CN105369202A - Method for preparing thermal barrier coating on heavy gas turbine blade - Google Patents

Method for preparing thermal barrier coating on heavy gas turbine blade Download PDF

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Publication number
CN105369202A
CN105369202A CN201510810339.2A CN201510810339A CN105369202A CN 105369202 A CN105369202 A CN 105369202A CN 201510810339 A CN201510810339 A CN 201510810339A CN 105369202 A CN105369202 A CN 105369202A
Authority
CN
China
Prior art keywords
turbine blade
cocraly
gas turbine
heavy gas
thermal barrier
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201510810339.2A
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Chinese (zh)
Inventor
张鹏
王璐
程玉贤
张春刚
王博
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Liming Aero Engine Group Co Ltd
Original Assignee
Shenyang Liming Aero Engine Group Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shenyang Liming Aero Engine Group Co Ltd filed Critical Shenyang Liming Aero Engine Group Co Ltd
Priority to CN201510810339.2A priority Critical patent/CN105369202A/en
Publication of CN105369202A publication Critical patent/CN105369202A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • C23C14/28—Vacuum evaporation by wave energy or particle radiation
    • C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
    • 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
    • C23C14/024—Deposition of sublayers, e.g. to promote adhesion of the coating
    • C23C14/025—Metallic sublayers
    • 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
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention relates to preparing methods for coatings, in particular to a method for preparing a thermal barrier coating on a heavy gas turbine blade. The method comprises the following steps that firstly, a CoCrAlY bonding layer is prepared on the heavy gas turbine blade through an electron beam physical vapor deposition (EB-PVD) technology and then is subjected to vacuum diffusion treatment; secondly, the surface of the CoCrAlY bonding layer is subjected to shot blasting by universal shot blasting equipment through glass beads; thirdly, the heavy gas turbine blade with the CoCrAlY bonding layer is subjected to stress relieving thermal treatment; and fourthly, a yttria stabilized zirconia (YSZ) surface layer is prepared on the heavy gas turbine blade with the CoCrAlY bonding layer by the EB-PVD technology. According to the method for preparing the thermal barrier coating on the heavy gas turbine blade, the problem that the columnar structure of a ceramic surface layer in the thermal barrier coating on the surface of a heavy gas turbine blade is incomplete is solved, and the prepared coating is good in matching; accordingly, the application environment temperature condition of the blade can be effectively improved, and the service life of the blade can be effectively prolonged.

Description

A kind of preparation method of heavy combustion engine thermal barrier coating of turbine blade
Technical field
The present invention relates to a kind of preparation method of coating, be specifically related to a kind of preparation method of heavy combustion engine thermal barrier coating of turbine blade.
Background technology
, all there is ZrO high-temperature unit of aircraft engine work area 2y 2o 3/ MCrAlY system thermal barrier coating, to improve component use temperature.Current domestic thermal barrier coating adopts supersonic spray coating tack coat mostly, and the processing method preparation of plasma spraying surface layer, Bulk coat cold-hot alternation ability is weak.Existing electro beam physics vapour deposition (EB-PVD) technology part is used for the preparation of aero engine turbine blades thermal barrier coating, but not yet on the turbine blade of restriking that volume is relatively large, carry out thermal barrier coating preparation, and frequent inclusion cluster shape structure in the columnar structure of the YSZ surface layer of preparation, have a strong impact on coating thermal shock resistance.
Summary of the invention
The invention provides a kind of preparation method of heavy combustion engine thermal barrier coating of turbine blade, solve the incomplete problem of ceramic topcoats columnar structure in heavy combustion engine turbine blade surface thermal barrier coating, preparation coating coupling is good, can effectively improve blade applications ambient temperature conditions and life-span.
The present invention is a kind of preparation method of heavy combustion engine thermal barrier coating of turbine blade, comprises the steps:
One, utilize EB-PVD technology to prepare CoCrAlY tack coat on heavy combustion engine turbine blade, diffusion in vacuum process is carried out to described CoCrAlY tack coat;
Two, to the surface of CoCrAlY tack coat, use general blaster, application glass ball carries out shot peening;
Three, hidden lino removal is carried out to the heavy combustion engine turbine blade with CoCrAlY tack coat;
Four, EB-PVD technology is utilized to prepare YSZ surface layer with on the heavy combustion engine turbine blade of CoCrAlY tack coat.
The preparation method of described heavy combustion engine thermal barrier coating of turbine blade, wherein said hidden lino removal, temperature 1050 DEG C, time 2h.
Beneficial effect of the present invention is: application machine shot peening method of the present invention, eliminates tie layer surface chaotic configuration to the impact of physical vapor deposition YSZ surface layer columnar growth, improves coating thermal shock resistance; Both reach the good object that to bond with YSZ surface layer, follow-up YSZ surface layer deposited stabilizer columnar growth can have been realized again, eliminate the cluster-shaped structure be mingled with in the columnar structure of YSZ surface layer.Thermal barrier coating prepared by the present invention is columnar structure, and thermal boundary effect and cold-and-heat resistent alternation ability all have and significantly improve, and turbine blade coating of restriking is heat insulation reaches 60 DEG C, and a life-span of blade extends to 3000h from 1200h.
Accompanying drawing explanation
Fig. 1 is the columnar structure YSZ surface layer electronic scanning figure that method of the present invention is prepared;
Fig. 2 be prior art containing cluster-shaped structure YSZ surface layer electronic scanning figure.
Embodiment
A preparation method for heavy combustion engine thermal barrier coating of turbine blade, comprises the steps:
One, utilize EB-PVD technology to prepare CoCrAlY tack coat on heavy combustion engine turbine blade, diffusion in vacuum process is carried out to described CoCrAlY tack coat;
Two, to the surface of CoCrAlY tack coat, use general blaster, application glass ball carries out shot peening;
Three, hidden lino removal is carried out to the heavy combustion engine turbine blade with CoCrAlY tack coat, temperature 1050 DEG C, time 2h;
Four, EB-PVD technology is utilized to prepare YSZ surface layer with on the heavy combustion engine turbine blade of CoCrAlY tack coat.
As shown in Figure 1, the columnar structure YSZ surface layer prepared of aforesaid method is very complete; And the YSZ surface layer of the prior art shown in Fig. 2 contains cluster-shaped structure.

Claims (2)

1. a preparation method for heavy combustion engine thermal barrier coating of turbine blade, is characterized in that, comprises the steps:
One, utilize EB-PVD technology to prepare CoCrAlY tack coat on heavy combustion engine turbine blade, diffusion in vacuum process is carried out to described CoCrAlY tack coat;
Two, to the surface of CoCrAlY tack coat, use general blaster, application glass ball carries out shot peening;
Three, hidden lino removal is carried out to the heavy combustion engine turbine blade with CoCrAlY tack coat;
Four, EB-PVD technology is utilized to prepare YSZ surface layer with on the heavy combustion engine turbine blade of CoCrAlY tack coat.
2. the preparation method of heavy combustion engine thermal barrier coating of turbine blade according to claim 1, is characterized in that, described hidden lino removal, temperature 1050 DEG C, time 2h.
CN201510810339.2A 2015-11-20 2015-11-20 Method for preparing thermal barrier coating on heavy gas turbine blade Pending CN105369202A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510810339.2A CN105369202A (en) 2015-11-20 2015-11-20 Method for preparing thermal barrier coating on heavy gas turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510810339.2A CN105369202A (en) 2015-11-20 2015-11-20 Method for preparing thermal barrier coating on heavy gas turbine blade

Publications (1)

Publication Number Publication Date
CN105369202A true CN105369202A (en) 2016-03-02

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Family Applications (1)

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CN201510810339.2A Pending CN105369202A (en) 2015-11-20 2015-11-20 Method for preparing thermal barrier coating on heavy gas turbine blade

Country Status (1)

Country Link
CN (1) CN105369202A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018037196A1 (en) * 2016-08-25 2018-03-01 Safran Method for producing a thermal barrier system on a metal substrate of a turbo engine part
CN110735117A (en) * 2019-11-29 2020-01-31 中国航发沈阳黎明航空发动机有限责任公司 duplex guide vane thermal barrier coating preparation method
CN110791734A (en) * 2019-11-29 2020-02-14 中国航发沈阳黎明航空发动机有限责任公司 Preparation method of thermal barrier coating of turbine working blade
CN111962028A (en) * 2020-09-03 2020-11-20 北京金轮坤天特种机械有限公司 EB-PVD/APS composite structure double-ceramic-layer thermal barrier coating and preparation method thereof

Citations (6)

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Publication number Priority date Publication date Assignee Title
CN101234296A (en) * 2008-02-29 2008-08-06 南京工业大学 Preparation technique of porous stainless steel-ceramic compound film
CN101265561A (en) * 2008-03-31 2008-09-17 北京航空航天大学 Transient state ultrahigh temperature resisting heat barrier coat ceramic layer material and preparation method thereof
CN101357854A (en) * 2008-09-12 2009-02-04 西安交通大学 Postprocessing method for reducing thermal conductivity of ceramic heat barrier coating
CN102127738A (en) * 2010-11-25 2011-07-20 北京航空航天大学 Multilayer thermal barrier coating and preparation method thereof
CN103009704A (en) * 2011-09-21 2013-04-03 中国农业机械化科学研究院 Nanometer/columnar-like crystal mixing structure thermal barrier coating and preparation method thereof
CN103484824A (en) * 2013-08-27 2014-01-01 北京航空航天大学 Compound binding layer material with 1200 DEG C high-temperature oxidization resistance and fuel gas thermal corrosion resistance and preparation method of compound binding layer material

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101234296A (en) * 2008-02-29 2008-08-06 南京工业大学 Preparation technique of porous stainless steel-ceramic compound film
CN101265561A (en) * 2008-03-31 2008-09-17 北京航空航天大学 Transient state ultrahigh temperature resisting heat barrier coat ceramic layer material and preparation method thereof
CN101357854A (en) * 2008-09-12 2009-02-04 西安交通大学 Postprocessing method for reducing thermal conductivity of ceramic heat barrier coating
CN102127738A (en) * 2010-11-25 2011-07-20 北京航空航天大学 Multilayer thermal barrier coating and preparation method thereof
CN103009704A (en) * 2011-09-21 2013-04-03 中国农业机械化科学研究院 Nanometer/columnar-like crystal mixing structure thermal barrier coating and preparation method thereof
CN103484824A (en) * 2013-08-27 2014-01-01 北京航空航天大学 Compound binding layer material with 1200 DEG C high-temperature oxidization resistance and fuel gas thermal corrosion resistance and preparation method of compound binding layer material

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018037196A1 (en) * 2016-08-25 2018-03-01 Safran Method for producing a thermal barrier system on a metal substrate of a turbo engine part
CN109689934A (en) * 2016-08-25 2019-04-26 赛峰集团 Method for manufacturing thermal barrier system on the metallic matrix of turbine engine components
CN109689934B (en) * 2016-08-25 2021-09-21 赛峰集团 Method for manufacturing a thermal barrier system on a metal substrate of a turbine engine component
CN110735117A (en) * 2019-11-29 2020-01-31 中国航发沈阳黎明航空发动机有限责任公司 duplex guide vane thermal barrier coating preparation method
CN110791734A (en) * 2019-11-29 2020-02-14 中国航发沈阳黎明航空发动机有限责任公司 Preparation method of thermal barrier coating of turbine working blade
CN110735117B (en) * 2019-11-29 2021-06-29 中国航发沈阳黎明航空发动机有限责任公司 Preparation method of thermal barrier coating of duplex guide blade
CN111962028A (en) * 2020-09-03 2020-11-20 北京金轮坤天特种机械有限公司 EB-PVD/APS composite structure double-ceramic-layer thermal barrier coating and preparation method thereof

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Application publication date: 20160302

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