CN106756713A - Improve coating of combustion engine compressor drum barrel wearability peculiar to vessel and preparation method thereof - Google Patents
Improve coating of combustion engine compressor drum barrel wearability peculiar to vessel and preparation method thereof Download PDFInfo
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- CN106756713A CN106756713A CN201610989864.XA CN201610989864A CN106756713A CN 106756713 A CN106756713 A CN 106756713A CN 201610989864 A CN201610989864 A CN 201610989864A CN 106756713 A CN106756713 A CN 106756713A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
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Abstract
The present invention is to provide a kind of coating for improving combustion engine compressor drum barrel wearability peculiar to vessel and preparation method thereof.Combustion engine compressor drum barrel alloy substrate is pre-processed；Ceramic fibre is pre-processed, is 18%~80%YSZ powders, 18~80%Al according still further to mass ratio composition2O3The ratio mixing of powder and 2%~20% ceramic fibre, carries out ball-milling treatment and obtains ceramic composite powder to mixture；Using plasma spraying method in combustion engine compressor drum barrel alloy substrate one layer of tack coat of surface spraying；It is coated on tack coat using plasma spray and continues to spray one layer of Ceramic Composite working lining.The present invention solves the problems, such as that the big toughness of the fragility of ceramic coating is not enough using addition ceramic short fiber, realized in plasma ceramic coating fiber reinforced, the work to break of composite coating, slows down ceramic coating brittle layer and scales off in increase process of friction and wear, realizes improving the purpose of wearability.
Description
Technical field
Surface the present invention relates to metal material is modified, and combustion engine compressor drum barrel wearability specifically peculiar to vessel is applied
Layer and preparation method thereof.
Background technology
With the fast development of China's marine gas turbine, modernization naval vessel to the performance requirement of gas turbine increasingly
It is high.High-pressure compressor rotor is one of critical piece of gas turbine, for the supercharging air to entering gas turbine, makes air
Pressure reaches predetermined value.Its efficiency high, reliable operation are required for high-pressure compressor rotor, it is rigidly good, lightweight etc..Main body
Present following aspects：1. compact conformation, light weight, structure unit unit power quality is less than 1Kg/Kw.2. small volume, uses
When can be with save space.3. motion block is played, from cold start-up to band at full capacity, depending on the size and the difference of structural shape of the power of the assembling unit
In several minutes between half an hour, in case of emergency the starting time of many units can shorten about half left and right.4. run
Steadily, reliability is high, a large amount of unit reliabilities up to the forced outage rate of 99%, i.e. unit be only 1%.5. efficiency high, now simply
Cycle combustion turbine efficiency highest up to 42.9%, and Combined Cycle Unit efficiency highest oneself up to 58%, the latter is various at present
The peak efficiency value reached in thermal machine.In order to reach all requirement of the above, it is desirable to which the drum barrel of high-pressure compressor rotor is each
Drum barrel diameter between level disk is identical, and positioning is coordinated with the face of cylinder and end face between drum letter and disk, by precision bolt by they
Tense, frictional force transmitting torque is produced in end face.Part service efficiency is being improved, is being saved under the principle of material, high pressure drum barrel is being adopted
With coating soverlay technique prepare oxide ceramic coating serve it is heat-insulated, wear-resisting and erosion-resisting, to reach the elongated component longevity
Order, prevent unexpected touching from rubbing, improve the purpose of gas turbine proficiency.
Plasma arc temperature is very high, is particularly well-suited to spray compound oxidate ceramic, can spray work with complex shape
Part, deposition efficiency is high, easily prepares thick film coating and Large area coatings.Therefore, using plasma spraying technology in combustion engine peculiar to vessel
Compressor drum surface prepares wear-resisting oxide ceramic coating.
The defects such as the stomata, crackle and the layering that often occur in plasma spraying coating can be brought much to coating performance
Detrimental effect.YSZ/Al2O3Ceramic phase-brittle phase is belonged to, there is high temperature resistant, anti-oxidant, corrosion-resistant, but toughness
It is not enough.Research shows, during coating failure, the presence of fiber can be transmitted effectively, bear external force, and be pulled out in fiber
Go out, consumed energy during unsticking, and the extensions path of crackle can be extended, so as to improve the toughness of material, reduce material
Fragility.
Ceramic fibre is a kind of fibrous light refractory material, and temperature in use is high, heat-proof quality is good, high temeperature chemistry property is steady
The good characteristic such as fixed, corrosion-resistant, anti-oxidant, good thermal shock, non-volatile, pollution-free, thus in machinery, metallurgy, chemical industry, stone
The industry such as oil, ceramics, glass, electronics is obtained for and is widely applied.Ceramic fibre has obvious toughening effect in adding coating,
Fiber reinforced mechanism mainly includes crackle bending and deflection, fibre debonding, spike protein gene and fiber bridge joint, wherein spike protein gene
It is fiber reinforced main mechanism, can be described as being close to the fiber of crack tip under outer stress along it and matrix
Interface skids off.In the process, external carbuncle needs to overcome interface friction shearing force to do work, and increases the work to break of composite.
Spike protein gene can cause crack tip stress relaxation to slow down the purpose of Crack Extension so as to reach.
Traditional combustion engine compressor drum barrel plasma spraying oxide ceramics wear-resistant coating peculiar to vessel, generally using aluminum oxide pottery
There is hardness greatly in porcelain coating, fragility is big not in view of ceramic coating as working lining in fretting wear, but the not enough spy of toughness
Point, coating is easily in process of friction and wear, and the micro-crack of coat inside is continuous at holiday (such as hole, micro-crack)
Or flaky particles interface forms and constantly extended along defect or interface, the micro-crack of different directions is interlaced and forms net
Shape, so as to the fracture for causing coating causes coating fragility bed separation, causes its wear resistance decrease.
The content of the invention
Coating it is an object of the invention to improve combustion engine compressor drum barrel wearability peculiar to vessel.The present invention also aims to
A kind of preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel is provided.
The coating for improving combustion engine compressor drum barrel wearability peculiar to vessel of the invention is included using plasma spraying method spraying
Tack coat on combustion engine compressor drum barrel alloy substrate and the working lining being sprayed on using plasma spraying method on tack coat,
The working lining is made up of working lining powder body material and ceramic fibre, and working lining powder body material is by YSZ and Al2O3It is made, working lining
Mass ratio composition be 18%~80%YSZ powders, 18~80%Al2O3Powder and 2%~20% ceramic fibre.
The coating for improving combustion engine compressor drum barrel wearability peculiar to vessel of the invention can also include：
1st, the ceramic fibre is SiC fibers, mullite fiber, YSZ fibers or alumina silicate fibre.
2nd, the YSZ is Yttria stabilized zirconia that yttria levels are 6%~8%mol.
3rd, the bonding composition of layer is NiCoCrAlY, NiAl or NiCrAlY.
The preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel of the invention is：
(1) combustion engine compressor drum barrel alloy substrate is pre-processed；
(2) ceramic fibre is pre-processed, is 18%~80%YSZ powders, 18~80% according still further to mass ratio composition
Al2O3The ratio mixing of powder and 2%~20% ceramic fibre, carries out ball-milling treatment and obtains ceramic composite powder to mixture；
(3) using plasma spraying method in combustion engine compressor drum barrel alloy substrate one layer of tack coat of surface spraying；
(4) it is coated on tack coat using plasma spray and continues to spray one layer of Ceramic Composite working lining.
The preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel of the invention can also include：
1st, the parameter of pre-treatment process of ceramic fibre is：(1) ball-milling treatment, ratio of grinding media to material is 2：1st, ball milling speed is 350r/
Min, Ball-milling Time are 10min, (2) ultrasonic disperse 1h, (3) dried process；The technological parameter of ball-milling treatment is carried out to mixture
For：Ratio of grinding media to material is 1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；The particle diameter of ceramic composite powder is 20 μm~120 μ
m。
2nd, before plasma spraying is carried out, bonding layer material and ceramic composite powder are dried, drying temperature 200
DEG C, soaking time 2h.
3rd, plasma spraying tack coat technological parameter is：570~630A of electric current, 65~75V of voltage, spray distance 130~
150mm, 90 ° of spray angle, adhesive layer thickness is 30 μm~80 μm.
4th, plasma spraying working lining technological parameter is：590~640A of electric current, 70~78V of voltage, spray distance 100~
120mm, 90 ° of spray angle, the thickness of working lining is 200 μm~300 μm.
In order to improve the wearability of plasma spraying ceramic coat, the present invention solves ceramics and applies using addition ceramic short fiber
The problem that the big toughness of fragility of layer is not enough, realized in plasma ceramic coating it is fiber reinforced, it is multiple in increase process of friction and wear
The work to break of coating is closed, is slowed down ceramic coating brittle layer and is scaled off, realize improving the purpose of wearability.From plasma spraying
Technology prepares YSZ/Al2O3The composite coating of doped ceramics fiber, is used to improve combustion engine compressor drum barrel wearability peculiar to vessel.
Ceramic fibre can realize fiber reinforced, compound painting in increase process of friction and wear in composite coating in the present invention
The work to break of layer, slows down ceramic coating brittle layer and scales off, and realizes improving the purpose of wearability.Its Main Function mechanism is：
1. crackle bending and deflection, hinder the expansion of crackle.2. fibre debonding, spike protein gene and fiber bridge joint, make the disconnected of composite coating
Work(increase is split, crack tip stress relaxation is caused so as to slow down Crack Extension.
The present invention includes following beneficial effect：
(1)YSZ/Al2O3Ceramic phase-brittle phase is belonged to, toughness is not enough.Composite is formed after doped ceramics fiber to apply
Layer, ceramic fibre has certain toughening effect in composite coating, and reduction oxide ceramic coating is in process of friction and wear
Brittle layer scales off, and improves combustion engine compressor drum barrel wearability peculiar to vessel.
(2) plasma spraying prepares YSZ/Al2O3The composite coating of doped ceramics fiber in powder, is a kind of simple and practical
Property method high.
Brief description of the drawings
Coating cross sections pattern after Fig. 1 doped ceramics fibers；
The scanning electron microscope (SEM) photograph of coating frictional abrasion surface after Fig. 2 doped ceramics fibers；
The scanning electron microscope (SEM) photograph of coating frictional abrasion surface after Fig. 3 undoped p ceramic fibres；
The weightless comparison diagram of coating friction after Fig. 4 doped ceramics fiber and undoped p ceramic fibre.
Specific embodiment
The present invention is doped to YSZ/Al by by ceramic fibre2O3Composite powder is formed in powder, YSZ/Al is prepared2O3
The composite coating of doped ceramics fiber.Ceramic fibre in coating can be solved under compressor drum barrel actual condition, and ceramics are applied
Layer exist the big toughness of fragility it is not enough the characteristics of, easily cause the problem that brittle layer scales off, improve the anti-wear performance of coating.
Matrix preferably is selected from：Austenitic stainless steel, martensitic stain less steel, ferritic stainless steel.
Tack coat primitive component is NiCoCrAlY or NiAl or NiCrAlY.
Working lining original material is YSZ/Al2O3.Wherein YSZ is (i.e.：Yttria-Stabilized Zirconia, yittrium oxide
Stabilized zirconia), yttria levels are 6%~8%mol.
Ceramic fibre is that the ceramic fibre of doping is SiC fibers or mullite fiber or YSZ fibers or alumina silicate fibre etc..
Preparation method for improving the coating of combustion engine compressor drum barrel wearability peculiar to vessel of the invention, it is related to a kind of base
YSZ/Al is prepared in plasma spraying technology2O3The method of doped ceramics fiber composite coating, comprises the following steps：
(1) alloy substrate pretreatment：The surface of matrix is polished smooth using sand paper, then uses absolute ethyl alcohol and acetone
Matrix after cleaning is polished successively；Before plasma spraying, blasting treatment is carried out；
(2) preparation of composite tie layer sprayed on material：By ceramic fibre through ball-milling treatment to appropriate particle size, ultrasonic disperse,
Dried process；Ball-milling treatment after working lining powder body material is mixed according to a certain percentage with ceramic fibre, obtains composite granule；
(3) dusty spray pretreatment：It is dried to powder is preliminarily sprayed, 200 DEG C of holding temperature, soaking time 2h；
(4) tack coat is sprayed：Using plasma spraying method in pretreated one layer of tack coat of alloy substrate surface spraying；
(5) spray coating operations layer：Applied using one layer of Ceramic Composite of spraying is continued on plasma spraying tack coat after spray coating
Layer obtains complete coating system.
The step 2) in ball milling prepare ceramic fibre technological parameter and be：Ratio of grinding media to material is 2：1, ball milling speed is 350r/
Min, Ball-milling Time is 10min.Ultrasonic disperse 1h, dried process.Prepare the YSZ/Al of doped ceramics fiber2O3Composite powder work
Skill parameter is：Ratio of grinding media to material is 1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；The particle diameter of ceramic composite powder is 20 μm
~120 μm.
The step 4) in, plasma spraying prepares tack coat, and plasma spray coating process parameter is：Electric current be 570~
630A, voltage is 65~75V, and spray distance is 130~150mm, and spray angle is 90 °.
The step 5) in, plasma spraying prepares ceramic working lining, and plasma spray coating process parameter is：Electric current is 590
~640A, voltage is 70~78V, and spray distance is 100~120mm, and spray angle is 90 °.
In the abrasion-proof ceramic coat system, abrasion-proof ceramic coat gross thickness is 230 μm~380 μm, wherein bonding thickness
It is 30 μm~80 μm to spend, and the thickness of ceramic working lining is 200 μm~300 μm.
In order to prove effect of the invention, illustrate below and the present invention is described in more detail.
Embodiment 1
Step one：The surface of 1Cr18Ni9Ti matrixes is polished smooth using sand paper, then uses absolute ethyl alcohol and acetone
Matrix after cleaning is polished successively；Before plasma spraying, blasting treatment is carried out；
Step 2：Measure YSZ powder, Al2O3Powder and mullite fiber, using ball mill in mass fraction ratio
(0.20:0.76:0.04) mix, prepare composite powder.Mullite fiber ball milling condition is：Ratio of grinding media to material is 2：1, ball milling speed is
350r/min, Ball-milling Time is 10min.Ultrasonic disperse 1h, dried process.Prepare the doping mullite fiber of mass fraction 4%
YSZ/Al2O3Composite powder, ratio of grinding media to material is 1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；
Step 3：Tack coat NiCrAlY powder and step 2 is prepared into composite powder it is respectively put into drying box and is dried,
Drying temperature is 200 DEG C, and drying time is 2h；
Step 4：The dried tack coat NiCrAlY powder of step 3 is put into plasma spraying dust feeder, carry out etc.
Plasma spray prepares tack coat, and plasma spraying condition is：Electric current is 590~610A, and voltage is 65~75V, and spray distance is
130~150mm, spray angle is 90 °；
Step 5：The dried composite powder of step 3 is put into plasma spraying dust feeder, plasma spraying is carried out
Ceramic working lining is prepared, plasma spraying condition is：Electric current be 620~640A, voltage be 75~78V, spray distance be 100~
120mm, spray angle is 90 °.
Fig. 1 for doped ceramics fiber composite coating Cross Section Morphology, ceramic composite coating system by matrix, tack coat,
Working lining is constituted.As shown in Fig. 2 the ceramic layer anti-wear performance for obtaining being doped with after mullite fiber is excellent, there is not big face
There is a small amount of peeling and cheat in product bed separation, only surface, and there is slight abrasive wear.
Comparative example
Undoped p mullite fibre is prepared using plasma spray coating process similarly to Example 1 on 1Cr18Ni9Ti matrixes
The YSZ/Al of dimension2O3Composite coating.Comprise the following steps：
Step one：The surface of 1Cr18Ni9Ti matrixes is polished smooth using sand paper, then uses absolute ethyl alcohol and acetone
Matrix after cleaning is polished successively；Before plasma spraying, blasting treatment is carried out；
Step 2：Measure YSZ powder, Al2O3Powder, using ball mill in mass fraction ratio (0.20:0.80) mix,
Prepare the YSZ/Al of undoped p mullite fiber2O3Composite powder end.Ratio of grinding media to material is 1：1, ball milling speed is 200r/min, ball milling
Time is 2h；
Step 3：Tack coat NiCrAlY powder and step 2 is prepared into composite powder it is respectively put into drying box and is dried,
Drying temperature is 200 DEG C, and drying time is 2h；
Step 4：The dried tack coat NiCrAlY powder of step 3 is put into plasma spraying dust feeder, carry out etc.
Plasma spray prepares tack coat, and plasma spraying condition is：Electric current is 570~630A, and voltage is 65~75V, and spray distance is
130~150mm, spray angle is 90 °；
Step 5：The dried composite powder of step 3 is put into plasma spraying dust feeder, plasma spraying is carried out
Ceramic working lining is prepared, plasma spraying condition is：Electric current be 620~640A, voltage be 75~78V, spray distance be 100~
120mm, spray angle is 90 °.
Obtain wear-resistant coating system performance general, because ceramic working lining does not adulterate mullite fiber, as shown in figure 3,
So that coating is after same friction-wear test is carried out, large area fragility bed separation is there occurs.Fig. 4 is doping mass fraction
The friction weightlessness comparison diagram of 4% ceramic fibre composite coating and undoped p ceramic fibre composite coating, by understanding that friction is lost in figure
Weight is reduced to the 52mg of doping fiber composite coating by the 72.5mg of undoped p fiber composite coating, and wear weight loss is substantially reduced.Cause
This, it is seen that is in ceramic working lining YSZ/Al2O3Adding ceramic fibre can lift its anti-wear performance.
Embodiment 2
Step one：The surface of 1Cr18Ni9Ti matrixes is polished smooth using sand paper, then uses absolute ethyl alcohol and acetone
Matrix after cleaning is polished successively；Before plasma spraying, blasting treatment is carried out；
Step 2：Measure YSZ powder, Al2O3Powder and SiC fibers, using ball mill in mass fraction ratio (0.30:
0.66:0.04) mix, prepare composite powder.SiC fiber ball milling conditions are：Ratio of grinding media to material is 2：1, ball milling speed is 350r/min,
Ball-milling Time is 10min.Ultrasonic disperse 1h, dried process.Prepare the YSZ/Al of the SiC fibers of doping mass fraction 4%2O3It is multiple
Powder is closed, ratio of grinding media to material is 1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；
Step 3：Tack coat NiCrAlY powder and step 2 is prepared into composite powder it is respectively put into drying box and is dried,
Drying temperature is 200 DEG C, and drying time is 2h；
Step 4：The dried tack coat NiCrAlY powder of step 3 is put into plasma spraying dust feeder, carry out etc.
Plasma spray prepares tack coat, and plasma spraying condition is：Electric current is 570~630A, and voltage is 65~75V, and spray distance is
130~150mm, spray angle is 90 °；
Step 5：The dried composite powder of step 3 is put into plasma spraying dust feeder, plasma spraying is carried out
Ceramic working lining is prepared, plasma spraying condition is：Electric current be 590~610A, voltage be 70~74V, spray distance be 100~
120mm, spray angle is 90 °.
Embodiment 3
Doping mass fraction is prepared using plasma spray coating process similarly to Example 2 on 1Cr18Ni9Ti matrixes
The YSZ/Al of 8% SiC fibers2O3Composite coating.Its step is：
Step one：The surface of 1Cr18Ni9Ti matrixes is polished smooth using sand paper, then uses absolute ethyl alcohol and acetone
Matrix after cleaning is polished successively；Before plasma spraying, blasting treatment is carried out；
Step 2：Measure YSZ powder, Al2O3Powder and SiC fibers, using ball mill in mass fraction ratio (0.28:
0.64:0.08) mix, prepare composite powder.SiC fiber ball milling conditions are：Ratio of grinding media to material is 2：1, ball milling speed is 350r/min,
Ball-milling Time is 10min.Ultrasonic disperse 1h, dried process.Prepare the YSZ/Al of the SiC fibers of doping mass fraction 8%2O3It is multiple
Powder is closed, ratio of grinding media to material is 1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；
Step 3：Tack coat NiCrAlY powder and step 2 is prepared into composite powder it is respectively put into drying box and is dried,
Drying temperature is 200 DEG C, and drying time is 2h；
Step 4：The dried tack coat NiCrAlY powder of step 3 is put into plasma spraying dust feeder, carry out etc.
Plasma spray prepares tack coat, and plasma spraying condition is：Electric current is 570~630A, and voltage is 65~75V, and spray distance is
130~150mm, spray angle is 90 °；
Step 5：The dried composite powder of step 3 is put into plasma spraying dust feeder, plasma spraying is carried out
Ceramic working lining is prepared, plasma spraying condition is：Electric current be 590~610A, voltage be 70~74V, spray distance be 100~
120mm, spray angle is 90 °.
Claims (9)
1. a kind of coating for improving combustion engine compressor drum barrel wearability peculiar to vessel, it is characterized in that：Including using plasma spraying method
The tack coat being sprayed on combustion engine compressor drum barrel alloy substrate and the work being sprayed on using plasma spraying method on tack coat
Make layer, the working lining is made up of working lining powder body material and ceramic fibre, and working lining powder body material is by YSZ and Al2O3It is made,
The mass ratio composition of working lining is 18%~80%YSZ powders, 18~80%Al2O3Powder and 2%~20% ceramic fibre.
2. the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 1, it is characterized in that：The ceramics
Fiber is SiC fibers, mullite fiber, YSZ fibers or alumina silicate fibre.
3. the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 2, it is characterized in that：The YSZ
It is the Yttria stabilized zirconia that yttria levels are 6%~8%mol.
4. the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 3, it is characterized in that：The bonding
Composition of layer is NiCoCrAlY, NiAl or NiCrAlY.
5. a kind of preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel, it is characterized in that：
(1) combustion engine compressor drum barrel alloy substrate is pre-processed；
(2) ceramic fibre is pre-processed, is 18%~80%YSZ powders, 18~80%Al according still further to mass ratio composition2O3
The ratio mixing of powder and 2%~20% ceramic fibre, carries out ball-milling treatment and obtains ceramic composite powder to mixture；
(3) combustion engine compressor drum barrel alloy substrate one layer of tack coat of surface spraying is coated in using plasma spray；
(4) it is coated on tack coat using plasma spray and continues to spray one layer of Ceramic Composite working lining.
6. the preparation method of the coating of the raising combustion engine compressor drum barrel wearability peculiar to vessel stated according to claim 5, it is characterized in that：
The parameter of pre-treatment process of ceramic fibre is：(1) ball-milling treatment, ratio of grinding media to material is 2：1st, when ball milling speed is 350r/min, ball milling
Between be 10min, (2) ultrasonic disperse 1h, (3) dried process；It is to the technological parameter that mixture carries out ball-milling treatment：Ratio of grinding media to material is
1：1, ball milling speed is 200r/min, and Ball-milling Time is 2h；The particle diameter of ceramic composite powder is 20 μm~120 μm.
7. the preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 5, its feature
It is：Before plasma spraying is carried out, bonding layer material and ceramic composite powder are dried, 200 DEG C of drying temperature, be incubated
Time 2h.
8. the preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 5, its feature
It is：Plasma spraying tack coat technological parameter is：570~630A of electric current, 65~75V of voltage, 130~150mm of spray distance, spray
90 ° of angle is applied, adhesive layer thickness is 30 μm~80 μm.
9. the preparation method of the coating for improving combustion engine compressor drum barrel wearability peculiar to vessel according to claim 5, its feature
It is：Plasma spraying working lining technological parameter is：590~640A of electric current, 70~78V of voltage, 100~120mm of spray distance, spray
90 ° of angle is applied, the thickness of working lining is 200 μm~300 μm.
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| CN109023205A (en) * | 2018-08-30 | 2018-12-18 | 昆明理工大学 | A kind of preparation method of thermal spraying thermal barrier coating |
| CN110835719A (en) * | 2018-08-17 | 2020-02-25 | 北京航化节能环保技术有限公司 | Hot-sprayed high-temperature oxidation-resistant coating for gasifier burner and preparation method thereof |
| CN111876716A (en) * | 2020-07-10 | 2020-11-03 | 江苏科环新材料有限公司 | Fiber-reinforced anti-explosion tube composite coating for tube heating surface of boiler and preparation thereof |
| CN112481577A (en) * | 2020-11-18 | 2021-03-12 | 东北大学 | Thermal shock resistant thermal barrier coating material and preparation method thereof |
| CN114318206A (en) * | 2021-12-13 | 2022-04-12 | 中船重工龙江广瀚燃气轮机有限公司 | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof |
| CN114351080A (en) * | 2022-01-13 | 2022-04-15 | 中国民航大学 | Preparation method of plasma spraying YSZ ceramic matrix sealing coating capable of improving deposition rate |
| CN115323463A (en) * | 2022-09-23 | 2022-11-11 | 西北有色金属研究院 | Method for preparing composite ceramic coating on surface of ZK61M magnesium alloy |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS60110863A (en) * | 1983-11-22 | 1985-06-17 | Mitsubishi Heavy Ind Ltd | Manufacture of thruster |
| CN102094164A (en) * | 2009-12-15 | 2011-06-15 | 沈阳天贺新材料开发有限公司 | Nanometer zirconium oxide thermal barrier coating and preparation method thereof |
| CN102963061A (en) * | 2012-12-03 | 2013-03-13 | 上海理工大学 | Nano columnar crystal thermal barrier coating layer and preparation method thereof |
| CN104085153A (en) * | 2014-06-27 | 2014-10-08 | 哈尔滨工程大学 | Composite material and preparation method thereof |
| CN105755418A (en) * | 2016-03-23 | 2016-07-13 | 西安交通大学 | Ceramic fiber/crystal whisker reinforced composite thermal barrier coating and preparation method thereof |
-
2016
- 2016-11-10 CN CN201610989864.XA patent/CN106756713A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS60110863A (en) * | 1983-11-22 | 1985-06-17 | Mitsubishi Heavy Ind Ltd | Manufacture of thruster |
| CN102094164A (en) * | 2009-12-15 | 2011-06-15 | 沈阳天贺新材料开发有限公司 | Nanometer zirconium oxide thermal barrier coating and preparation method thereof |
| CN102963061A (en) * | 2012-12-03 | 2013-03-13 | 上海理工大学 | Nano columnar crystal thermal barrier coating layer and preparation method thereof |
| CN104085153A (en) * | 2014-06-27 | 2014-10-08 | 哈尔滨工程大学 | Composite material and preparation method thereof |
| CN105755418A (en) * | 2016-03-23 | 2016-07-13 | 西安交通大学 | Ceramic fiber/crystal whisker reinforced composite thermal barrier coating and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 张亮: "等离子喷涂抗高温氧化涂层的组织性能分析", 《中国优秀硕士学位论文全文数据库》 * |
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| CN109023205A (en) * | 2018-08-30 | 2018-12-18 | 昆明理工大学 | A kind of preparation method of thermal spraying thermal barrier coating |
| CN111876716A (en) * | 2020-07-10 | 2020-11-03 | 江苏科环新材料有限公司 | Fiber-reinforced anti-explosion tube composite coating for tube heating surface of boiler and preparation thereof |
| CN112481577A (en) * | 2020-11-18 | 2021-03-12 | 东北大学 | Thermal shock resistant thermal barrier coating material and preparation method thereof |
| CN114318206A (en) * | 2021-12-13 | 2022-04-12 | 中船重工龙江广瀚燃气轮机有限公司 | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof |
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| CN114351080B (en) * | 2022-01-13 | 2023-12-12 | 中国民航大学 | Preparation method of plasma spraying YSZ ceramic matrix sealing coating capable of improving deposition rate |
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