CN108642435A - A kind of big thickness high-temperature protection coating of turbine outer ring inner wall and preparation method thereof - Google Patents
A kind of big thickness high-temperature protection coating of turbine outer ring inner wall and preparation method thereof Download PDFInfo
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- CN108642435A CN108642435A CN201810894348.8A CN201810894348A CN108642435A CN 108642435 A CN108642435 A CN 108642435A CN 201810894348 A CN201810894348 A CN 201810894348A CN 108642435 A CN108642435 A CN 108642435A
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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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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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
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-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
- C23C4/18—After-treatment
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- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to big thickness high-temperature protection coatings of a kind of turbine outer ring inner wall and preparation method thereof, belong to technical field of material surface treatment.The material of a kind of big thickness high-temperature protection coating of turbine outer ring inner wall, including superalloy turbine outer shroud and the coating for being set to turbine outer ring inner wall, coating is CoNiCrAlY.Coating texture's even compact, hardness are moderate, high temperature protection function admirable.The preparation method of the above-mentioned big thickness high-temperature protection coating of turbine outer ring inner wall, including：The turbine outer ring inner-wall spraying Jing Guo preceding processing at least twice, between adjacent spraying twice, destressing heat treatment and secondary blasting treatment are carried out to coating, after the completion of spraying, diffusion in vacuum heat treatment is carried out to coating.The preparation method enhances coating and the bond strength of turbine outer ring and the cohesive strength of coating, can significantly reduce big thickness coatings and fall off risk, improve the yield rate of coating.
Description
Technical field
The present invention relates to technical field of material surface treatment, and more particularly to a kind of big thickness high temperature of turbine outer ring inner wall is anti-
Protect coating and preparation method thereof.
Background technology
" heart " of the aero-engine as aircraft can provide power needed for flight for aircraft, be a kind of highly complex
With accurate thermal machine, core component includes air compressor, combustion chamber and turbine etc..Wherein, turbine includes turbine
Outer shroud and turbine rotor blade, rotor blade are set in the ring of turbine outer ring, inner wall of the blade tip towards turbine outer ring.Outside turbine
Important component of the ring as composition engine gas runner also primarily serves during controlling working condition between turbine blade-tip
The effect of gap.It is reported that caused by the 1/3 of turbine performance loss is leakage by tip clearance, tip clearance and blade height
The ratio between often increase by 1%, turbine efficiency reduces about 1.5%, and oil consumption rate then increases about 3%.Therefore, turbine outer ring need and turbo blade
Blade tip possesses good cooperation.Turbine outer ring can be contacted directly with high-temperature fuel gas during military service, and environment temperature is higher, and be worked
Inclement condition, this has higher requirement for the high-temperature behavior of turbine outer ring.It is typically employed on turbine outer ring inner wall and adds honeycomb
Or the structure type of directly applying coating is protected.Honeycomb is high with specific strength, thermal fatigue resistance is good and can grind
The advantages that erosion, can link together with turbine outer ring by welding, but its service temperature is easy by solder fusing temperature
The limitation of degree, and its fire-resistant gas scouring capability is still not ideal enough.
As another candidate scheme, the coating material coated by the Service Environment requirement of turbine outer ring need to have excellent
High temperature resistance, anti-oxidant, heat resistanceheat resistant erosion and have good seal performance.MCrAlY coatings because with excellent resistance to high temperature oxidation and
The features such as hot corrosion resistance, low crisp/ductility transition temperature and good high-temp plastic, is widely used to turbogenerator heat
The protection of end pieces.The preparation method of MCrAlY coatings has physical vapour deposition (PVD), thermal spraying and laser melting coating etc. a variety of.Physics gas
Phase deposition technique includes mainly electro beam physics vapour deposition, sputtering, ion plating etc., and prepared coating structure is fine and close, in conjunction with strong
Degree is high, but deposition efficiency is low, manufacturing cost is high, and Composition Control is more difficult when coating material complicated component, it is difficult to be used for more
The preparation of the big thickness coatings of constituent element.MCrAlY coatings prepared by laser cladding have with substrate combinating strength is high, consistency is high,
The advantages that crystal grain is small, but coating is easily broken off the application for limiting the technology.Plasma spray technology utilizes heat source by powder or silk material
It is heated to melting or semi-molten state, and is injected into substrate material surface using high-speed flow and forms coating, in state
Anti- construction and national product life numerous areas obtain extensive use.Wherein, electric arc spraying and air plasma spraying are in air
It is operated in environment, sprayed on material oxidation is more serious, and gas can deposit on matrix together with molten particles, to shadow
The compactness and porosity of coating are rung, and then influences the high temperature oxidation resistance of coating.High speed flame spraying (HVOF/AF) can be made
Standby high compactness, high bond strength, low porosity and the small coating of thermal stress, but spraying is carried out under atmospheric environment, still not
Evitable the problems such as there are coating internal oxidition is serious and vulnerable to pollution.Coating structure prepared by cold spraying is fine and close and oxide contains
It measures low, there is excellent high temperature oxidation resistance, but shorter spray is away from limiting application of the technology on complex part.
It should be pointed out that minimize turbine outer ring and interlobate gap, prepared protective coating needs to carry out
Grinding is to suitable roughness；And the residual stress accumulation in big thickness coatings preparation process causes turbine outer ring may
A degree of deformation occurs, therefore coating must assure that certain allowance on thickness.On the other hand, due to turbine outer ring
Inner wall protective coating is on active service in high temperature and the combustion gas environment of corrosion for a long time, and turbine outer ring inner wall and blade tip are in work shape
State is difficult to avoid that improper scraped finish can occur when changing, it is desirable that coating must have is on active service when certain thickness can meet long
It is required that.However, with the increase of coating layer thickness, internal residual stress is more easy to concentrate, be on active service during again there are Long-term Vibration,
The problems such as improper scraped finish of blade tip and the erosion of high temperature corrosion medium, lead to coating coated by turbine outer ring inner wall easily
Partly or wholly obscission occurs.For these reasons, there is an urgent need for be well combined with matrix and high in the exploitation of turbine outer ring inner wall
The excellent big thickness coatings and preparation method thereof of warm barrier propterty.
Invention content
In view of the deficiencies of the prior art, the purpose of the present invention is to provide a kind of big thickness high temperature protections of turbine outer ring inner wall
Coating, which is well combined with matrix and high temperature protection function admirable.
Another object of the present invention is to provide the preparation method of the big thickness high-temperature protection coating of above-mentioned turbine outer ring inner wall,
This method is easy to operate, and controllability is strong, and high yield rate is environmentally friendly.
The present invention solves its technical problem using following technical scheme to realize.
The present invention proposes a kind of big thickness high-temperature protection coating of turbine outer ring inner wall, including superalloy turbine outer shroud and sets
It is placed in the coating of turbine outer ring inner wall, the material of coating is CoNiCrAlY, which has excellent anti-oxidant and heat and corrosion resistant
Performance, and its comprehensive performance can be improved by being heat-treated after spraying.
The present invention proposes a kind of preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall, including：
The turbine outer ring inner-wall spraying Jing Guo preceding processing at least twice, between adjacent spraying twice, to coating into
After the completion of spraying, diffusion in vacuum heat treatment is carried out to coating for row destressing heat treatment and secondary blasting treatment.
Beneficial effects of the present invention include：
(1) spraying process carries out in low vacuum environment, and beam-plasma spot diameter is big and beam spot internal temperature, velocity gradient
Small, dusty spray can be melted fully, can be effectively reduced no cofusing particle ratio in coating and be ensured that coating structure is uniform, hardness is suitable
In, ensure that coating has excellent high temperature protection performance.
(2) before spraying starts, by vacuumizing and filling argon gas repeatedly, vacuum chamber indoor oxygen/nitrogen content can be effectively reduced,
To which effectively control coating material occurs to aoxidize and be nitrogenized in spraying process, prevent from generating hard particles or item in coat inside
Band, while coating still has certain porosity, can effectively be reduced when with blade tip improper scraped finish occurs for turbine outer ring
Damage to blade.
(3) turbine outer ring is carried out blasting treatment and treats spray-coating surface using transferred arc before spraying to clear up, it can be abundant
Surface oxidized skin and impurity to be sprayed are removed, coating surface activity to be painted is significantly improved；Spraying process carries out in inertia protective atmosphere,
Allow the temperature higher of turbine outer ring, it is ensured that coating has good bond strength with turbine outer ring；By at Vacuum Heat
It manages and carries out the modes such as destressing processing and DIFFUSION TREATMENT in stove, can further enhance outside the cohesive strength and coating and turbine of coating
The bond strength of ring reduces big thickness coatings and falls off risk.
(4) spraying and heat treatment process carry out in vacuum chamber, and dust, noise and thermal pollution are effectively controlled,
The harm and environmental pollution to operator can be reduced.
Description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the big thickness high-temperature protection coating cross-sectional view of turbine outer ring inner wall of the present invention；
Fig. 2 is CoNiCrAlY coating cross sections patterns in the embodiment of the present invention.
Icon：1- superalloy turbine outer shrouds；2-CoNiCrAlY coatings.
Specific implementation mode
It in order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below will be in the embodiment of the present invention
Technical solution be clearly and completely described.The person that is not specified actual conditions in embodiment, builds according to normal condition or manufacturer
The condition of view carries out.Reagents or instruments used without specified manufacturer is the conventional production that can be obtained by commercially available purchase
Product.
Below to big thickness high-temperature protection coating of a kind of turbine outer ring inner wall of the embodiment of the present invention and preparation method thereof into
Row illustrates.
Fig. 1 is please referred to, an embodiment of the present invention provides a kind of big thickness high-temperature protection coatings of turbine outer ring inner wall, including whirlpool
Wheel outer shroud 1 and coating 2, coating 2 are attached to the inner wall of turbine outer ring 1.In the embodiment of the present invention, the material of turbine outer ring 1 is height
The material of temperature alloy, coating 2 is CoNiCrAlY.Preferably, the thickness of coating 2 is 0.8~1.5mm.
An embodiment of the present invention provides the preparation methods of the big thickness high-temperature protection coating of above-mentioned turbine outer ring inner wall, including：
The turbine outer ring inner-wall spraying Jing Guo preceding processing at least twice, between adjacent spraying twice, to coating into
After the completion of spraying, diffusion in vacuum heat treatment is carried out to coating for row destressing heat treatment and secondary blasting treatment.
Specifically, by after superalloy turbine outer shroud degreasing degreasing, treats spraying position and carry out pre-treatment.The present invention is implemented
Pre-treatment in example includes sandblasting, the cleaning of transferred arc electricity and preheating.
Blasting treatment can remove turbine outer ring surface oxidized skin to be sprayed to increase surface-active, improve coating and turbine outer ring
Between bond strength.In sandblasting procedures, masking protection, sandblasting are carried out to turbine outer ring non-spraying region frock clamp or adhesive tape
Pressure control is 0.3~0.6MPa, and sandblasting distance controlling is in 100~300mm, the nozzle axial direction and turbine outer ring of sand-blasting machine
Inner wall keeps 60 °~90 ° of angle.After blasting treatment, spray-coating surface surface roughness Ra>3 μm, residual can be blown off with compressed air
Sand grains or dust, make sprayed surface roughness uniformity and without metallic luster and pollution-free.It should be noted that at sandblasting
Sand material used in reason can be white fused alumina, Brown Alundum or fused alumina zirconia, and the granularity of sand material can be 24~46#.
Further to remove the oxidation film and other dirts of turbine outer ring coating surface to be painted, the very high surface of activity is generated, with
Coating and turbine outer ring is promoted to generate certain metallurgical binding, treating spray-coating surface using transferred arc before spraying carries out sputtering cleaning.
Specifically, the turbine outer ring that sandblasting is roughened, which is put into fixture, is placed in low-voltage plasma spraying vacuum chamber, take out true
Sky is to 0.5mbar, then backfills argon gas to 35~50mbar, the electric current of plasma gun is 550~700A, transfer arc current is
20~40A, argon flow amount are 55~70L/min, hydrogen flowing quantity is 0~3L/min, spray is away from for 250~350mm, plasma gun
Under conditions of movement speed is 400~600mm/s, turbine outer ring rotating speed is 40~80rpm, turbine outer ring coating surface to be painted is carried out
Transferred arc electricity is cleared up.
After the cleaning of transferred arc electricity, the pre-heat treatment is carried out to turbine outer ring using plasma flame flow under the conditions of non-powder feeding,
To improve the temperature that coating is contacted with turbine outer ring surface, reduction is answered because what the thermal dilation difference of turbine outer ring and coating generated
Power enhances the bond strength of coating and turbine outer ring.
The method of the pre-heat treatment includes：In non-powder feeding, vacuum chamber pressure be 65~80mbar, plasma gun electric current is
550~700A, argon gas flow be 55~70L/min, the flow of hydrogen be 0~5L/min, spray away from for 250~350mm, etc. from
Under conditions of sub- spray gun movement speed is 400~600mm/s, turbine outer ring rotating speed is 40~80rpm, plasma flame flow pair is utilized
Turbine outer ring carries out the pre-heat treatment.It should be noted that preheating temperature is 400~800 DEG C, if when transferred arc electricity is cleared up outside turbine
Ring has reached this temperature, then skips preheating step.
Spraying is to prepare the critical process of big thickness coatings.Specifically, vacuum chamber pressure be 65~80mbar, etc. from
Sub- spray gun electric current is 650~850A, argon flow amount is 40~55L/min, hydrogen flowing quantity is 4~11L/min, helium gas flow 0
~10L/min, powder feeding rate are 30~50g/min, spray gun movement speed is 40~70mm/s, turbine outer ring rotating speed be 200~
Under conditions of 400rpm, sprayed using atomization CoNiCrAlY powder.In the embodiment of the present invention, the coating layer thickness of preparation is 0.8
~1.5mm.
There can be the accumulation of coating residual stress in spraying process, with the increase of coating layer thickness, residual stress is tired in coating
Product can be also more and more significant, and coating shedding risk is caused to sharply increase.If not removed in time, turbine outer ring can be caused to become
Shape, coat inside form crackle and fall off.It falls off risk to reduce big thickness coatings, avoids the occurrence of coating chip off-falling and antiscour energy
Hypodynamic phenomenon need to eliminate residual stress in coating in time, reduce its deformation and form crackle tendency, can be in coating spraying
Destressing heat treatment is carried out after to certain thickness, makes coat inside that relaxation occur.
Specifically, turbine outer ring inner wall institute spray-on coating thickness often increases by 0.4~0.5mm, turbine outer ring is placed in vacuum
A destressing heat treatment is carried out in heat-treatment furnace, is higher than 10 in vacuum degree-2Pa, temperature are kept the temperature under conditions of being 550~750 DEG C
2~4h, then furnace cooling.
For ensure twice between spray-on coating effectively combine and go de-stress to be heat-treated after coating surface it is that may be present
Oxide skin and impurity need to carry out blasting treatment to the turbine outer ring surface through destressing heat treatment before carrying out secondary spraying.Two
Secondary blasted condition includes：Blasting pressure is 0.1~0.2MPa, and for sandblasting distance controlling in 100~300mm, the granularity of sand grains is 46
~60#, the nozzle axial direction of sand-blasting machine keep 60 °~90 ° of angle with turbine outer ring surface.
After destressing processing and surface second blasting treatment, overturn when turbine outer ring is sprayed relative to the last time
It is replaced in after 180 ° in low-voltage plasma spraying vacuum chamber, continues to be sprayed into according still further to aforementioned preheating and spraying parameter
Design thickness.
By the experimental study of inventor, if the overall thickness of coating is more than 1mm, a destressing heat treatment work need to be further added by
Sequence, and blasting treatment is made to coating according to above-mentioned secondary blasting craft parameter and continues to spray according still further to spraying process after overturning
It applies.
In spraying process, the spraying particle of molten condition is mainly thick with the bumps on turbine outer ring or depositing coating surface
The form of matte mechanical snap combines.As coating layer thickness increases, bond strength has the tendency that reduction.Pass through diffusion in vacuum heat
Processing, coating have different degrees of counterdiffusion with turbine outer ring surface each element, can form expansion of the thickness up to some tens of pm or so
Band is dissipated, the bond strength of coating and turbine outer ring can be effectively improved by being formed by micro- metallurgical binding；Meanwhile diffusion heat treatments are also
Can it is a degree of eliminate coating internal flaw, enhance the cohesive strength of coating.Therefore, coating spraying is to final thickness
Afterwards, turbine outer ring is placed in vacuum heat treatment furnace and is diffused heat treatment.
The method of diffusion heat treatments includes：It is higher than 10 in vacuum degree-2Pa, heating rate are 10~20 DEG C/min, temperature 950
4~10h is kept the temperature under conditions of~1100 DEG C.Then furnace cooling, or be filled with argon gas to 200~500mbar acceleration and be cooled to room
Temperature.
The feature and performance of the present invention are described in further detail with reference to embodiments.
Embodiment 1
A kind of big thickness high-temperature protection coating of turbine outer ring inner wall is present embodiments provided, is mainly made by following steps
It forms：
(1) by GH3536 superalloy turbine outer shroud degreasing degreasings, spray-coating surface is roughened using fused alumina zirconia sandblasting, grit size
For 24#, blasting pressure 0.45MPa, sandblasting distance is 200mm, and being blown off with compressed air may remaining sand grains or dust.
(2) turbine outer ring that sandblasting is roughened is put into fixture and is placed in low-voltage plasma spraying vacuum chamber, vacuumized
To 0.5mbar, then argon gas is backfilled to 40mbar, transferred arc electricity cleaning is carried out to turbine outer ring, plasma gun electric current is 600A,
Transfer arc current is 25A, argon gas 60L/min, hydrogen 2L/min, and away from for 300mm, spray gun movement speed is 500mm/s, turbine for spray
Outer shroud rotating speed is 60rpm.
(3) the pre-heat treatment is carried out under the conditions of non-powder feeding, vacuum chamber pressure is 70mbar, and plasma gun electric current is
600A, argon gas 60L/min, hydrogen 3L/min, away from for 300mm, spray gun movement speed is 500mm/s for spray, and turbine outer ring rotating speed is
60rpm。
(4) turbine outer ring starts to spray after being preheated to 500 DEG C, the aerosolization CoNiCrAlY using granularity at 5.5-38 μm
Powder, vacuum chamber pressure are 70mbar, and plasma gun electric current is 720A, argon gas 45L/min, hydrogen 8L/min, powder feeding speed
Rate is 30g/min, and away from for 290mm, spray gun movement speed is 50mm/s for spray, and turbine outer ring rotating speed is 300rpm, is sprayed into coating
Thickness 0.5mm.
(5) turbine outer ring is placed in vacuum heat treatment furnace and carries out destressing heat treatment, vacuum degree is better than 10-2Pa, with rate
15 DEG C/min is warming up to 650 DEG C, keeps the temperature 3h, furnace cooling.
(6) secondary blasting treatment, blasting pressure will be carried out with 46# fused alumina zirconias through destressing heat treatment turbine outer ring spray-coating surface
For 0.15MPa, sandblasting distance is 180mm, and remaining sand grains or dust are blown off with compressed air.
(7) turbine outer ring is placed in low-voltage plasma spraying vacuum chamber and overturns 180 ° when being sprayed relative to first time,
It is preheated and is sprayed according to technological parameter in (3) and (4) successively again, until coating layer thickness is 0.95mm.
(8) turbine outer ring is placed in vacuum heat treatment furnace and is diffused heat treatment, vacuum degree is better than 10-2Pa, with 15 DEG C/
Min rates are warming up to 980 DEG C, keep the temperature furnace cooling after 7h.
Embodiment 2
A kind of big thickness high-temperature protection coating of turbine outer ring inner wall is present embodiments provided, is mainly made by following steps
It forms：
(1) by GH4648 superalloy turbine outer shroud degreasing degreasings, spray-coating surface is roughened using Brown Alundum sandblasting, grit size
For 30#, blasting pressure 0.40MPa, sandblasting distance is 160mm, and being blown off with compressed air may remaining sand grains or dust.
(2) turbine outer ring that sandblasting is roughened is put into fixture and is placed in low-voltage plasma spraying vacuum chamber, vacuumized
To 0.5mbar, then argon gas is backfilled to 35mbar, transferred arc electricity cleaning is carried out to turbine outer ring, plasma gun electric current is 580A,
Transfer arc current is 28A, argon gas 62L/min, hydrogen 1L/min, and away from for 320mm, spray gun movement speed is 450mm/s, turbine for spray
Outer shroud rotating speed is 50rpm.
(3) the pre-heat treatment is carried out under the conditions of non-powder feeding, vacuum chamber pressure is 65mbar, and plasma gun electric current is
580A, argon gas 62L/min, hydrogen 2L/min, away from for 320mm, spray gun movement speed is 450mm/s for spray, and turbine outer ring rotating speed is
50rpm。
(4) turbine outer ring starts to spray after being preheated to 550 DEG C, the aerosolization CoNiCrAlY powder using granularity at 11-63 μm
End, vacuum chamber pressure are 70mbar, and plasma gun electric current is 710A, argon gas 48L/min, hydrogen 10L/min, powder feeding rate
For 40g/min, spray is away from for 300mm, and spray gun movement speed is 45mm/s, and turbine outer ring rotating speed is 280rpm, is sprayed into painting thickness
Spend 0.45mm.
(5) turbine outer ring is placed in vacuum heat treatment furnace and carries out destressing heat treatment, vacuum degree is better than 10-2Pa, with 12 DEG C/
Min rates are warming up to 600 DEG C, keep the temperature 4h, furnace cooling.
(6) secondary blasting treatment, blasting pressure will be carried out with 54# Brown Alundums through destressing heat treatment turbine outer ring spray-coating surface
For 0.12MPa, sandblasting distance is 150mm, and remaining sand grains or dust are blown off with compressed air.
(7) turbine outer ring is placed in low-voltage plasma spraying vacuum chamber and overturns 180 ° when being sprayed relative to first time,
It is preheated and is sprayed according to technological parameter in (3) and (4) successively again, until coating layer thickness is 0.90mm.
(8) turbine outer ring is placed in vacuum heat treatment furnace and is diffused heat treatment, vacuum degree is better than 10-2Pa, with 12 DEG C/
Min rates are warming up to 990 DEG C, keep the temperature 6h, furnace cooling.
Embodiment 3
A kind of big thickness high-temperature protection coating of turbine outer ring inner wall is present embodiments provided, is mainly made by following steps
It forms：
(1) by GH3625 superalloy turbine outer shroud degreasing degreasings, spray-coating surface is roughened using white fused alumina sandblasting, grit size
For 36#, blasting pressure 0.38MPa, sandblasting distance is 120mm, and being blown off with compressed air may remaining sand grains or dust.
(2) turbine outer ring that sandblasting is roughened is put into fixture and is placed in low-voltage plasma spraying vacuum chamber, vacuumized
To 0.5mbar, then argon gas is backfilled to 45mbar, transferred arc electricity cleaning is carried out to turbine outer ring, plasma gun electric current is 650A,
Transfer arc current is 30A, argon gas 65L/min, and away from for 340mm, spray gun movement speed is 550mm/s for spray, and turbine outer ring rotating speed is
70rpm。
(3) the pre-heat treatment is carried out under the conditions of non-powder feeding, vacuum chamber pressure is 75mbar, and plasma gun electric current is
650A, argon gas 65L/min, hydrogen 2L/min, away from for 340mm, spray gun movement speed is 550mm/s for spray, and turbine outer ring rotating speed is
70rpm。
(4) turbine outer ring starts to spray after being preheated to 600 DEG C, the aerosolization CoNiCrAlY powder using granularity at 15-45 μm
End, vacuum chamber pressure are 75mbar, and plasma gun electric current is 800A, argon gas 40L/min, hydrogen 5L/min, helium 10L/
Min, powder feeding rate 35g/min, away from for 280mm, spray gun movement speed is 60mm/s for spray, and turbine outer ring rotating speed is 320rpm,
It is sprayed into coating layer thickness 0.48mm.
(5) turbine outer ring is placed in vacuum heat treatment furnace and carries out destressing heat treatment, vacuum degree is better than 10-2Pa, with 18 DEG C/
Min rates are warming up to 750 DEG C, keep the temperature 2h, furnace cooling.
(6) secondary blasting treatment, blasting pressure will be carried out with 54# white fused aluminas through destressing heat treatment turbine outer ring spray-coating surface
For 0.18MPa, sandblasting distance is 220mm, and remaining sand grains or dust are blown off with compressed air.
(7) turbine outer ring is placed in low-voltage plasma spraying vacuum chamber and overturns 180 ° when being sprayed relative to first time,
It is preheated and is sprayed according to technological parameter in (3) and (4) successively again, until coating layer thickness is 0.95mm.
(8) after carrying out destressing heat treatment and sandblasting according to technological parameter in (5) and (6), turbine outer ring is placed in low pressure
180 ° are overturn when plasma spraying vacuum chamber and opposite second of spraying, is preheated according still further to technological parameter in (3) and (4)
And spraying, until coating layer thickness 1.30mm.
(9) turbine outer ring is placed in vacuum heat treatment furnace and is diffused heat treatment, vacuum degree is better than 10-2Pa, with 18 DEG C/
Min rates are warming up to 1070 DEG C, keep the temperature 4h, and room temperature is cooled to the furnace after filling argon gas to 300mabr into vacuum drying oven.
Embodiment 4
A kind of big thickness high-temperature protection coating of turbine outer ring inner wall is present embodiments provided, is mainly made by following steps
It forms：
(1) by K403 superalloy turbine outer shroud degreasing degreasings, spray-coating surface is roughened using Brown Alundum sandblasting, and grit size is
46#, blasting pressure 0.42MPa, sandblasting distance are 170mm, and being blown off with compressed air may remaining sand grains or dust.
(2) turbine outer ring that sandblasting is roughened is put into fixture and is placed in low-voltage plasma spraying vacuum chamber, vacuumized
To 0.5mbar, then argon gas is backfilled to 40mbar, transferred arc electricity cleaning is carried out to turbine outer ring, plasma gun electric current is 550A,
Transfer arc current is 32A, argon gas 58L/min, hydrogen 3L/min, and away from for 280mm, spray gun movement speed is 600mm/s, turbine for spray
Outer shroud rotating speed is 70rpm.
(3) the pre-heat treatment is carried out under the conditions of non-powder feeding, vacuum chamber pressure is 70mbar, and plasma gun electric current is
550A, argon gas 58L/min, hydrogen 3L/min, away from for 280mm, spray gun movement speed is 600mm/s for spray, and turbine outer ring rotating speed is
60rpm。
(4) turbine outer ring starts to spray after being preheated to 650 DEG C, the aerosolization CoNiCrAlY powder using granularity at 22-45 μm
End, vacuum chamber pressure are 70mbar, and plasma gun electric current is 750A, argon gas 50L/min, hydrogen 5L/min, helium 5L/
Min, powder feeding rate 35g/min, away from for 320mm, spray gun movement speed is 65mm/s for spray, and turbine outer ring rotating speed is 240rpm,
It is sprayed into coating layer thickness 0.45mm.
(5) turbine outer ring is placed in vacuum heat treatment furnace and carries out destressing heat treatment, vacuum degree is better than 10-2Pa, with 20 DEG C/
Min rates are warming up to 700 DEG C, keep the temperature 2h, furnace cooling.
(6) it will be handled with 60# Brown Alundums through destressing heat treatment turbine outer ring spray-coating surface, blasting pressure is
0.18MPa, sandblasting distance is 240mm, and remaining sand grains or dust are blown off with compressed air.
(7) turbine outer ring is placed in low-voltage plasma spraying vacuum chamber and overturns 180 ° when being sprayed relative to first time,
It is preheated and is sprayed according to technological parameter in (3) and (4) successively again, until coating layer thickness is 0.92mm.
(8) after carrying out destressing heat treatment and sandblasting according to technological parameter in (5) and (6), turbine outer ring is placed in low pressure
180 ° are overturn when plasma spraying vacuum chamber and opposite second of spraying, is preheated according still further to technological parameter in (3) and (4)
And spraying, until coating layer thickness 1.35mm.
(9) turbine outer ring is placed in vacuum heat treatment furnace and is diffused heat treatment, vacuum degree is better than 10-2Pa, with 20 DEG C/
Min rates are warming up to 1090 DEG C, keep the temperature 4h, and room temperature is cooled to the furnace after filling argon gas to 400mabr into vacuum drying oven.
Test example
High-temperature protection coating prepared by Examples 1 to 4 is chosen, under conditions of 1050 DEG C after constant temperature oxidation 200h, by HB
The high temperature oxidation resistance of 5258-2000 testing coatings.The result shows that reaching complete anti-oxidant rank.
Using temperature of the infrared radiation thermometer monitoring turbine outer ring in the cleaning of transferred arc electricity, preheating and spraying process, press
The bond strength of ASTM C633 testing coatings is applied by the microhardness of ASTM E384 testing coatings by ASTM E2109 tests
The porosity of layer.The oxygen content of coating is measured by GB/T 4698.7-2011.As a result such as following table：
1 characterization result of table
Binding test result is as it can be seen that the big thickness high-temperature protection coating thickness of turbine outer ring inner wall provided by the present invention is reachable
The bond strength of 0.8~1.5mm, coating and matrix>70MPa, porosity ＜ 1%, oxygen content<0.5%, hardness>300HV0.3.
1050 DEG C of constant temperature oxidation experiments are up to complete anti-oxidant rank.Prepared coating is well combined with turbine outer ring, and even tissue causes
Close, hardness is moderate, and high temperature oxidation resistance is excellent, and the military service that can meet the big thickness high-temperature protection coating of turbine outer ring inner wall is wanted
It asks.
Fig. 2 is the big thickness CoNiCrAlY high-temperature protection coating Cross Section Morphologies of turbine outer ring inner wall that embodiment 1 provides.It can
Know the coating uniform, compact structure, porosity is low.
Embodiments described above is a part of the embodiment of the present invention, instead of all the embodiments.The reality of the present invention
The detailed description for applying example is not intended to limit the range of claimed invention, but is merely representative of the selected implementation of the present invention
Example.Based on the embodiments of the present invention, those of ordinary skill in the art are obtained without creative efforts
Every other embodiment, shall fall within the protection scope of the present invention.
Claims (10)
1. a kind of big thickness high-temperature protection coating of turbine outer ring inner wall, which is characterized in that including superalloy turbine outer shroud and set
It is placed in the coating of the turbine outer ring inner wall, the material of the coating is CoNiCrAlY.
2. the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 1, which is characterized in that the coating
Thickness is 0.8~1.5mm.
3. a kind of preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall as claimed in claim 1 or 2, feature
It is, including：
The turbine outer ring inner-wall spraying Jing Guo preceding processing at least twice, between the adjacent spraying described twice, to apply
Layer carries out destressing heat treatment and secondary blasting treatment, and after the completion of the spraying, diffusion in vacuum heat treatment is carried out to the coating.
4. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3, which is characterized in that
The method of coating described in the turbine outer ring inner-wall spraying includes：
Vacuum chamber pressure is 65~80mbar, plasma gun electric current is 650~850A, argon flow amount is 40~55L/
Min, hydrogen flowing quantity are 4~11L/min, helium gas flow is 0~10L/min, powder feeding rate is 30~50g/min, spray gun movement
Under conditions of speed is 40~70mm/s, turbine outer ring rotating speed is 200~400rpm, sprayed using atomized powder.
5. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3, which is characterized in that
The coating layer thickness of the turbine outer ring inner-wall spraying by pre-treatment often increases by 0.4~0.5mm, is carried out to the coating primary
The destressing heat treatment and the secondary blasting treatment.
6. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3 or 5, feature exist
In the method for the destressing heat treatment includes：The turbine outer ring for being coated with the coating is placed in vacuum heat treatment furnace
It is interior, it is higher than 10 in vacuum degree-2Pa, temperature keep the temperature 2~4h, then furnace cooling under conditions of being 550~750 DEG C.
7. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3 or 5, feature exist
In the condition of the secondary blasting treatment includes：The granularity of sand grains is 46~60#, and blasting pressure is 0.1~0.2MPa, sandblasting
Distance is 100~300mm.
8. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3, which is characterized in that
The diffusion in vacuum heat-treating methods include：It is higher than 10 in vacuum degree-2Pa, heating rate are 10~20 DEG C/min, temperature 950
4~10h is kept the temperature under conditions of~1100 DEG C, then is cooled down.
9. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 3, which is characterized in that
The pre-treatment includes a blasting treatment, the cleaning of transferred arc electricity and the pre-heat treatment；
The method of transferred arc electricity cleaning includes：The turbine outer ring Jing Guo the blasting treatment is put into juxtaposition in fixture
In low-voltage plasma spraying vacuum chamber, it is evacuated to 0.5mbar, backfill argon gas is to 35~50mbar, in plasma gun
Electric current be 550~700A, transfer arc current be 20~40A, argon flow amount is 55~70L/min, hydrogen flowing quantity is 0~3L/
Min, spray away from for 250~350mm, plasma gun movement speed be 400~600mm/s, turbine outer ring rotating speed is 40~80rpm
Under conditions of, the inner wall of turbine outer ring coating surface to be painted is cleared up.
10. the preparation method of the big thickness high-temperature protection coating of turbine outer ring inner wall according to claim 9, feature exist
In the method for the pre-heat treatment includes：In non-powder feeding, vacuum chamber pressure be 65~80mbar, plasma gun electric current is
550~700A, argon flow amount are 55~70L/min, hydrogen flowing quantity be 0~5L/min, spray away from for 250~350mm, described etc. from
Under conditions of sub- spray gun movement speed is 400~600mm/s, turbine outer ring rotating speed is 40~80rpm, plasma flame flow pair is utilized
The turbine outer ring carries out the pre-heat treatment.
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| CN111519125A (en) * | 2020-05-28 | 2020-08-11 | 广东省新材料研究所 | Surface treatment method for outer ring of aircraft engine turbine and outer ring of aircraft engine turbine |
| CN113502446A (en) * | 2021-05-27 | 2021-10-15 | 中国航发南方工业有限公司 | Quick-turnover and quick-change type spraying protection clamp and spraying method |
| CN117947386A (en) * | 2024-03-26 | 2024-04-30 | 成都晨发泰达航空科技股份有限公司 | High-density EB-PVD metal coating and preparation method thereof |
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