CN107740024B - High-temperature abradable coating and preparation process thereof - Google Patents
High-temperature abradable coating and preparation process thereof Download PDFInfo
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- CN107740024B CN107740024B CN201710901064.2A CN201710901064A CN107740024B CN 107740024 B CN107740024 B CN 107740024B CN 201710901064 A CN201710901064 A CN 201710901064A CN 107740024 B CN107740024 B CN 107740024B
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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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame 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
- C23C4/18—After-treatment
Abstract
The invention discloses a high-temperature abradable coating and a preparation process thereof, MCrAlY alloy powder is sprayed to the surface of a substrate through supersonic flame spraying equipment to prepare the coating, the surface of the substrate is sprayed for many times, the deposition thickness of single spraying is less than or equal to 0.02mm, and the vacuum heat treatment is adopted to carry out stress relief and diffusion treatment on the coated coating every time when the coating is sprayed for 0.8-1.5 mm; the thickness of the coating obtained by spraying is more than or equal to 1.5 mm. The problems that in the prior art, a high-temperature abradable coating is poor in abradability, the coating is easy to fall off, the high-temperature stability is poor and the like are solved, and the sealing effect of the gas path of the high-pressure turbine is effectively improved.
Description
Technical Field
The invention belongs to the technical field of abradable coatings, and particularly relates to a high-temperature abradable coating and a preparation process thereof.
Background
The outer ring of the turbine of the aero-engine is in a working condition environment of high temperature, high speed opposite grinding and high speed air flow scouring, the air path sealing performance of the outer ring of the turbine and the rotor blades is improved, and the working efficiency of the turbine can be obviously improved. Turbine outer rings are typically made of high temperature alloy materials. The high-temperature alloy has good high-temperature strength, but has high-temperature hardness and poor abradability, and is easy to damage and wear a working blade when directly used, and the air tightness is poor. In addition, the high-temperature oxidation resistance of the high-temperature alloy is poor, and the high-temperature alloy is easy to ablate in the working process, so that the blade tip clearance of the turbine blade of the engine is enlarged, and the working efficiency of air flow is reduced.
The first method is to adopt an integral high-new material to replace the original high-temperature alloy material, but the integral high-new material is used, so that the cost is high, the processing difficulty is high, and the design and production period is long; the second is that the inner surface of the outer ring of the high-pressure turbine, namely the surface of the high-temperature alloy, is coated with a high-temperature abradable seal coating, and when the rotor blade is heated and extends under the action of centrifugal force, the blade scrapes the seal coating, so that the gas path sealing effect is achieved. The conclusion proves that the high-temperature abradable seal coating has an important effect on improving the working efficiency and reliability of the high-pressure turbine, the oil consumption can be reduced by 0.5-1% when the blade tip clearance of the high-pressure turbine of a typical engine is reduced by 0.13-0.25 mm, and the efficiency of the engine can be improved by about 2%; the high-temperature sealing coating which can be worn, oxidized and ablated at high temperature and scour prevention is coated on the outer ring of the turbine, so that the gas flow loss can be obviously reduced, the heat efficiency of the engine is improved, and the high-temperature sealing coating has the characteristics of low cost, simple processing technology and short production period.
However, with the continuous improvement of the requirements on service life, reliability and economy in the development process of the aircraft engine, the rotating speed and temperature of the engine are multiplied, the working condition environment of a turbine part is further severe, and uncertain factors caused by engine surge and the like cause the outer ring block to bear the worse working condition environments such as high temperature, high speed airflow scouring, high speed abrasion, high alternating load and the like. The original high-temperature abradable seal coating has low bonding strength with a substrate, easy chipping and peeling of the coating, poor thermal stability and high-temperature abradability, and can not meet the use requirements of advanced aeroengines.
At present, the MCrAlY/polyphenyl ester coating is mainly prepared by atmospheric plasma in domestic high-temperature sealing coatings. Because of the large pores, the high-temperature sealing coating invented by Beijing aviation manufacturing engineering institute (patent number: 201410616508.4) is easy to be oxidized by oxygen and MCrAlY under high-temperature environment to generate Al2O3、Cr2O3The oxide phase with high hardness and brittleness is equal, so that the hardness of the coating is improved, the blade tip of a turbine rotor blade which is abraded with the oxide phase in the using process of an engine is seriously abraded, the abradability of the coating is lost, the coating has a complex structure, the cracking probability of the coating is high, and the batch production is difficult.
Therefore, how to improve the high-temperature abradability, the oxidation ablation resistance, the bonding strength, the thermal shock resistance and the service life of the high-temperature abradable seal coating is a technical problem to be solved.
Disclosure of Invention
The invention aims to provide a high-temperature abradable coating and a preparation process thereof, and solves the problems of poor sealing effect and short service life of the high-temperature abradable coating in the prior art. The invention can be used for sealing the outer ring gas path of an aircraft engine and a ground gas high-pressure turbine, has the characteristics of oxidation resistance, high temperature, low hardness, abrasion resistance, high temperature stability, thermal shock resistance and high binding force, can reach the working temperature of more than 1100 ℃, and can greatly improve the service life of a coating and the sealing effect.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention provides a preparation process of a high-temperature abradable coating, which adopts MCrAlY alloy powder, wherein M in the MCrAlY alloy powder is metal Ni and/or metal Co; spraying MCrAlY alloy powder to the surface of a substrate through supersonic flame spraying equipment to prepare a coating; spraying the surface of the matrix for multiple times, wherein the deposition thickness of single spraying is less than or equal to 0.02mm, and performing stress relief and diffusion treatment on the sprayed coating by adopting vacuum heat treatment every time the spraying is 0.8-1.5 mm; the thickness of the coating obtained by spraying is more than or equal to 1.5 mm; and then grinding and/or turning the coating to enable the thickness of the coating to meet the requirement of the final size of the workpiece.
Furthermore, the invention is characterized in that:
the vacuum heat treatment comprises the following steps: under the vacuum degree of less than or equal to 6.65 multiplied by 10-2pa, keeping the temperature of the coated coating at 950-1100 ℃ for 4-6 h, and then slowly cooling to below 500 ℃.
The supersonic flame spraying equipment adopts kerosene and oxygen as combustion spraying gas, wherein the flow rate of the kerosene is 4 GPH-6 GPH, and the flow rate of the oxygen is 1700 SCFH-2000 SCFH; or hydrogen and oxygen as combustion spray gases.
Adopting nitrogen as carrier gas, wherein the flow rate of the nitrogen is 20 SCFH-30 SCFH; the powder feeding rate is 20 g/min-40 g/min, and the spraying distance is 300 mm-450 mm.
The grain size of the MCrAlY alloy powder is between-50 and +15 mu m.
Before spraying the surface of the substrate, the surface of the substrate is degreased and roughened, so that the roughness of the surface of the substrate is larger than Ra 5.0 mu m. Preferably, 20# alumina sand is used as a working medium, and the wind pressure is 0.1MPa to 0.3 MPa.
Before the surface of the substrate is sprayed, the area outside the part needing spraying is shielded and protected.
The base body to be sprayed is a high-temperature alloy high-pressure turbine outer ring, and the high-temperature alloy is isometric crystal casting high-temperature alloy or single crystal high-temperature alloy.
The invention also provides a high-temperature abradable coating prepared by the preparation process of any one of claims 1-7.
Furthermore, the invention is characterized in that:
the coating is of a single-layer structure.
The coating and the surface of the substrate are metallurgically bonded, the porosity of the coating structure is lower than 1%, the oxygen content is lower than 5%, and the bonding strength of the coating is higher than 60 MPa.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention relates to a preparation process of a high-temperature abradable coating, which is characterized in that MCrAlY alloy powder is sprayed to the surface of a substrate through supersonic flame spraying equipment to prepare the coating, the surface of the substrate is sprayed for multiple times, the deposition thickness of single spraying is less than or equal to 0.02mm, and the coating which is coated is subjected to stress removal and diffusion treatment by vacuum heat treatment every time the coating is sprayed for 0.8-1.5 mm; the thickness of the coating obtained by spraying is more than or equal to 1.5 mm. The metallurgical bonding of the high-temperature abradable coating and the matrix can be realized by using the method, the porosity of the prepared coating tissue is lower than 1%, the oxygen content is lower than 5%, the bonding strength is greater than 60MPa, the high-temperature hardness HR45Y of the coating at 1000 ℃ is less than or equal to 70, the water-cooling thermal shock resistance is greater than 100 times, the thermal stability at 1000 ℃ is good, the hardness change is not large, the coating prepared by adopting the process has the characteristics of oxidation resistance, low hardness at high temperature, abradability, good high-temperature stability, thermal shock resistance and high bonding strength, the working temperature can reach 1100 ℃, the abrasion of the turbine rotor blade can be obviously reduced, the abradability, the reliability and the service life of the coating are improved, the service life of the turbine rotor blade is obviously prolonged, the maintenance cost of an engine is obviously reduced.
The high-temperature abradable coating has a single-layer structure, the thickness of the high-temperature abradable coating is larger than or equal to 1.5mm, and the material of the high-temperature abradable coating is MCrAlY alloy powder. The high-temperature abradable coating can be applied to sealing of an outer ring gas path of a high-pressure turbine of an aeroengine and a gas turbine, metallurgical bonding between the high-temperature abradable coating and a substrate is realized, the porosity of the coating tissue is lower than 1%, the oxygen content is lower than 5%, the bonding strength is higher than 60MPa, the 1000 ℃ high-temperature hardness HR45Y of the coating is less than or equal to 70, the water-cooling thermal shock resistance is higher than 100 times, the 1000 ℃ thermal stability is good, the hardness change is not large, the high-temperature abradable coating has the characteristics of oxidation resistance, low high-temperature hardness, abradability, high-temperature stability, thermal shock resistance and high bonding strength, the working temperature can reach 1100 ℃, the abrasion of turbine rotor blades can be obviously reduced, the abradability, the reliability and the service life of the coating are improved, the.
Drawings
FIG. 1 is a block diagram of the high temperature abradable coating provided by the present invention.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
the invention provides a preparation process of a high-temperature abradable coating, which adopts MCrAlY alloy powder, wherein M in the MCrAlY alloy powder is metal Ni and/or metal Co; spraying MCrAlY alloy powder to the surface of a substrate through supersonic flame spraying equipment to prepare a coating; spraying the surface of the matrix for multiple times, wherein the deposition thickness of single spraying is less than or equal to 0.02mm, and performing stress relief and diffusion treatment on the sprayed coating by adopting vacuum heat treatment every time the spraying is 0.8-1.5 mm; the thickness of the coating obtained by spraying is more than or equal to 1.5 mm; and then grinding and/or turning the coating to enable the thickness of the coating to meet the requirement of the final size of the workpiece.
In the preparation process of the high-temperature abradable coating, the vacuum heat treatment is: under the vacuum degree of less than or equal to 6.65 multiplied by 10-2pa, keeping the temperature of the coated coating at 950-1100 ℃ for 4-6 h, and then slowly cooling to below 500 ℃.
In the preparation process of the high-temperature abradable coating, the supersonic flame spraying equipment adopts kerosene and oxygen as combustion spraying gas, wherein the flow rate of the kerosene is 4 GPH-6 GPH, and the flow rate of the oxygen is 1700 SCFH-2000 SCFH; hydrogen and oxygen may also be used as combustion spray gases.
Adopting nitrogen as carrier gas, wherein the flow rate of the nitrogen is 20 SCFH-30 SCFH; the powder feeding rate is 20 g/min-40 g/min, and the spraying distance is 300 mm-450 mm.
In the preparation process of the high-temperature abradable coating, the particle size range of the MCrAlY alloy powder is-50 mu m to +15 mu m.
In the preparation process of the high-temperature abradable coating, before the surface of the matrix is sprayed, the surface of the matrix is degreased and roughened, so that the roughness of the surface of the matrix is larger than Ra 5.0 mu m.
In the preparation process of the high-temperature abradable coating, before the surface of the matrix is sprayed, the area except the part needing to be sprayed is shielded and protected.
In the preparation process of the high-temperature abradable coating, the matrix to be sprayed is a high-temperature alloy high-pressure turbine outer ring, and the high-temperature alloy is isometric crystal casting high-temperature alloy or single crystal high-temperature alloy.
In the preparation process of the high-temperature abradable coating, metallurgical bonding is realized between the coating and a substrate, the porosity of the coating tissue is lower than 1%, the oxygen content is lower than 5%, the bonding strength is greater than 60MPa, the 1000 ℃ high-temperature hardness HR45Y of the coating is less than or equal to 70, the water-cooling thermal shock resistance is greater than 100 times, and the 1000 ℃ thermal stability is good.
Referring to fig. 1, the present invention also provides a high temperature abradable coating made by the process of any one of claims 1-7.
The high-temperature abradable coating is of a single-layer structure, and the thickness of the high-temperature abradable coating is larger than or equal to 1.5 mm.
The high-temperature abradable coating is metallurgically bonded with the surface of the substrate, the porosity of the coating structure is lower than 1%, the oxygen content is lower than 5%, and the bonding strength of the coating is greater than 60 MPa.
Example 1:
in the embodiment, supersonic flame spraying equipment is adopted, the base material is a K465 high-temperature alloy base high-pressure turbine outer ring, and the CoNiCrAlY high-temperature abradable coating is prepared on the high-pressure turbine outer ring, and the method specifically comprises the following steps:
the sprayed surface of the part is cleaned by acetone or gasoline, and then the non-sprayed surface is protected by a thermal spraying glue coating belt.
Carrying out sand blasting treatment on the spraying surface of the outer ring of the high-pressure turbine by using clean and dry 20-mesh alumina sand, wherein the wind pressure is 0.4MPa, the roughness of the surface of the treated matrix is 7 mu m, and then removing the protective adhesive tape.
Preparing a high-temperature abradable coating on the surface of the part subjected to sand blasting treatment by using supersonic flame spraying equipment, wherein CoNiCrAlY alloy powder is adopted as powder, and the CoNiCrAlY alloy powder comprises the following components by taking the mass of the CoNiCrAlY alloy powder as 100 percent: 32 wt% Ni, 21 wt% Cr, 8 wt% Al, 0.5 wt% Y, and the balance Co. The particle size range is-38 mu m- +10 mu m. And carrying out vacuum heat treatment on the coating every time the coating is sprayed for 0.8mm, wherein the total thickness of the coating is 2.4mm, and finally ensuring the final size of the part through grinding and turning.
The technological parameters of the supersonic flame spraying are as follows: kerosene and oxygen are used as combustion spraying gas, the oxygen flow is 1900SCFH, and the kerosene flow is 4.5 GPH; the nitrogen is used as carrier gas, the flow rate of the nitrogen is 25SCFH, the powder feeding rate is 30g/min, the spraying distance is 350mm, and the single-pass deposition thickness is 0.01 mm.
The vacuum heat treatment comprises the following specific processes: placing the substrate and the coated coating layer in a vacuum heat treatment furnace with a vacuum degree of 3X 10-2pa, heating to 1100 ℃ along with the furnace, keeping the temperature for 6h, slowly cooling to below 500 ℃ along with the furnace, closing the heating device, and cooling to room temperature along with the furnace.
Example 2:
the invention adopts supersonic flame spraying to prepare NiCrAlY high-temperature abradable coating, and the base material is DD5 single crystal high-temperature alloy. The method specifically comprises the following steps:
cleaning the surface to be sprayed with acetone or gasoline, roughening the substrate by laser, wherein the roughness of the surface of the treated substrate is 6 microns, preparing a high-temperature abradable coating on the surface of the roughened DD5 single crystal substrate by supersonic flame spraying equipment, wherein NiCrAlY alloy powder is adopted as powder, and the NiCrAlY alloy powder comprises the following components in percentage by mass based on 100 percent of the NiCrAlY alloy powder: 22 wt% of Cr, 10 wt% of Al, 1.0 wt% of Y and the balance of Ni, wherein the granularity of the alloy powder is-45 mu m to +15 mu m. The coating is subjected to vacuum heat treatment every 1.0mm of spraying, and the total thickness of the coating is 2.0 mm.
The technological parameters of the supersonic flame spraying are as follows: adopting kerosene and oxygen as combustion spraying gas, wherein the flow rate of the oxygen is 1850SCFH, and the flow rate of the kerosene is 4 GPH; nitrogen is used as carrier gas, the flow rate of the nitrogen is 20SCFH, the powder feeding rate is 25g/min, and the spraying distance is 320 mm.
The vacuum heat treatment parameter is 1 × 10-2pa, raising the temperature to 1000 ℃ with the furnace, keeping the temperature for 4h, slowly cooling with the furnace to below 500 ℃, closing the heating device, and cooling with the furnace to room temperature.
Example 3:
in the embodiment, the NiCoCrAlY high-temperature sealing coating is prepared by supersonic flame spraying, the base material is K477 high-temperature alloy, and the method specifically comprises the following steps:
the surface to be sprayed is cleaned by acetone, and then the non-spraying surface is protected by a hot spraying glue coating belt. The sprayed surface is subjected to sand blasting treatment by 20-mesh alumina sand which is cleaned and dried, the wind pressure is 0.2MPa, and the surface roughness of the treated matrix is 6 mu m. Preparing a high-temperature abradable coating on the roughened surface by supersonic flame spraying equipment, wherein NiCoCrAlY alloy powder is adopted, and the NiCoCrAlY alloy powder comprises the following components by taking the mass of the NiCoCrAlY alloy powder as 100 percent: 20 wt% of Co, 21 wt% of Cr, 11 wt% of Al, 0.8 wt% of Y and the balance of Ni; the particle size range is-45 mu m- +15 mu m. The coating is subjected to vacuum heat treatment every 1.2mm of spraying, and the total thickness of the coating is 2.2 mm.
The technological parameters of the supersonic flame spraying are as follows: kerosene and oxygen are used as combustion spraying gas, the flow rate of the oxygen is 1950SCFH, the flow rate of the kerosene is 5.1GPH, nitrogen is used as carrier gas, the flow rate of the nitrogen is 23SCFH, the powder feeding rate is 30g/min, and the spraying distance is 340 mm. The thickness of the single-pass deposition is 0.01 mm.
The vacuum heat treatment parameter is vacuum degree of 9 × 10-3pa, heating to 1050 ℃ along with the furnace, preserving heat for 5 hours, slowly cooling to below 500 ℃ along with the furnace, closing the heating device, and cooling to room temperature along with the furnace.
The high-temperature abradable coating and the preparation method thereof can be applied to sealing of an outer ring gas path of a high-pressure turbine of an aeroengine and a gas turbine, metallurgical bonding of the high-temperature abradable coating and a substrate is realized, the porosity of the coating tissue is lower than 1%, the oxygen content is lower than 5%, the bonding strength is greater than 60MPa, the 1000 ℃ high-temperature hardness HR45Y of the coating is less than or equal to 70, the water-cooling thermal shock resistance is greater than 100 times, the 1000 ℃ thermal stability is good, the hardness change is not large, the high-temperature abradable coating has the characteristics of oxidation resistance, low high-temperature hardness, abradability, high-temperature stability, thermal shock resistance and high bonding strength, the working temperature can reach 1100 ℃, the abrasion of turbine rotor blades can be obviously reduced, the abradability, the reliability and the service life of the coating are improved, the service life of the turbine.
Claims (10)
1. The preparation process of the high-temperature abradable coating is characterized in that MCrAlY alloy powder is adopted, and M in the MCrAlY alloy powder is metal Ni and/or metal Co; spraying MCrAlY alloy powder to the surface of a substrate through supersonic flame spraying equipment to prepare a coating; spraying the surface of the matrix for multiple times, wherein the deposition thickness of single spraying is less than or equal to 0.02mm, and performing stress relief and diffusion treatment on the sprayed coating by adopting vacuum heat treatment every time the spraying is 0.8-1.5 mm; the thickness of the coating obtained by spraying is more than or equal to 1.5 mm; and then grinding and/or turning the coating to enable the thickness of the coating to meet the requirement of the final size of the workpiece.
2. The process for preparing a high temperature abradable coating as claimed in claim 1, wherein the vacuum heat treatment is: under the vacuum degree of less than or equal to 6.65 multiplied by 10-2pa under vacuum, coating the coated layer on the substrateKeeping the temperature at 950-1100 ℃ for 4-6 h, and then slowly cooling to below 500 ℃.
3. The process for preparing a high-temperature abradable coating according to claim 1, wherein the supersonic flame spraying apparatus uses kerosene and oxygen as combustion spraying gas, wherein the kerosene flow rate is 4-6 GPH, and the oxygen flow rate is 1700-2000 SCFH; or hydrogen and oxygen are used as combustion spraying gas;
adopting nitrogen as carrier gas, wherein the flow rate of the nitrogen is 20 SCFH-30 SCFH; the powder feeding rate is 20 g/min-40 g/min, and the spraying distance is 300 mm-450 mm.
4. The process for preparing a high-temperature abradable coating as claimed in claim 1, wherein the grain size range of the MCrAlY alloy powder is-50 μm to +15 μm.
5. The process for preparing a high-temperature abradable coating as claimed in claim 1, wherein the substrate surface is degreased and roughened to a surface roughness of greater than Ra 5.0 μm before being sprayed.
6. The process for preparing a high-temperature abradable coating as claimed in claim 1, wherein the substrate surface is masked and protected in areas other than the areas to be painted before painting.
7. The process for preparing a high-temperature abradable coating as claimed in claim 1, wherein the substrate to be sprayed is a high-temperature alloy high-pressure turbine outer ring, and the high-temperature alloy is an equiaxed cast high-temperature alloy or a single-crystal high-temperature alloy.
8. A high-temperature abradable coating obtained by the process of any one of claims 1 to 7.
9. The high temperature abradable coating of claim 8, wherein the coating is a single layer structure.
10. The high temperature abradable coating of claim 8, wherein the coating metallurgically bonds to the substrate surface, the coating has a porosity of less than 1%, an oxygen content of less than 5%, and a coating bond strength of greater than 60 MPa.
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| CN108179371A (en) * | 2017-12-25 | 2018-06-19 | 中国航发动力股份有限公司 | A kind of high-temperature abradable seal coating and preparation method thereof |
| CN108642430A (en) * | 2018-05-16 | 2018-10-12 | 安徽三环水泵有限责任公司 | A kind of process of surface treatment of slush pump pump shaft |
| CN108716479A (en) * | 2018-05-16 | 2018-10-30 | 安徽三环水泵有限责任公司 | A kind of wear-resisting slush pump pump shaft and preparation method thereof |
| CN108642435B (en) * | 2018-08-07 | 2020-10-16 | 广东省新材料研究所 | Large-thickness high-temperature protective coating for inner wall of outer ring of turbine and preparation method of large-thickness high-temperature protective coating |
| CN109227973B (en) * | 2018-08-20 | 2020-09-29 | 杨燕军 | Aluminum-based diamond composite ultra-high hardness scribing cutter and manufacturing method thereof |
| CN115287575A (en) * | 2022-07-21 | 2022-11-04 | 中国航发成都发动机有限公司 | Method for spraying high-bonding-strength coating by supersonic flame |
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| EP1076727B1 (en) * | 1998-02-28 | 2005-06-01 | General Electric Company | Multilayer bond coat for a thermal barrier coating system and process therefor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1076727B1 (en) * | 1998-02-28 | 2005-06-01 | General Electric Company | Multilayer bond coat for a thermal barrier coating system and process therefor |
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| 几种先进涂层;白;《航空材料》;19790411;第47页 * |
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