CN112575296A - Turbine blade high-temperature protective coating and preparation method thereof - Google Patents
Turbine blade high-temperature protective coating and preparation method thereof Download PDFInfo
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- CN112575296A CN112575296A CN202011258186.2A CN202011258186A CN112575296A CN 112575296 A CN112575296 A CN 112575296A CN 202011258186 A CN202011258186 A CN 202011258186A CN 112575296 A CN112575296 A CN 112575296A
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
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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
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
- C23C10/08—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases only one element being diffused
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/02—Pretreatment of the material to be coated
- C23C14/028—Physical treatment to alter the texture of the substrate surface, e.g. grinding, polishing
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5846—Reactive treatment
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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
- C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
- C23C16/06—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of metallic material
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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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
- C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
- C23C28/022—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer with at least one MCrAlX layer
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- General Chemical & Material Sciences (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of protective coatings, and particularly relates to a high-temperature protective coating for a turbine blade and a preparation method thereof. The technical scheme of the invention is as follows: a high-temperature protective coating for turbine blades comprises an inner cavity aluminized coating and an outer surface MCrAlY aluminized coating, wherein M is Ni, Co or Ni + Co. According to the high-temperature protective coating for the turbine blade and the preparation method thereof, after vapor phase aluminizing treatment is carried out on the inner cavity of the blade, the air film hole is easy to clean, is not blocked and sintered, the infiltrated layer is 100% covered, and the maximum change of the thickness and the components is not more than 20%; the beta-phase coating is formed on the outer surface of the blade, so that the Al content in the MCrAlY coating is effectively improved, and the mechanical property of the coating is not influenced.
Description
Technical Field
The invention belongs to the technical field of protective coatings, and particularly relates to a high-temperature protective coating for a turbine blade and a preparation method thereof.
Background
The turbine blade is known as a pearl on a crown, has a severe service environment, and needs to have good thermal shock resistance, high-temperature corrosion resistance, high-heat alternation resistance and complex stress performance. In order to improve the temperature bearing capacity of the turbine blade, the inner cavity of the turbine blade adopts a complex cooling channel to realize air film cooling, and meanwhile, a protective coating is applied to the outer surface of the inner cavity of the turbine blade. With the rise of the temperature of gas before the turbine, the temperature of the inner cavity of the turbine blade of the advanced aeroengine reaches 900-950 ℃, meanwhile, the wall thickness of the air-cooled blade is thin, the geometric shape is complex, the oxidation/hot corrosion of the inner cavity and the generation of cracks are unpredictable, and the service life and the reliability of the blade are seriously influenced. The protective coating is applied to the surface of the inner cavity of the blade, so that the oxidation corrosion rate of the alloy of the blade matrix is reduced, and the method is an effective and feasible way for prolonging the service life of the hollow air-cooled blade. The solid powder method and the slurry injection method adopted at present can not thoroughly solve the problems of nonuniform inner cavity seepage layer, blockage of air film holes, difficult cleaning after seepage and the like, and seriously affect the quality of the seepage layer in the air film holes of the blades.
The outer surface of the turbine blade is typically coated with an aluminide diffusion coating and a MCrAlY (M ═ Ni, Co, or Ni + Co) cladding. The aluminide coating mainly comprises a beta phase with good oxidation resistance, but the components of the aluminide coating are not easy to control according to requirements, and the mechanical properties of the matrix alloy are greatly influenced by the coating. The MCrAlY (M is Ni, Co or Ni and Co) coating has the advantages that the components and the thickness can be controlled according to requirements, so that the corrosion resistance and the mechanical property are considered, and the characteristics of different use working conditions are met, therefore, the MCrAlY coating is widely researched and applied as a high-temperature protective coating material on the outer surface of the turbine blade or a bonding bottom layer material of a thermal barrier coating. The Al content of a typical MCrAlY coating is between 8 and 15 wt.%, the Cr content is between 15 and 22 wt.%, and the coating structure mainly comprises gamma andthe gamma 'phase is composed, and a part of beta-NiAl or beta-CoAl exists in a dispersed phase in the gamma' phase. The function of Al in the coating is to form Al at high temperature2O3The addition of Cr can improve the hot corrosion performance of the coating and reduce the generation of Al due to the' third element effect2O3Critical Al content required for selective oxidation of the film. The active element Y can promote Al2O3Nucleation and growth of the film, and the adhesion of the oxide film can be improved by utilizing a pinning effect, so that the oxidation resistance of the coating is improved, but serious grain boundary segregation can be caused by excessive Y addition, and the high temperature and mechanical properties of the coating can be reduced on the contrary, so that the addition amount is generally less than or equal to 1 wt.%.
The high-temperature protective coating mainly forms a layer of continuous compact Al on the surface2O3/Cr2O3The film provides protection for a matrix, and the content of Al, Cr and other elements in the coating is very important for the service life of the MCrAlY coating. Lee et al showed that the service life of the coating was mainly dependent on the thickness of the coating, the content of beta-NiAl in the coating and the oxidation rate of the coating. The high-temperature oxidation and hot corrosion service life of the MCrAlY coating can be prolonged by increasing the content of Al and Cr elements in the coating, but when the content of Al and Cr elements in the coating is increased to a certain degree, the brittleness of the coating is increased rapidly, cracks formed in the service process are expanded to a part matrix, and the service life and reliability of a blade are influenced. In addition, the direct preparation of high aluminum coatings has the problem of reduced target processability.
Disclosure of Invention
The invention provides a turbine blade high-temperature protective coating and a preparation method thereof, gas film holes are easy to clean, are not blocked and are not sintered after the gas-phase aluminizing treatment of the inner cavity of a blade, a permeated layer is 100 percent covered, and the maximum change of the thickness and the components is not more than 20 percent; the beta-phase coating is formed on the outer surface of the blade, so that the Al content in the MCrAlY coating is effectively improved, and the mechanical property of the coating is not influenced.
The technical scheme of the invention is as follows:
a high-temperature protective coating for turbine blades comprises an inner cavity aluminized coating and an outer surface MCrAlY aluminized coating, wherein M is Ni, Co or Ni + Co.
The preparation method of the turbine blade high-temperature protective coating comprises the following steps: 1) performing abrasive flow treatment on the inner cavity of the turbine blade to remove residues on the surface of the inner cavity; 2) carrying out wet sand blasting treatment on the outer surface of the turbine blade to activate the surface of the part; 3) preparing an MCrAlY bottom layer on the outer surface of the turbine blade by adopting a vacuum arc plating process; 4) and preparing aluminized layers on the MCrAlY bottom layers of the inner cavity of the turbine blade and the outer surface of the turbine blade by adopting a chemical vapor deposition process.
The invention has the beneficial effects that: the invention adopts vacuum arc plating MCrAlY coating and then aluminizing treatment to change the MCrAlY coating phase composition from gamma/gamma' phase to beta phase, and the coating can form continuous compact Al in the oxidation process2O3The oxide film has good oxidation and corrosion resistance. The invention carries out aluminizing treatment on the inner cavity of the blade, improves the high-temperature oxidation corrosion resistance of the inner cavity, and the gas film hole is easy to clean, free from blockage and sintering after the gas phase aluminizing treatment, the infiltrated layer is 100 percent covered, and the maximum change of the thickness and the components is not more than 20 percent. Aiming at the problem that the residues in the inner cavity influence the bonding force of the aluminized layer, the inner cavity is polished by abrasive particle flow.
Drawings
FIG. 1 shows the XRD phase analysis result of a turbine blade NiCrAlY coating;
FIG. 2 is an XRD phase analysis result of a coating after turbine blade NiCrAlY aluminizing;
FIG. 3 is a macroscopic view of samples of a superalloy substrate, a NiCrAlY coating, and a NiCrAlY aluminized coating;
FIG. 4 is a graph of the oxidation kinetics of superalloy substrate, NiCrAlY coating, and NiCrAlY aluminized coating samples oxidized at 1050 ℃ for 300 hours at constant temperature;
FIG. 5 is a photograph of a cross-section of a blade body coating after a turbine blade has been coated with a NiCrAlY coating and aluminized;
FIG. 6 is a photograph of a cross-section of the inner film hole coating after the turbine blade has been coated with a NiCrAlY coating and aluminized.
Detailed Description
A preparation method of a high-temperature protective coating of a turbine blade comprises the following steps:
1) the inner cavity of the turbine blade is treated by abrasive particle flow.
2) And carrying out wet sand blowing treatment on the surface of the blade, and carrying out ultrasonic cleaning, acetone solution immersion cleaning and drying. The wet sand blowing process parameters are as follows: the white corundum sand has the granularity of 180 meshes, the content of corundum sand is 20 percent, the wind pressure is 0.15MPa, and the sand blowing distance is 180 mm.
3) The surface of the blade is coated with a 30 μm NiCrAlY base layer by vacuum arc plating. The ion cleaning process parameters are as follows: the bias voltage U is 500V-700V, the arc current I is 70 +/-2A, and the duty ratio D is 25-45%. The deposition process parameters are as follows: the bias voltage U is 200V-275V, the arc current I is 70 +/-2A, and the duty ratio D is 10-30%.
4) And carrying out chemical vapor aluminizing treatment on the NiCrAlY bottom layer and the inner cavity of the blade.
As shown in FIG. 1, the NiCrAlY underlayer consists essentially of the γ/γ' phase; as shown in FIG. 2, the NiCrAlY substrate chemical vapor aluminized coating consists essentially of a beta phase; as shown in FIG. 4, aluminizing significantly improved the oxidation resistance of NiCrAlY, promoting continuous densification of Al2O3Forming an oxide film; as shown in fig. 5 and 6, the thickness of the inner and outer surface coating layers of the blade was uniform.
Claims (2)
1. A high-temperature protective coating for turbine blades is characterized by comprising an inner cavity aluminized coating and an outer surface MCrAlY aluminized coating, wherein M is Ni, Co or Ni + Co.
2. The method for preparing the turbine blade high-temperature protective coating according to claim 1, comprising the steps of: 1) performing abrasive flow treatment on the inner cavity of the turbine blade to remove residues on the surface of the inner cavity; 2) carrying out wet sand blasting treatment on the outer surface of the turbine blade to activate the surface of the part; 3) preparing an MCrAlY bottom layer on the outer surface of the turbine blade by adopting a vacuum arc plating process; 4) and preparing aluminized layers on the MCrAlY bottom layers of the inner cavity of the turbine blade and the outer surface of the turbine blade by adopting a chemical vapor deposition process.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011258186.2A CN112575296A (en) | 2020-11-12 | 2020-11-12 | Turbine blade high-temperature protective coating and preparation method thereof |
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| CN202011258186.2A CN112575296A (en) | 2020-11-12 | 2020-11-12 | Turbine blade high-temperature protective coating and preparation method thereof |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0578860A (en) * | 1991-09-20 | 1993-03-30 | Hitachi Ltd | Alloy-coated gas turbine blade and its manufacture |
| EP1380672A1 (en) * | 2002-07-09 | 2004-01-14 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP1411148A1 (en) * | 2002-10-15 | 2004-04-21 | ALSTOM Technology Ltd | Method of depositing a MCrALY-coating on an article and the coated article |
| US20060141283A1 (en) * | 2004-12-29 | 2006-06-29 | Honeywell International, Inc. | Low cost inovative diffused MCrAIY coatings |
| CN101310971A (en) * | 2007-05-25 | 2008-11-26 | 中国科学院金属研究所 | Ni-base superalloy complex gradient coating and preparation technique thereof |
| CN106756819A (en) * | 2016-09-30 | 2017-05-31 | 广东省新材料研究所 | A kind of MCrAlY high-temperature protection coatings preparation method |
| CN108048805A (en) * | 2017-12-08 | 2018-05-18 | 中国航发动力股份有限公司 | A kind of turbo blade composite coating and preparation method thereof |
| CN111570952A (en) * | 2020-05-09 | 2020-08-25 | 中国航发沈阳发动机研究所 | Air-cooled hollow blade air film hole inner wall sharp corner rounding device and method |
-
2020
- 2020-11-12 CN CN202011258186.2A patent/CN112575296A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0578860A (en) * | 1991-09-20 | 1993-03-30 | Hitachi Ltd | Alloy-coated gas turbine blade and its manufacture |
| EP1380672A1 (en) * | 2002-07-09 | 2004-01-14 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP1411148A1 (en) * | 2002-10-15 | 2004-04-21 | ALSTOM Technology Ltd | Method of depositing a MCrALY-coating on an article and the coated article |
| US20060141283A1 (en) * | 2004-12-29 | 2006-06-29 | Honeywell International, Inc. | Low cost inovative diffused MCrAIY coatings |
| CN101310971A (en) * | 2007-05-25 | 2008-11-26 | 中国科学院金属研究所 | Ni-base superalloy complex gradient coating and preparation technique thereof |
| CN106756819A (en) * | 2016-09-30 | 2017-05-31 | 广东省新材料研究所 | A kind of MCrAlY high-temperature protection coatings preparation method |
| CN108048805A (en) * | 2017-12-08 | 2018-05-18 | 中国航发动力股份有限公司 | A kind of turbo blade composite coating and preparation method thereof |
| CN111570952A (en) * | 2020-05-09 | 2020-08-25 | 中国航发沈阳发动机研究所 | Air-cooled hollow blade air film hole inner wall sharp corner rounding device and method |
Non-Patent Citations (1)
| Title |
|---|
| 王建录等: "《高温透平叶片精密加工与检测技术》", 31 December 2016, 西安交通大学出版社 * |
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Application publication date: 20210330 |