; Preferably, the particle diameter of TiC is 5-15 μm, is preferably 6-12 μm, is more preferably 8-10 μm.
8. the engine prop column as described in one of claim 4-7, is characterized in that: along the longitudinal profile of the fused layer of TiC and matrix, its thickness is 50 μm-200 μm, preferred 100-200 μm; Preferably, wherein the volume fraction of TiC is 20%-80%, is preferably 50%-85%; Preferred in this layer, the particle diameter of TiC is 1-10 μm, is preferably 2-8 μm.
9. the engine prop column as described in one of claim 4-8, is characterized in that: gradient composite coating gross thickness is 170-550 μm, preferably at 300-550 μm.
10. the engine prop column as described in one of claim 4-9, is characterized in that: organize according to heat treatment be not all in pearlite, martensite, ferrite, bainite, austenite and sorbite one or more; Preferably, this gradient composite coating is applied in steel surface.
11. 1 kinds of engine prop column preparation methods as described in one of claim 1-3, it is characterized in that, surface of internal cavity has wear-resistant coating, comprises the steps:
1) first prepare a titanium plate, preferably, wherein the purity of titanium should control at 99.7-99.99%, and the THICKNESS CONTROL of described titanium plate is at 0.2-3mm; Preferably, described titanium plate is first by addition surface treatment;
2) according to engine prop column size, engine prop column evaporative pattern is made with polystyrene foam plastics;
3) sand mold is made according to engine prop column size; According to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, fix graphite paper in sand mold intrinsic motivation tappet core outer wall surface accordingly, then by titanium coiled sheet around and the graphite paper being close to austenitic stainless steel engine prop column core makes itself and graphite paper combine closely; Preferably, CO is used 2waterglass hardened sand, precoated sand, self-hardening resin sand or tide mould sand make sand mold;
4) smelt carbon steel base material for molten steel, preferably, temperature controls at 1610 DEG C-1630 DEG C;
5) poured into by above-mentioned molten steel in the sand mold of the engine prop column core being placed with graphite paper and titanium plate, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix is carbon steel, and working surface is the complex with titanium plate; Preferably, adopt evaporative pattern process for suction casting, above-mentioned molten steel is poured in the sand mold of the engine prop column core being placed with graphite paper and titanium plate; Preferably, pouring temperature controls at 1610 DEG C-1630 DEG C, and the duration of pouring is that 40-50 is advisable second, more preferably, after one minute, at hot topping; Further preferably, room temperature cooling;
6) the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, finally cools to room temperature with the furnace, thus forms wear-resistant coating at tappet inner surface, and matrix of holding out is still plain steel;
Wherein, wear-resistant coating is TiC dense ceramic layers.
The preparation method of 12. engine prop columns as claimed in claim 11, it is characterized in that: TiC dense ceramic layers is as the criterion monocrystalline phase, described accurate monocrystalline refers to mutually, between polycrystalline phase with monocrystalline phase, compared to polycrystalline phase, uniform orientation is high, crystal boundary obviously reduces, and the microscopic structure that atomic arrangement is more orderly; Preferably, by rate-determining steps 6) in temperature retention time, holding temperature obtain this TiC dense ceramic layers.
The preparation method of 13. 1 kinds of engine prop columns as described in one of claim 4-10, is characterized in that, its surface of internal cavity has gradient composite coating, comprises the steps:
1) first prepare a titanium plate, preferably, wherein the purity of titanium should control at 99.7-99.99%, and more preferably, the THICKNESS CONTROL of described titanium plate is at 0.2-3mm; Preferably, described titanium plate is first by addition surface treatment;
2) according to engine prop column size, engine prop column evaporative pattern is made with polystyrene foam plastics;
3) sand mold is made according to engine prop column size, according to the work force-bearing situation of engine prop column, the position of its key wear is the surface of internal cavity of engine prop column, graphite paper is fixed accordingly in sand mold intrinsic motivation tappet core outer wall surface, then by titanium coiled sheet around and be close on the graphite paper of engine prop column core, itself and graphite paper are combined closely; Preferably, CO is used 2waterglass hardened sand, precoated sand, self-hardening resin sand or tide mould sand make sand mold;
4) smelt carbon steel base material for molten steel, preferably, temperature controls at 1610 DEG C-1630 DEG C;
5) poured into by above-mentioned molten steel in the sand mold of the engine prop column core being placed with graphite paper and titanium plate, after molten steel cooled and solidified, take out foundry goods, sand removal process, obtaining engine prop column matrix is carbon steel, and working surface is the complex with titanium plate; Preferably, adopt evaporative pattern process for suction casting, above-mentioned molten steel is poured in the sand mold of the engine prop column core being placed with graphite paper and titanium plate, preferably, pouring temperature controls at 1610 DEG C-1630 DEG C, and the duration of pouring is 40-50 second, more preferably, after one minute, at hot topping; Further preferably, room temperature cooling;
6) the engine prop column complex obtained having cast puts into the holding furnace inside holding with protective atmosphere, finally cools to room temperature with the furnace, thus forms wear-resistant coating at tappet inner surface, and matrix of holding out is still plain steel;
7) engine prop column with gradient composite coating of gained by further heat treatment to obtain more suitably matrix.
The preparation method of 14. engine prop columns as claimed in claim 13, it is characterized in that: by rate-determining steps 6) in temperature retention time, holding temperature obtain this gradient composite coating and carbide coating, described carbide coating comprises the fused layer of the accurate monocrystalline phase TiC dense ceramic layers of distribution gradient successively, micron TiC ceramic layer, TiC and matrix.
The preparation method of 15. engine prop columns as claimed in claim 14, is characterized in that: holding temperature, temperature retention time and the gross thickness of gradient composite coating that finally can obtain meet following formula,
L＝kTlogt 1/2+b 0
Wherein:
The gross thickness (μm) of L---gradient composite coating,
K---be constant, value is 0-1, k ≠ 0,
T---holding temperature (K),
T---temperature retention time (s),
B 0---original depth (μm), the thickness of the composite bed formed after namely molten steel is poured into a mould and between titanium plate 2.
The preparation method of 16. engine prop columns as described in one of claim 13-15, is characterized in that: described step 1) in, surface-treated step is as follows:
First step pickling, selects the hydrogen peroxide of the hydrochloric acid of 300mL/L or the phosphoric acid of 60mL/L or 120mL/L, rear running water;
Second step pickling, selects the hydrogen peroxide of the hydrofluoric acid of 300mL/L or the sulfuric acid of 200mL/L or 240mL/L, rear running water;
3rd step surface finish, selects 800 orders or thinner Al 2o 3sand paper, finally uses alcohol ultrasonic cleaning.
The preparation method of 17. engine prop column surface of internal cavity carbide coatings as described in one of claim 13-16, is characterized in that: described step 3) in graphite paper be more than three grades, purity 99%, thickness is 0.1-0.35mm.
The preparation method of 18. engine prop column surface of internal cavity carbide coatings as described in one of claim 13-17, it is characterized in that: described step 6) in, be warming up to 1000-1130 DEG C, programming rate controls at 7 DEG C/min, temperature retention time is 4-12h, preferred 6-10h.
19. engine prop column preparation methods as described in one of claim 13-18, is characterized in that: selected plain steel is mild steel, medium carbon steel and high-carbon steel.
20. engine prop column preparation methods as described in one of claim 13-19, it is characterized in that: described protection gas is argon gas or nitrogen, gas flow is 4-8mL/min.
The preparation method of 21. engine prop column surface of internal cavity carbide coatings as described in one of claim 13-20, is characterized in that: described step 7) in heat treatment step be: heat-treat at about 550-800 DEG C, matrix is pearlitic structrure; Or heat-treat at 220-450 DEG C, matrix is bainite structure; Or heat-treat below 220 DEG C, matrix is martensitic structure.
CN201410658061.7A 2014-11-18 2014-11-18 Engine prop column and preparation method thereof Active CN104525860B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410658061.7A CN104525860B (en) 2014-11-18 2014-11-18 Engine prop column and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410658061.7A CN104525860B (en) 2014-11-18 2014-11-18 Engine prop column and preparation method thereof

Publications (2)

Publication Number Publication Date
CN104525860A true CN104525860A (en) 2015-04-22
CN104525860B CN104525860B (en) 2018-02-27

Family

ID=52841591

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410658061.7A Active CN104525860B (en) 2014-11-18 2014-11-18 Engine prop column and preparation method thereof

Country Status (1)

Country Link
CN (1) CN104525860B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106541109A (en) * 2016-10-14 2017-03-29 石嘴山市华兴源机械设备有限公司 Furnace of calcium carbide it is compound go out converter nose and preparation method
RU2649600C2 (en) * 2016-06-14 2018-04-04 Федеральное государственное бюджетное учреждение науки Удмуртский федеральный исследовательский центр Уральского отделения Российской академии наук Method of producing castings from iron-carbon alloys with alloyed surface layer containing carbide titanium
CN113136541A (en) * 2021-06-22 2021-07-20 中南大学 Zr-based alloy surface gradient ZrC coating and preparation method thereof

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2140462A (en) * 1983-05-25 1984-11-28 Maschf Augsburg Nuernberg Ag Multi-layer coated metallic body
CN101406948A (en) * 2008-11-20 2009-04-15 西安建筑科技大学 Method for preparing gray iron-base composite material for in situ production of titanium carbide
CN101479401A (en) * 2006-06-27 2009-07-08 谢夫勒两合公司 Wear-resistant coating and production method for the same
CN102286723A (en) * 2011-07-21 2011-12-21 中国第一汽车股份有限公司 Surface wear-resistance coating applied to automobile high-alloy steel movement friction pair
CN103160782A (en) * 2011-12-16 2013-06-19 中国科学院兰州化学物理研究所 Method of preparing diamond-like coating layer on the surface of automobile motor air valve tappet
CN103938167A (en) * 2014-03-19 2014-07-23 潍柴动力股份有限公司 Tappet and its preparation method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2140462A (en) * 1983-05-25 1984-11-28 Maschf Augsburg Nuernberg Ag Multi-layer coated metallic body
CN101479401A (en) * 2006-06-27 2009-07-08 谢夫勒两合公司 Wear-resistant coating and production method for the same
CN101406948A (en) * 2008-11-20 2009-04-15 西安建筑科技大学 Method for preparing gray iron-base composite material for in situ production of titanium carbide
CN102286723A (en) * 2011-07-21 2011-12-21 中国第一汽车股份有限公司 Surface wear-resistance coating applied to automobile high-alloy steel movement friction pair
CN103160782A (en) * 2011-12-16 2013-06-19 中国科学院兰州化学物理研究所 Method of preparing diamond-like coating layer on the surface of automobile motor air valve tappet
CN103938167A (en) * 2014-03-19 2014-07-23 潍柴动力股份有限公司 Tappet and its preparation method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
王亮亮等: "TiC/Fe表面梯度复合材料微区组织及陶瓷层磨损性能", 《焊接学报》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2649600C2 (en) * 2016-06-14 2018-04-04 Федеральное государственное бюджетное учреждение науки Удмуртский федеральный исследовательский центр Уральского отделения Российской академии наук Method of producing castings from iron-carbon alloys with alloyed surface layer containing carbide titanium
CN106541109A (en) * 2016-10-14 2017-03-29 石嘴山市华兴源机械设备有限公司 Furnace of calcium carbide it is compound go out converter nose and preparation method
CN106541109B (en) * 2016-10-14 2019-10-22 石嘴山市华兴源机械设备有限公司 Furnace of calcium carbide compound converter nose and preparation method out
CN113136541A (en) * 2021-06-22 2021-07-20 中南大学 Zr-based alloy surface gradient ZrC coating and preparation method thereof

Also Published As

Publication number Publication date
CN104525860B (en) 2018-02-27

Similar Documents

Publication Publication Date Title
CN104533992A (en) Brake disc and preparation method thereof
CN104525716A (en) Cold punched die and manufacturing method thereof
CN104533993A (en) Brake disc and preparation method thereof
CN104525315B (en) Hammerhead and production method thereof
CN104525900A (en) Wear resistant carbide coating layer and preparation method thereof
CN104525593A (en) Wire drawing die and production method thereof
CN104525860A (en) Engine tappet and production method thereof
CN104525909A (en) Wear-resisting pipe and manufacturing method thereof
CN104527150B (en) wear-resistant coating and preparation method thereof
CN104525913A (en) Guardrails and a manufacturing method thereof
CN104525573A (en) Roller and preparation method thereof
CN104525861B (en) Engine cam and preparation method thereof
CN104532234A (en) Wear resistant carbide coating and production method thereof
CN104525681A (en) A cold punching die and a manufacturing method thereof
CN104525914B (en) Engine cam and preparation method thereof
CN104525910A (en) Wear-resistant pipe and preparation method thereof
CN104525912A (en) Lining plate and preparation method thereof
CN104525916A (en) Engine tappet and manufacturing method thereof
CN104525887A (en) Grinding roller and preparation method thereof
CN104525888A (en) Guide roller and manufacturing method thereof
CN104532694B (en) Guard rail and preparation method thereof
CN104525898B (en) Guide plate and manufacturing method thereof
CN104525299B (en) Jaw plate and production method thereof
CN104532899A (en) Form-relieved tooth and preparation method thereof
CN104588616A (en) Wire-drawing die and manufacturing method thereof

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant
CB03 Change of inventor or designer information

Inventor after: Zhao Nana

Inventor after: Xiao Peng

Inventor after: Xu Yunhua

Inventor after: Lu Zhengxin

Inventor after: Zhong Lisheng

Inventor after: Liang Shuhua

Inventor after: Yan Yinglin

Inventor after: Ye Fangxia

Inventor after: Wang Juan

Inventor after: Zou Juntao

Inventor before: Xu Yunhua

Inventor before: Xiao Peng

Inventor before: Zhao Nana

Inventor before: Lu Zhengxin

Inventor before: Zhong Lisheng

Inventor before: Liang Shuhua

Inventor before: Yan Yinglin

Inventor before: Ye Fangxia

Inventor before: Wang Juan

Inventor before: Zou Juntao

CB03 Change of inventor or designer information