CN109371353A - A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process - Google Patents
A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process Download PDFInfo
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- CN109371353A CN109371353A CN201811423537.3A CN201811423537A CN109371353A CN 109371353 A CN109371353 A CN 109371353A CN 201811423537 A CN201811423537 A CN 201811423537A CN 109371353 A CN109371353 A CN 109371353A
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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
-
- 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
-
- 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
-
- 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
-
- 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
- C23C4/11—Oxides
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- 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 aero-engine technology field, in particular to a kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process.It from the inside to the outside successively include adhesive layer, transition zone and abradable layer coating；The adhesive layer uses SiC, and the transition zone uses Yb2SiO5, the abradable layer coating ZrO2.Y2O3Polyester.Coating of the invention is the resistance to 1200 DEG C of abradable seals that can be matched with SiC/SiC ceramic matric composite, it is heat-insulated both with compound coating, can solve mechanical damage caused by SiC/SiC ceramic matrix composite turbine component phase mutual friction and ceramic base avoided to answer material high-temperature oxydation and structure degradation equivalent damage problem.Plasma spraying technology has many advantages, such as that high-energy density, high efficiency, low cost and equipment investment are small, is the optimum process method of refractory ceramics coating material preparation.
Description
Technical field
The present invention relates to aero-engine technology field, in particular to a kind of ceramic base answers material turbine outer ring high temperature and obturages painting
Layer and its preparation process.
Background technique
Engine during the work time, under the collective effect of centrifugal force, aerodynamic force and expanded by heating, rotor it is all kinds of
Part and casing all can deformation occurs.Therefore, in design, manufacture and repair procedures, needing to apply on turbine outer ring surface can
Abrasive sealing coating controls gap structurally, prevents the turbo blade blade tip rotated in the operating condition and turbine outer ring phase
Mutual friction causes mechanical damage.Common high temperature sealing coating material is generally combined by metal material and nonmetallic materials,
But fail by the seal coating system of base phase of metal material vulnerable to high-temperature oxydation, 1000 are usually less than using temperature
℃.With the development of aero-engine, to the heat-resisting ability of high-temperature component, more stringent requirements are proposed.It is set in new engine
In meter, turbine outer ring part has selected SiC/SiC ceramic matric composite, and original Metal Substrate high temperature seal coating structural system exists
Cracked in use process, peeling phenomenon has been unable to satisfy hot environment requirement.Exploitation can be multiple with SiC/SiC ceramic base
Resistance to 1200 DEG C of abradable seals that condensation material matches, it is heat-insulated both with compound coating and technology of preparing, can solve SiC/
Mechanical damage caused by SiC ceramic based composites turbine part phase mutual friction simultaneously avoids ceramic base from answering material high-temperature oxydation and structure
Degeneration equivalent damage problem.Plasma spraying technology has high-energy density, high efficiency, low cost and equipment investment small etc. excellent
Point is the optimum process method of refractory ceramics coating material preparation.
Engine during the work time, under the collective effect of centrifugal force, aerodynamic force and expanded by heating, rotor it is all kinds of
Part and casing all can deformation occurs.Therefore, in design, manufacture and repair procedures, needing to apply on turbine outer ring surface can
Abrasive sealing coating controls gap structurally, prevents the turbo blade blade tip rotated in the operating condition and turbine outer ring phase
Mutual friction causes mechanical damage.Common high temperature sealing coating material is generally combined by metal material and nonmetallic materials,
But fail by the seal coating system of base phase of metal material vulnerable to high-temperature oxydation, 1000 are usually less than using temperature
℃.With the development of aero-engine, to the heat-resisting ability of high-temperature component, more stringent requirements are proposed.It is set in new engine
In meter, turbine outer ring part has selected SiC/SiC ceramic matric composite, and original Metal Substrate high temperature seal coating structural system exists
Cracked in use process, peeling phenomenon has been unable to satisfy hot environment requirement.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of ceramic base answer material turbine outer ring high temperature seal coating and its
Preparation process, which is the resistance to 1200 DEG C of abradable seals that can be matched with SiC/SiC ceramic matric composite, heat-insulated simultaneous
The compound coating of tool, can solve mechanical damage caused by SiC/SiC ceramic matrix composite turbine component phase mutual friction simultaneously
Ceramic base is avoided to answer material high-temperature oxydation and structure degradation equivalent damage problem.Plasma spraying technology has high-energy density, Gao Sheng
Efficiency, the advantages that low cost and equipment investment are small are produced, is the optimum process method of refractory ceramics coating material preparation.
Specific technical solution is as follows:
A kind of ceramic base answers material turbine outer ring high temperature seal coating, from the inside to the outside successively includes adhesive layer, transition zone and can
Wearing course coating；The adhesive layer uses SiC, and the transition zone uses Yb2SiO5, the abradable layer coating is that yttrium oxide is steady
Fixed zirconium oxide-polyester coatings.
A kind of ceramic base answers the preparation process of material turbine outer ring high temperature seal coating, and three kinds of coatings are all made of plasma spraying
Technique preparation, specifically comprises the following steps:
(1) it degreases
It is embathed, is degreased using alcohol；
(2) protection before spraying
Part non-spraying region is protected using protective glue band or fixture；
(3) plasma spraying SiC coating
Parameter are as follows: electric current 750A-850A, argon flow 50L/min-60L/min, hydrogen flowing quantity 5L/min-6L/
Min, powder feeding rate 20-30g/min, spray distance 100-110mm, spray angle are 75 ° -90 °；
(4) plasma spraying Yb2SiO5Coating
Parameter are as follows: electric current 650A-750A, argon flow 50L/min-60L/min, hydrogen flowing quantity 9L/min-10L/
Min, powder feeding rate 30-40g/min, spray distance 100-110mm, spray angle are 75 ° -90 °；
(5) zirconium oxide-polyester coatings of plasma spray stabilized with yttrium oxide
Parameter are as follows: electric current 550A-650A, argon flow 40L/min-50L/min, hydrogen flowing quantity 6L/min-9L/
Min, powder feeding rate 30-40g/min, spray distance 100-120mm, spray angle are 75 ° -90 °；
(6) it clears up
After spraying, protective glue band or disassembly shield jig are removed.
Zirconium oxide-polyester coatings of the stabilized with yttrium oxide are zirconium oxide-polybenzoate of stabilized with yttrium oxide.
Compared with prior art, the present invention has following advantageous effects:
The present invention is directed to aero-engine ceramic matrix composite turbine outer ring member, carries out high-temperature abradable seal coating
Structure design, ingredient design, composite-making process research, develop the high-temperature abrasive to match with outer ring basis material and seal
Tight coating meets the development demand of advanced aero engine.Novel abradable seal coating, which meets, has high-temperature stability, can
The operating temperature demand for meeting 1200 DEG C, does not undergo phase transition decomposition under high temperature action, will not fail.In the blade tip of rotor blade
When with obturaging material interaction, seal coating itself is worn and scraping, under the premise of blade injury degree is minimum, obtains
Minimum clearance under engine actual working state phase, promotes the thrust of engine, and reduces fuel consumption.With good knot
Intensity and ceramic matric composite Matrix Match and thermal-shock resistance are closed, it is excellent to guarantee that coating has during military service
Cracking resistance and spalling resistance.SiC ceramic based composites occur under high-temperature service environment with oxygen, the vapor in combustion gas
Reaction generates the substance for being easy to volatilize, and causes material weightless and ultimate failure.So the high temperature seal coating knot of this patent preparation
Structure system forms effective protection to matrix, avoids the high-temperature oxydation and structure degradation equivalent damage of matrix, solves exhaust gas corrosion and asks
Topic realizes the long-life in aero-engine and high reliability application.This renovation technique can be also used for aero-engine and
The high temperature protection of other industry ceramic matric composites has boundless market prospects.
Detailed description of the invention
Fig. 1 is the structural schematic diagram that ceramic base of the present invention answers material turbine outer ring high temperature seal coating.
Specific embodiment
The present invention is described in detail with specific embodiment below in conjunction with the accompanying drawings, but protection scope of the present invention is not by attached
Figure and embodiment are limited.
Embodiment 1
Step 1: to zero progress oil removing abatement processes, using alcohol wipe part spraying area, degreasing and sundries；
Step 2: the position for not needing spraying to part is protected, and is protected by the way of the masking of metal tooling；
Step 3: need spraying area to carry out plasma spraying coat of silicon carbide part, design parameter is electric current 750A,
Argon flow is 50L/min, hydrogen flowing quantity 5L/Min, powder feeding rate 20g/min, spray distance 110mm, spray angle
It is 90 °；
Step 4: need spraying area to carry out plasma spraying ytterbium silicate coating part, design parameter is electric current 650A,
Argon flow is 50L/min, hydrogen flowing quantity 9L/Min, powder feeding rate 30g/min, spray distance 110mm, spray angle
It is 85 °；
Step 5: needing spraying area to carry out zirconium oxide+polyester coatings of plasma spraying stabilized with yttrium oxide part, have
Body parameter be electric current 550A, argon flow 40L/min, hydrogen flowing quantity 6L/Min, powder feeding rate 30g/min, spraying away from
From for 110mm, spray angle is 90 °；
Step 6: after spraying, removing the protecting tool set-up in non-spraying region.
It is HR15Y80-90 that ceramic base prepared by embodiment 1, which answers material turbine outer ring high temperature seal coating hardness, and intensity meets
Technique requirement.
Embodiment 2
Step 1: to zero progress oil removing abatement processes, using alcohol wipe part spraying area, degreasing and sundries；
Step 2: the position for not needing spraying to part is protected, and is protected by the way of the masking of metal tooling；
Step 3: need spraying area to carry out plasma spraying coat of silicon carbide part, design parameter is electric current 850A,
Argon flow is 60L/min, hydrogen flowing quantity 6L/Min, powder feeding rate 30g/min, spray distance 100mm, spray angle
It is 75 °；
Step 4: need spraying area to carry out plasma spraying ytterbium silicate coating part, design parameter is electric current 750A,
Argon flow is 60L/min, hydrogen flowing quantity 10L/Min, powder feeding rate 40g/min, spray distance 100mm, angle of spray
Degree is 90 °；
Step 5: needing spraying area to carry out zirconium oxide+polyester coatings of plasma spraying stabilized with yttrium oxide part, have
Body parameter be electric current 650A, argon flow 50L/min, hydrogen flowing quantity 9L/Min, powder feeding rate 40g/min, spraying away from
From for 100mm, spray angle is 80 °；
Step 6: after spraying, removing the protecting tool set-up in non-spraying region.
Embodiment 3
Step 1: to zero progress oil removing abatement processes, using alcohol wipe part spraying area, degreasing and sundries；
Step 2: the position for not needing spraying to part is protected, and is protected by the way of the masking of metal tooling；
Step 3: need spraying area to carry out plasma spraying coat of silicon carbide part, design parameter is electric current 800A,
Argon flow is 55L/min, hydrogen flowing quantity 5.5L/Min, powder feeding rate 25g/min, spray distance 105mm, angle of spray
Degree is 80 °；
Step 4: need spraying area to carry out plasma spraying ytterbium silicate coating part, design parameter is electric current 700A,
Argon flow is 55L/min, hydrogen flowing quantity 9.5L/Min, powder feeding rate 35g/min, spray distance 105mm, angle of spray
Degree is 75 °；
Step 5: needing spraying area to carry out zirconium oxide+polyester coatings of plasma spraying stabilized with yttrium oxide part, have
Body parameter be electric current 600A, argon flow 45L/min, hydrogen flowing quantity 8L/Min, powder feeding rate 35g/min, spraying away from
From for 120mm, spray angle is 75 °；
Step 6: after spraying, removing the protecting tool set-up in non-spraying region.
Claims (3)
1. a kind of ceramic base answers material turbine outer ring high temperature seal coating, it is characterised in that: from the inside to the outside successively include adhesive layer, mistake
Cross layer and abradable layer coating；The adhesive layer uses SiC, and the transition zone uses Yb2SiO5, the abradable layer coating be
Zirconium oxide-polyester coatings of stabilized with yttrium oxide.
2. the preparation process that a kind of ceramic base answers material turbine outer ring high temperature seal coating, which is characterized in that three kinds of coatings are all made of
Plasma spray coating process preparation, specifically comprises the following steps:
(1) it degreases: being embathed using alcohol, degreased；
(2) protection before spraying: part non-spraying region is protected using protective glue band or fixture；
(3) plasma spraying SiC coating: technical parameter are as follows: electric current 750A-850A, argon flow 50L/min-60L/min,
Hydrogen flowing quantity is 5L/min-6L/min, powder feeding rate 20-30g/min, spray distance 100-110mm, and spray angle is
75°-90°；
(4) plasma spraying Yb2SiO5Coating: technical parameter are as follows: electric current 650A-750A, argon flow 50L/min-60L/
Min, hydrogen flowing quantity 9L/min-10L/min, powder feeding rate 30-40g/min, spray distance 100-110mm, angle of spray
Degree is 75 ° -90 °；
(5) zirconium oxide-polyester coatings of plasma spray stabilized with yttrium oxide: technical parameter are as follows: electric current 550A-650A, argon flow
For 40L/min-50L/min, hydrogen flowing quantity 6L/min-9L/min, powder feeding rate 30-40g/min, spray distance 100-
120mm, spray angle are 75 ° -90 °；
(6) it clears up: after spraying, removing protective glue band or disassembly shield jig.
3. ceramic base according to claim 1 answers material turbine outer ring high temperature seal coating, it is characterised in that: the yttrium oxide
Stable zirconium oxide-polyester coatings are zirconium oxide-polybenzoate of stabilized with yttrium oxide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811423537.3A CN109371353A (en) | 2018-11-27 | 2018-11-27 | A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811423537.3A CN109371353A (en) | 2018-11-27 | 2018-11-27 | A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110273122A (en) * | 2019-07-16 | 2019-09-24 | 中国航发北京航空材料研究院 | The preparation method of the outer adjustment sheet long-life heat insulating coat of composite polyimide material |
| CN111823377A (en) * | 2020-07-30 | 2020-10-27 | 固安浩瀚光电科技有限公司 | Post-firing deprotection device for semiconductor ceramic and application method thereof |
| CN112048696A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof |
| CN115677385A (en) * | 2022-10-25 | 2023-02-03 | 哈尔滨工业大学 | Preparation method of abradable composite coating with ceramic matrix composite surface capable of resisting temperature up to 1300 DEG C |
| CN116535243A (en) * | 2023-04-06 | 2023-08-04 | 上海大学 | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof |
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| CN101653998A (en) * | 2009-09-18 | 2010-02-24 | 武汉理工大学 | High-temperature abradable seal coating |
| CN101805212A (en) * | 2010-03-25 | 2010-08-18 | 西北工业大学 | Method for preparing carborundum-coke ytterbium silicate composite coating on surface of carbon/carbon composite material |
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| CN101653998A (en) * | 2009-09-18 | 2010-02-24 | 武汉理工大学 | High-temperature abradable seal coating |
| CN101805212A (en) * | 2010-03-25 | 2010-08-18 | 西北工业大学 | Method for preparing carborundum-coke ytterbium silicate composite coating on surface of carbon/carbon composite material |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110273122A (en) * | 2019-07-16 | 2019-09-24 | 中国航发北京航空材料研究院 | The preparation method of the outer adjustment sheet long-life heat insulating coat of composite polyimide material |
| CN110273122B (en) * | 2019-07-16 | 2021-08-06 | 中国航发北京航空材料研究院 | Preparation method of long-life heat-insulation coating of polyimide composite material outer adjusting sheet |
| CN111823377A (en) * | 2020-07-30 | 2020-10-27 | 固安浩瀚光电科技有限公司 | Post-firing deprotection device for semiconductor ceramic and application method thereof |
| CN111823377B (en) * | 2020-07-30 | 2021-12-07 | 固安浩瀚光电科技有限公司 | Post-firing deprotection device for semiconductor ceramic and application method thereof |
| CN112048696A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof |
| CN115677385A (en) * | 2022-10-25 | 2023-02-03 | 哈尔滨工业大学 | Preparation method of abradable composite coating with ceramic matrix composite surface capable of resisting temperature up to 1300 DEG C |
| CN115677385B (en) * | 2022-10-25 | 2023-09-08 | 哈尔滨工业大学 | Preparation method of abradable composite coating with surface temperature resistance reaching 1300 ℃ of ceramic matrix composite |
| CN116535243A (en) * | 2023-04-06 | 2023-08-04 | 上海大学 | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof |
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Application publication date: 20190222 |