CN105463453A - Thermal barrier coating with stable interface and manufacturing method of thermal barrier coating - Google Patents

Thermal barrier coating with stable interface and manufacturing method of thermal barrier coating Download PDF

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Publication number
CN105463453A
CN105463453A CN201510830081.2A CN201510830081A CN105463453A CN 105463453 A CN105463453 A CN 105463453A CN 201510830081 A CN201510830081 A CN 201510830081A CN 105463453 A CN105463453 A CN 105463453A
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coating
ysz
preparation
mcraly
thermal barrier
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CN105463453B (en
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程玉贤
王璐
袁福河
宋佳
赵忠兴
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AECC Shenyang Liming Aero Engine Co Ltd
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Shenyang Liming Aero Engine Group Co Ltd
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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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • 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

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  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Physical Vapour Deposition (AREA)

Abstract

The invention provides a thermal barrier coating with a stable interface and a manufacturing method of the thermal barrier coating and belongs to the technical field of aero-engines. The coating is composed of a YSZ activated diffusion barrier, a MCrAlY metal bonding bottom layer, an aluminized layer and a YSZ ceramic face layer. The YSZ activated diffusion barrier is manufactured through an electron beam physical vapor deposition method, the MCrAlY metal bonding bottom layer is manufactured through a vacuum arc plating method, the aluminized layer is manufactured through a solid powder embedding method or a chemical vapor deposition method, the YSZ ceramic face layer is manufactured through the electron beam physical vapor deposition method, and therefore a typical columnar crystal structure is formed. The coating has the good oxidation resistance and cold-heat alternate circulating capacity. By the adoption of the method, the purpose of coating interface compatibility can be achieved, the strain tolerance of the coating can be improved, and therefore the oxidation resistance of high-temperature alloy is improved.

Description

Thermal barrier coating of a kind of interface stability and preparation method thereof
Technical field
This technology belongs to aero engine technology field, particularly a kind of thermal barrier coating and preparation method thereof of interface stability.
Background technology
Along with aircraft engine develops to high thrust-weight ratio, in combustion chamber, temperature and pressure improves constantly, and high turbine entrance temperature inlet temperature has become a large feature of high thrust-weight ratio aircraft engine.As the kernel component of engine, turbine blade stands impact and the erosion of high-temperature fuel gas for a long time, Service Environment very severe.The superalloy that turbine blade is selected has received the challenge of himself service temperature limit.The maximum operation (service) temperature of current latest generation nickel base superalloy is not also higher than 1150 DEG C, and close to 85% of alloy melting point, then the use temperature difficulty up increasing substantially alloy is very large.According to engine cool ability, be used alone as high thrust-weight ratio aero engine turbine blades high temperature alloy the demand being difficult to meet high engine speeds development.
Thermal barrier coating (TBCs) is generally by antioxidant anticorrosive metal bonding of good performance bottom (PtAl or MCrAlY, M=Ni, Co or Ni+Co) and the low ceramic topcoats (Y of thermal conductivity 2o 3partially stabilized ZrO 2, YSZ) and composition.It is widely used in aircraft engine hot-end component, makes superalloy can bear higher service temperature, improves turbine entrance temperature inlet temperature, engine life and reliability also can be made to increase substantially simultaneously, and oil consumption reduces, and dynamic performance is significantly improved.
Metal bonding coating is as the transition layer between ceramic topcoats and superalloy matrix, and it is reduce between ceramic topcoats and superalloy matrix because thermal expansivity does not mate caused thermal stresses that its effect mainly contains two: one; Two is the antioxidant anticorrosive performances (YSZ ceramic topcoats is oxygen ion conductor, and mostly is porous or columnar crystal structure, and these structures can become the rapid diffusion passage of corrosive medium, the corrosion of aggravation superalloy matrix) improving whole thermal barrier coating system.The Composition Design of the tack coat bonding force etc. to the speed of growth of oxide compound in Thermal Cycling, composition and matrix has conclusive effect, and bonding layer material should be able to form good interfacial diffusion resistance with high-temperature alloy base body, to avoid the degeneration (mutual diffusion causes) occurring matrix and tack coat performance in process under arms.Current common metal bond coating (PtAl or MCrAlY) under arms in process inevitably with superalloy matrix generation mutual diffusion, form fragility mutual diffusion band and open up harmful precipitated phases such as mending Mi Dui phase (TCP), cause alloy structure unstability.Research finds, the formation of high-temperature alloy surface fragility mutual diffusion band and TCP will cause the high temperature mechanical properties decrease more than 50% such as the high cycle fatigue of alloy substrate and creep rupture life.Meanwhile, the oxidation-resistance element in metal bonding coating such as Al, Cr etc. also to cause the high temperature oxidation corrosion resistance degradation of coating to alloy internal diffusion.
Therefore, how while ensureing metal bonding coating good oxidation resistance energy, to ensure that the interphase match of coating and superalloy and stability become the key issue developing high-temperature alloy protecting coating.
Summary of the invention
It is a kind of good with superalloy interface compatibility to the object of the present invention is to provide, and antioxidant property is excellent, the preparation method of the superalloy thermal barrier coating that strain tolerance limit is high.
The thermal barrier coating of a kind of interface stability of the present invention, this coating is made up of the active diffusion barrier/MCrAlY metal bonding bottom/aluminized coating/YSZ ceramic topcoats of YSZ; Wherein the active diffusion barrier of YSZ adopts the preparation of electro beam physics vapour deposition method, MCrAlY metal bonding bottom adopts the preparation of vacuum arc electroplating method, aluminized coating adopts pressed powder embedding method or chemical gaseous phase depositing process preparation, YSZ ceramic topcoats adopts the preparation of electro beam physics vapour deposition method, in typical column crystal structure.
The preparation method of the thermal barrier coating of a kind of interface stability of the present invention, carries out according to following steps:
(1) preparation of the active diffusion barrier of YSZ:
Adopt electro beam physics vapour deposition method to prepare the active diffusion barrier of YSZ at single crystal super alloy matrix, the test piece of active for complete for above-mentioned deposition YSZ diffusion barrier is carried out air-stable annealing 4 ~ 6 hours at 750 DEG C;
(2) preparation of MCrAlY bottom:
Adopt vacuum arc electroplating method to prepare the MCrAlY coating of about 20 ~ 40 μm in coatingsurface prepared by step (1), then carry out diffusion in vacuum thermal treatment 2 ~ 4 hours at 1050 DEG C;
(3) bottom post-processing technology:
Wet blast surface strengthening planarizing technique is adopted to diffusion state MCrAlY bottom prepared by step (2), improves protective coating interface binding power, improve secondary aluminized coating structure;
(4) preparation of aluminized coating:
Solid entrapping method or the MCrAlY coating of chemical gaseous phase depositing process to step (3) is adopted to carry out secondary aluminising;
(5) calorized coating post-processing technology:
Wet blast process is carried out, polishing coatingsurface to coating prepared by step (4), promotes Al 2o 3the quick formation of oxide film;
(6) YSZ ceramic topcoats preparation method:
The coating adopting electro beam physics vapour deposition method to prepare in step (5) prepares YSZ ceramic topcoats, adopt Ion Cleaning in preparation process 5 ~ 10 minutes, electron beam heating single crystal super alloy matrix to 850 ~ 900 DEG C;
(7) YSZ ceramic topcoats post-treating method:
Coating step (6) prepared carries out air-stable annealing 4 ~ 20 hours at 700 ~ 900 DEG C, improves the structure stability of thermal barrier coating.
In order to solve the issue of inter-diffusion in traditional MCrAlY coating and between superalloy matrix, in MCrAlY coating and between superalloy matrix, add the active diffusion barrier of one deck.In high-temperature service process, the active diffusion barrier of superalloy matrix/YSZ and the active diffusion barrier/MCrAlY coating interface place of YSZ can form the rich Al oxide compound of two-layer continuous print, this two-layer rich Al oxide compound stops the diffusion between MCrAlY coating and superalloy matrix effectively, improves the interface stability between MCrAlY coating and superalloy matrix.
In order to solve the problem that in MCrAlY coating, Al constituent content is limited, secondary aluminising process being carried out to MCrAlY coating, making MCrAlY coatingsurface form the rich Al layer of one deck.This rich Al layer can form Al fine and close continuously in oxidising process 2o 3oxide film, can improve the interface stability of MCrAlY bottom and YSZ ceramic topcoats.
In order to improve the strain tolerance limit of thermal barrier coating further, YSZ ceramic topcoats adopts the preparation of electro beam physics vapour deposition method, in typical column crystal structure.
This coating has good antioxidant property and alternating hot and cold circulation ability.The method both can solve coating interface compatibility problem, can improve again the strain tolerance limit of coating, thus improved the antioxidant property of superalloy.
The present invention compared with prior art has following major advantage:
(1), by introducing active diffusion barrier between MCrAlY bottom and superalloy matrix, both can at the fine and close Al of high-temperature oxidation process floating coat/alloy interface both sides in-situ preparation 2o 3film, stops the mutual diffusion of coating and alloy constituent element effectively, meanwhile, and the Al formed by surface reaction 2o 3film is conducive to the adhesivity improving oxide compound diffusion barrier, improves the interface stability between MCrAlY bottom and superalloy matrix.
(2) aluminising process is carried out to MCrAlY bottom, MCrAlY coatingsurface can be made to form the rich Al layer of one deck.This rich Al layer can form Al fine and close continuously in oxidising process 2o 3oxide film, improves the interface stability between MCrAlY bottom and YSZ ceramic topcoats.
(3), to diffusion state MCrAlY bottom adopt wet blast surface strengthening planarizing technique, protective coating interface binding power can be improved, improve aluminized coating structure.
(4) the wet blast process, after aluminized coating contributes to the structure improving ceramic topcoats, raising coating interface bonding force.
(5), adopt electro beam physics vapour deposition (EB-PVD) the columnar crystal structure YSZ ceramic topcoats prepared can improve the strain tolerance limit of coating, improve protective coating cold-and-heat resistent circulation ability.
(6) technology such as, ceramic topcoats preparation process intermediate ion cleaning, matrix heating assist in removing interface pollution thing, raising protective coating interface binding power.
(7), ceramic topcoats aftertreatment contributes to the structure stability improving ceramic topcoats.
(8), described thermal barrier coating system interphase match is good, and antioxidant property is excellent, and strain tolerance limit is high.
Accompanying drawing explanation
Fig. 1 is the Cross Section Morphology after conventional high temperature alloy substrate/MCrAlY coating system 1000 DEG C oxidation 100h.
Fig. 2 is the Cross Section Morphology after the active diffusion barrier of superalloy matrix/YSZ/MCrAlY coating system 1000 DEG C oxidation 100h.
Embodiment
Embodiment 1
A thermal barrier coating for interface stability, this coating is made up of the active diffusion barrier/MCrAlY metal bonding bottom/aluminized coating/YSZ ceramic topcoats of YSZ; Wherein the active diffusion barrier of YSZ adopts the preparation of electro beam physics vapour deposition method, MCrAlY metal bonding bottom adopts the preparation of vacuum arc electroplating method, aluminized coating adopts pressed powder embedding method or chemical gaseous phase depositing process preparation, YSZ ceramic topcoats adopts the preparation of electro beam physics vapour deposition method, in typical column crystal structure.
The preparation method of the thermal barrier coating of a kind of interface stability of the present invention, carries out according to following steps:
(1) preparation of the active diffusion barrier of YSZ:
Adopt the preparation of electro beam physics vapour deposition method, first the DZ125 sample after just wet blast loads superalloy fixture, straight feeding system is adopted to send into working vacuum room, the heating current of YSZ target is 1.3 ~ 1.5A, the Heating temperature of DZ125 alloy test piece is 850 ~ 900 DEG C, the speed of rotation of DZ125 alloy test piece is 12 ~ 15 revs/min, controls depositing time and makes coat-thickness be 2 μm, secondly complete for above-mentioned deposition YSZ test piece is carried out air-stable at 750 DEG C and anneal 4 hours.
(2) preparation of MCrAlY bottom
Above-mentioned test piece is loaded vacuum arc coating apparatus carry out Ion Cleaning and prepare NiCrAlY bottom, adopt vacuum arc electroplating method to prepare the MCrAlY coating of about 20 ~ 40 μm at high-temperature alloy surface, then carry out diffusion in vacuum thermal treatment 2 hours at 1050 DEG C; Vacuum arc plating method and technology parameter is: arc current 700 ~ 750A, coating time 120min, bias voltage-34V.
(3) bottom post-processing technology
Wet blast process is carried out to above-mentioned diffusion state MCrAlY bottom, and carry out ultrasonic cleaning, acetone soln embathes, dry; Wet blast processing parameter is: white fused alumina fineness of sand is 180 orders, emergy content 20%, blast 0.15MPa, and blast distance is 180mm.
(4) preparation of aluminized coating
Above-mentioned test piece being installed on unit clamp also carries out fastening with superalloy silk.Test piece is installed in aluminising tank and carries out secondary aluminising process.Solid entrapping method or chemical gaseous phase depositing process is adopted to carry out secondary aluminising to MCrAlY coating; Solid entrapping method concrete technology parameter is: adopt FeAl powder as penetration enhancer, Al 2o 3for antiseize lubricant, NH 4cl is activator.
(5) calorized coating post-processing technology
Wet blast process is carried out in test piece after aluminising, and carry out ultrasonic cleaning, acetone soln embathes, dry, and promotes Al 2o 3the quick formation of oxide film.Wet blast processing parameter is: white fused alumina fineness of sand is 280 orders, emergy content 35%, blast 0.25MPa, and blast distance is 350mm.
(6) YSZ ceramic topcoats preparation method
Above-mentioned test piece being installed on unit clamp also carries out fastening with superalloy silk.
Test piece is installed in load chamber, open mechanical pump and lobe pump, vacuumize, treat main vacuum chamber, load chamber vacuum tightness is respectively 5 × 10-2Pa, open the slide valve between two Room during 1Pa, pass into Ar gas, icon bombardment cleaning 10min is carried out to strip, object removes blade surface dirt, improves the bonding strength between coating and matrix.
Test piece and fixture after ion cleaning are moved on to main vacuum chamber, carries out YSZ ceramic topcoats deposition.Deposition YSZ surface layer processing parameter is: main vacuum chamber's pressure is 4 × 10-2Pa, and electron beam gun voltage is 18KV, and target heating current is 1.5A, and workpiece rotational frequency is 15r/min, and workpiece heat temperature is 850 DEG C.
(7) YSZ ceramic topcoats post-treating method
Air-stable annealing is carried out 20 hours at 700 DEG C to deposited thermal barrier coating, improves the structure stability of thermal barrier coating.
Fig. 1 is the Cross Section Morphology after conventional high temperature alloy substrate/MCrAlY coating system 1000 DEG C oxidation 100h.As can be seen from Fig., obvious mutual diffusion band is defined at superalloy matrix and MCrAlY coating interface place.
Fig. 2 is the Cross Section Morphology after the active diffusion barrier of superalloy matrix/YSZ/MCrAlY coating system 1000 DEG C oxidation 100h.As can be seen from Fig., high-temperature service process median surface place defines the Al of inertia 2o 3film, had both effectively stoped or had slowed down the mutual diffusion between long service process interalloy/coating system, improved the permanent stability of alloy/coating system, can ensure again the metallurgical binding of interface necessity.

Claims (2)

1. a thermal barrier coating for interface stability, is characterized in that this coating is made up of the active diffusion barrier/MCrAlY metal bonding bottom/aluminized coating/YSZ ceramic topcoats of YSZ; Wherein the active diffusion barrier of YSZ adopts the preparation of electro beam physics vapour deposition method, MCrAlY metal bonding bottom adopts the preparation of vacuum arc electroplating method, aluminized coating adopts pressed powder embedding method or chemical gaseous phase depositing process preparation, YSZ ceramic topcoats adopts the preparation of electro beam physics vapour deposition method, in typical column crystal structure.
2. the preparation method of the thermal barrier coating of a kind of interface stability according to claim 1, is characterized in that carrying out according to following steps:
(1) preparation of the active diffusion barrier of YSZ: adopt electro beam physics vapour deposition method to prepare the active diffusion barrier of YSZ at single crystal super alloy matrix, the test piece of active for complete for above-mentioned deposition YSZ diffusion barrier is carried out air-stable annealing 4 ~ 6 hours at 850 ~ 900 DEG C;
(2) preparation of MCrAlY bottom: adopt vacuum arc electroplating method to prepare the MCrAlY coating of about 20 ~ 40 μm in coatingsurface prepared by step (1), then carry out diffusion in vacuum thermal treatment 2 ~ 4 hours at 1050 DEG C;
(3) bottom post-processing technology: wet blast surface strengthening planarizing technique is adopted to diffusion state MCrAlY coating prepared by step (2), improves protective coating interface binding power, improve secondary aluminized coating structure;
(4) preparation of aluminized coating: adopt solid entrapping method or the MCrAlY coating of chemical gaseous phase depositing process to step (3) to carry out secondary aluminising;
(5) calorized coating post-processing technology: carry out wet blast process, polishing coatingsurface to coating prepared by step (4), promotes Al 2o 3the quick formation of oxide film;
(6) YSZ ceramic topcoats preparation method: the coating adopting electro beam physics vapour deposition method to prepare in step (5) prepares YSZ ceramic topcoats, adopt Ion Cleaning in preparation process 5 ~ 10 minutes, electron beam heating single crystal super alloy matrix to 850 ~ 900 DEG C;
(7) YSZ ceramic topcoats post-treating method: coating step (6) prepared carries out air-stable annealing 4 ~ 20 hours at 700 ~ 900 DEG C, improves the structure stability of thermal barrier coating.
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105734500A (en) * 2016-04-21 2016-07-06 西北有色金属研究院 High temperature oxidation-resistant thermal barrier coating layer with composite structure and preparation method thereof
CN106244977A (en) * 2016-08-30 2016-12-21 北京航空航天大学 Plasma evaporation deposits a kind of quasi-column structure heat-barrier coating ceramic layer and preparation method thereof
CN107345299A (en) * 2016-12-13 2017-11-14 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of turbine blade assemblies thermal barrier coating and preparation method thereof
CN108004543A (en) * 2017-11-30 2018-05-08 中国航发沈阳黎明航空发动机有限责任公司 A kind of thermal barrier coating of anti-CMAS corrosion and preparation method thereof
CN109930102A (en) * 2019-04-25 2019-06-25 清华大学无锡应用技术研究院 A kind of novel thermal barrier coating preparation process
CN110408931A (en) * 2019-09-02 2019-11-05 铜陵学院 A kind of thermal barrier coating and preparation method thereof with the long-life
CN111394702A (en) * 2020-04-03 2020-07-10 北航（四川）西部国际创新港科技有限公司 Thermal barrier coating and preparation method and application thereof
CN112941451A (en) * 2021-01-25 2021-06-11 武汉理工大学 Method for improving stability of thermal barrier coating in natural environment
CN115961248A (en) * 2022-12-07 2023-04-14 中国航发动力股份有限公司 Single crystal blade thermal barrier coating repairing method

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CN101045981A (en) * 2006-03-27 2007-10-03 三菱重工业株式会社 Oxidation-resistant coating and formation method thereof, thermal barrier coating, heat-resistant member, and gas turbine
CN101351576A (en) * 2005-11-08 2009-01-21 曼涡轮机股份公司 Heat-insulating protective layer for a component located within the hot gas zone of a gas turbine
CN103342016A (en) * 2013-07-05 2013-10-09 中国科学院金属研究所 High temperature coating containing zirconium oxide active diffusing barrier and preparation method thereof

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030138658A1 (en) * 2002-01-22 2003-07-24 Taylor Thomas Alan Multilayer thermal barrier coating
CN101351576A (en) * 2005-11-08 2009-01-21 曼涡轮机股份公司 Heat-insulating protective layer for a component located within the hot gas zone of a gas turbine
CN101045981A (en) * 2006-03-27 2007-10-03 三菱重工业株式会社 Oxidation-resistant coating and formation method thereof, thermal barrier coating, heat-resistant member, and gas turbine
CN103342016A (en) * 2013-07-05 2013-10-09 中国科学院金属研究所 High temperature coating containing zirconium oxide active diffusing barrier and preparation method thereof

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105734500A (en) * 2016-04-21 2016-07-06 西北有色金属研究院 High temperature oxidation-resistant thermal barrier coating layer with composite structure and preparation method thereof
CN105734500B (en) * 2016-04-21 2018-08-03 西北有色金属研究院 A kind of resistance to high temperature oxidation thermal barrier coating and preparation method thereof with composite construction
CN106244977A (en) * 2016-08-30 2016-12-21 北京航空航天大学 Plasma evaporation deposits a kind of quasi-column structure heat-barrier coating ceramic layer and preparation method thereof
CN107345299A (en) * 2016-12-13 2017-11-14 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of turbine blade assemblies thermal barrier coating and preparation method thereof
CN107345299B (en) * 2016-12-13 2019-09-27 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of turbine blade assemblies thermal barrier coating and preparation method thereof
CN108004543A (en) * 2017-11-30 2018-05-08 中国航发沈阳黎明航空发动机有限责任公司 A kind of thermal barrier coating of anti-CMAS corrosion and preparation method thereof
CN109930102A (en) * 2019-04-25 2019-06-25 清华大学无锡应用技术研究院 A kind of novel thermal barrier coating preparation process
CN110408931A (en) * 2019-09-02 2019-11-05 铜陵学院 A kind of thermal barrier coating and preparation method thereof with the long-life
CN110408931B (en) * 2019-09-02 2024-03-01 铜陵学院 Thermal barrier coating with long service life and preparation method thereof
CN111394702A (en) * 2020-04-03 2020-07-10 北航（四川）西部国际创新港科技有限公司 Thermal barrier coating and preparation method and application thereof
CN112941451A (en) * 2021-01-25 2021-06-11 武汉理工大学 Method for improving stability of thermal barrier coating in natural environment
CN115961248A (en) * 2022-12-07 2023-04-14 中国航发动力股份有限公司 Single crystal blade thermal barrier coating repairing method

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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company

Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City