CN102994938B - Novel laser processing method for surface of atmospheric plasma sprayed thermal barrier coating - Google Patents
Novel laser processing method for surface of atmospheric plasma sprayed thermal barrier coating Download PDFInfo
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- CN102994938B CN102994938B CN201210520934.9A CN201210520934A CN102994938B CN 102994938 B CN102994938 B CN 102994938B CN 201210520934 A CN201210520934 A CN 201210520934A CN 102994938 B CN102994938 B CN 102994938B
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- barrier coating
- thermal barrier
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- 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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Abstract
The invention discloses a novel laser processing method for the surface of an atmospheric plasma sprayed thermal barrier coating. On the surface of thermal barrier coating of a ceramic layer sprayed by adopting a plasma spraying method, the ceramic layer is induced by utilizing laser to produce a certain quantity of surface cracks perpendicular to a matrix and regularly distributed, the novel laser processing method specially comprises the following steps: a laser beam emitter is controlled through a controller connected with the laser beam emitter to scan the surface of the ceramic layer along a preset track, the controller is also connected with a base of the thermal barrier coating for placing the ceramic layer, and the controller controls the base to move along the direction perpendicular to the moving direction of the laser beam emitter while controlling the laser beam emitter to scan the surface of the ceramic layer along the preset track. With the adoption of the method, the sprayed atmospheric plasma thermal barrier coating is further induced to produce a certain quantity of surface cracks regularly distributed in the ceramic layer, so that the mechanical performance of the atmospheric plasma sprayed thermal barrier coating is improved in later preparation period, and the service life of the atmospheric plasma sprayed thermal barrier coating can be greatly prolonged.
Description
Technical field
The present invention relates to the method for toughening of thermal barrier coating, particularly a kind of new pattern laser treatment process of air plasma spraying thermal barrier coating surface.
Background technology
Since the development that is modern Aviation industry of 20 middle of century internal combustion turbine is laid a good foundation, internal combustion turbine obtains further promotion and application in fields such as military affairs, space flight, energy source and power, production.The fuel gas temperature of current New Type Military gas turbine engine is up to about 1500 DEG C, and for the use temperature of the high-melting-point nickel based super alloy of active service engine blade only at 850 DEG C ~ about 1100 DEG C, directional solidificating alloy and single crystal alloy also can only work at about 1000 DEG C of temperature, cannot meet the needs of Modern New engine operating temperature.Meanwhile, along with the development of aircraft industry, large-scale gas turbine of new generation needs higher thrust-weight ratio, efficiency gas and turbine intake temperature.Therefore, the heat-resisting ability improving turbine blade quickly and efficiently just becomes the task of top priority.Thermal barrier coating (Thermal barrier coating, be called for short TBC) swift and violent as a kind of thermal protection technology development in recent years, thermal barrier coating typically refers to the ceramic coating being deposited on high-temperature alloy surface, having good effect of heat insulation, its Main Function is thermal boundary, and avoid the high temperature oxidation, burn into wearing and tearing etc. of matrix, the temperature reaching metallic matrix can be reduced about 50-150 DEG C by it, thus promotes the heat-resisting ability of high-temperature hot end pieces.It can improve combustion engine working temperature and resistance to corrosion, reduction cooling require, increase combustion engine power and improve efficiency of combustion, is therefore widely used in Aeronautics and Astronautics, the aspect such as shipbuilding, automobile.
Thermal barrier coating system is an extremely complicated solid system.Generally comprise four parts: superalloy matrix, tack coat, thermal growth oxide layer (TGO) and ceramic layer.The major cause of restricted T BC application is coating interface unsticking.Coating interface unsticking is greater than ceramic layer mainly due to metallic matrix coefficient of thermal expansion, and because thermal mismatch stress causes having very high strain energy in ceramic aspect, strain energy drives Interface Crack to be formed.
Preparation technology mainly contains the technology such as electro beam physics vapour deposition (EB-PVD), air plasma spraying (APS).Electro beam physics vapour deposition process costs is higher, but prepared thermal insulation layer construction is even, and microstructure has multiple dimensioned empty column crystal feature, and high with the bonding strength of matrix, service life is long, is mainly applied to the preparation of aircraft engine thermal barrier coating.Air plasma spraying lower cost, microstructure has the multilayer laminated feature of coin shape, and thermal boundary effect is better, is mainly used in the preparation of civilian heavy duty gas turbine thermal barrier coating.Because each constituent materials attribute of thermal barrier coating and geometrical shape exist larger difference, particularly between each component there is very big-difference in thermal expansivity, when high temperature changes, usually lost efficacy due to thermal mismatch stress.Simultaneously because ceramic layer is loose porous material, therefore Sauerstoffatom is easily diffused into tack coat by ceramic layer, causes tack coat and ceramic layer interface to be oxidized, and forms thermal growth oxide layer.The high temperature of thermal growth oxide layer fast growth can interface induced go out sizable hot growth stress thus cause ceramic layer and tie-layer interface to damage to lose efficacy.
Mainly ceramic layer columnar crystal structure is even for the long-life reason of Electron Beam-Physical Vapor Deposited Thermal Barrier Coatings, between column crystal, crystal boundary is in conjunction with weak, is equivalent to there is a large amount of vertical crack, greatly relaxes thermal mismatch strain, reduce thermal stresses intensity, thus there is long-life advantage.Air plasma spraying thermal barrier coating microstructure is mainly the sheet structure being parallel to matrix, and being parallel to, the bonding strength in thermal barrier coating surface direction is higher, and the ability relaxing thermal stresses is more weak.Thus the thermal mismatch stress in reduction air plasma spraying thermal barrier coating and hot growth stress are one of key factors improving the air plasma spraying life-span.The main technology in order to improve the air plasma spraying thermal barrier coating life-span is that preparation has some amount and the air plasma spraying thermal barrier coating of the vertical crack of regular distribution at present, existence due to vertical crack makes ceramic coating have Large strain toughness feature, add the ability that ceramic layer relaxes thermal mismatching, reduce the thermal stresses in ceramic layer, simultaneously because vertical crack is in surface ceramii layer regular distribution, therefore can strain energy effectively in emission surface, make it that there is efficient thermal boundary and long life characteristics.
The current atmospheric plasma spraying technology extensively adopted is owing to accurately cannot control generation and the expansion of vertical crack in ceramic layer, therefore mostly be uneven in the air plasma spraying thermal barrier coating ceramic layer on surface after spraying, the vertical crack of mixed and disorderly formation, and crack number does not reach the demand reducing ceramic layer thermal stresses yet.Application number be 201210435928.3 patent of invention " a kind of method for toughening of high heat insulation anti-sintering thermal barrier coating " propose and adopt laser scanning on two ceramic layer thermal barrier coating surface, generate the crackle perpendicular to matrix or damage, because in its pair of ceramic layer thermal barrier coating system, two kinds of ceramic interfacial combined functions are poor, therefore require that generating shorter surface crack and this crackle should only be present in ceramic layer on surface, thus ensure that the interface of two-layer ceramic is complete.But this reduces the toughening effect of surface crack, and the method generates crackle or damage cannot control.
Summary of the invention
In order to solve above-mentioned prior art Problems existing, the object of the present invention is to provide a kind of new pattern laser treatment process of air plasma spraying thermal barrier coating surface, the further inductive formation some amount in ceramic layer of the air plasma spraying thermal barrier coating after spraying can be made, the surface crack of regular distribution, thus the phase improves the mechanical property of air plasma spraying thermal barrier coating after the production, increases substantially its life-span.
In order to achieve the above object, the present invention is achieved by the following technical solutions.
A kind of new pattern laser treatment process of air plasma spraying thermal barrier coating surface, on the surface of the ceramic layer thermal barrier coating of plasma spraying method spraying, utilize the generation of induced with laser ceramic layer inside perpendicular to the some amount of matrix, the surface crack of regular distribution, concrete grammar is: control laser beam transmitter 2 along desired trajectory scanning surface ceramii layer by the controller 1 be connected with laser beam transmitter 2, also be connected with the base 3 placing single ceramic layer thermal barrier coating with Time Controller 1, controller 1 also controls base 3 and moves along the direction vertical with laser beam transmitter travel direction while control laser beam transmitter 2 scans surface ceramii layer along desired trajectory.
The width of the laser beam that described laser beam transmitter 2 is launched is 150 μm, and laser beam power W/ sweep velocity m/s is 15.18≤p/v≤23.04, and the sweep span of laser beam transmitter 1 is 10 to 20 times of ceramic layer thickness.
Compared to the prior art, tool of the present invention has the following advantages:
1, the heating induction effect that the new pattern laser treatment process on the air plasma spraying thermal barrier coating surface that the present invention proposes controls laser beam transmitter by controller makes the formation of surface crack to control, also the base controlling to place single ceramic layer thermal barrier coating with Time Controller moves along the direction vertical with laser beam transmitter travel direction, thus the surperficial vertical crack of abundant darker regular distribution can be formed at ceramic layer on surface, reach the effect relaxing thermal mismatch stress and hot growth stress, the life-span of thermal barrier coating is greatly improved, or form the surface crack of net distribution, the block unsticking of ceramic layer can be prevented like this.Meanwhile, due to crackle generate position and spacing all by manual control, therefore after the inventive method process, surface crack is formed according to schedule, be not concentrated in a certain region, thus ensure that the intensity of thermal barrier coating, and then improve the life-span of thermal barrier coating.
2, because the width of the laser beam of laser beam transmitter 2 transmitting is 150 μm, laser beam power W/ sweep velocity m/s is 15.18≤p/v≤23.04, the heat that then laser beam produces only can induce the vertical crack below irradiation area, and harmful effect is not produced to ceramic layer and tie-layer interface, thus large-scale damage is not formed to surface ceramii layer while induction crackle generates.
3, when 10 to 20 times that the sweep span of laser beam transmitter 2 is ceramic layer thickness, when namely the spacing of adjacent twice vertical crack is 10 to 20 times of ceramic layer thickness, the restraining effect of effects on surface crackle is the most obvious.
Accompanying drawing explanation
Fig. 1 is the inventive method schematic diagram.
Fig. 2 is the inventive method implementation result schematic diagram.
Fig. 3 is the electron microscope scanning figure of the air plasma spraying thermal barrier coating test specimen surface ceramii layer after the inventive method process.
Embodiment
Below in conjunction with the drawings and specific embodiments, further detailed description is done to the present invention.
The new pattern laser treatment process on a kind of air plasma spraying thermal barrier coating of the present invention surface, first plasma spraying method spraying thermal barrier coating test specimen is as shown in Figure 2 adopted, be followed successively by superalloy substrate, the tack coat of superalloy substrate and ceramic layer and ceramic layer from inside to outside, then as shown in Figure 1, control laser beam transmitter 2 by the controller 1 be connected with laser beam transmitter 2 and scan surface ceramii layer along laser beam transmitter guide rail 5, as v in Fig. 1
1direction is moved, also be connected with the base 3 placing thermal barrier coating test specimen 4 with Time Controller 1, it is mobile along base rail 6 (direction vertical with laser beam transmitter travel direction) that controller 1 also controls base 3 while control laser beam transmitter 2 scans surface ceramii layer along desired trajectory, as v in Fig. 1
2direction is moved.The width of the laser beam that laser beam transmitter 2 is launched is 150 μm, and laser beam power W/ sweep velocity m/s is 15.18≤p/v≤23.04, and the sweep span of laser beam transmitter 2 is 10 to 20 times of ceramic layer thickness.
As shown in Figure 2, pottery near laser beam point of application in a part of domed region in brittle ceramic layer surface can heat up expansion rapidly, form thermal expansion district, because the short surface ceramic in addition of compole during heat-processed material thermal conductivity is very low, therefore below thermal expansion district, pottery does not almost produce volume change in this mechanism, and the pottery in thermal expansion district then can produce tensile stress in pottery thereunder.When tensile stress meets or exceeds the maximum value that surface ceramic can bear, its lower zone is caused to germinate vertical crack and expanding subsequently, the track launched by adjusting laser beam projector 2 just can make the vertical crack generated be formed according to required distribution, form the structure of the made thermal barrier coating of similar electro beam physics vapour deposition to improve the strain ability to bear of ceramic layer, relief of thermal stress, improve the strain toughness of air plasma spraying thermal barrier coating, thus reach the object extending its work-ing life.
Fig. 3 be according to disposal methods of the present invention after the electron microscope scanning figure of air plasma spraying thermal barrier coating test specimen surface ceramii layer.Can find to generate a series of surperficial vertical crack in heat-barrier coating ceramic layer from figure after process of the present invention, this experimental result can prove feasibility of the present invention well.A series of surface crack can obviously be observed in inside, sweeping district in figure 3, and its generational verctor causes germinating vertical crack below thermal expansion district and expanding subsequently in mainly LASER HEATING, and its principle as shown in Figure 2.In addition find laser sweeping district's pattern and surrounding ceramic floor different, this is because there is melting resolidification in one deck that after LASER HEATING, surface ceramii layer is very thin, because this process only occurs at one deck that surface ceramii layer is very thin, therefore can not affect greatly its performance.
Claims (1)
1. the new pattern laser treatment process on an air plasma spraying thermal barrier coating surface, on the surface of the ceramic layer thermal barrier coating of air plasma spraying, utilize the generation of induced with laser ceramic layer inside perpendicular to the some amount of matrix, the surface crack of regular distribution, it is characterized in that: concrete grammar is: control laser beam transmitter (2) along desired trajectory scanning surface ceramii layer by the controller (1) be connected with laser beam transmitter (2), same Time Controller (1) is also connected with the base (3) placing single ceramic layer thermal barrier coating, controller (1) also controls base (3) and moves along the direction vertical with laser beam transmitter travel direction while control laser beam transmitter (2) scans surface ceramii layer along desired trajectory, the width of the laser beam that described laser beam transmitter (2) is launched is 150 μm, and laser beam power W/ sweep velocity m/s is 15.18≤p/v≤23.04, and the sweep span of laser beam transmitter (2) is 10 to 20 times of ceramic layer thickness.
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| CN201210520934.9A CN102994938B (en) | 2012-12-04 | 2012-12-04 | Novel laser processing method for surface of atmospheric plasma sprayed thermal barrier coating |
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| CN201210520934.9A CN102994938B (en) | 2012-12-04 | 2012-12-04 | Novel laser processing method for surface of atmospheric plasma sprayed thermal barrier coating |
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| CN102994938B true CN102994938B (en) | 2014-12-24 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103266295B (en) * | 2013-05-23 | 2015-10-07 | 广州有色金属研究院 | A kind of thermal barrier coating by laser surface modifying method |
| CN105821366B (en) * | 2016-04-25 | 2018-11-09 | 昆明理工大学 | A method of release uses the internal stress of thermal spraying prepares coating |
| CN112725719B (en) * | 2020-10-21 | 2022-05-20 | 西安交通大学 | Ceramic protective coating and preparation method thereof |
| CN115852294B (en) * | 2022-12-28 | 2023-08-01 | 西安交通大学 | Thermal barrier coating containing surface cracks based on stress regulation and control and preparation method thereof |
| CN117072253B (en) * | 2023-10-16 | 2024-01-09 | 西安交通大学 | Thermal barrier coating for high-temperature blade of heavy-duty gas turbine and design, manufacture and evaluation methods thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5216808A (en) * | 1990-11-13 | 1993-06-08 | General Electric Company | Method for making or repairing a gas turbine engine component |
| US20090017260A1 (en) * | 2001-08-02 | 2009-01-15 | Kulkarni Anand A | Segmented thermal barrier coating |
| US20100062173A1 (en) * | 2001-06-15 | 2010-03-11 | Mitsubishi Heavy Industries Ltd. | Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5216808A (en) * | 1990-11-13 | 1993-06-08 | General Electric Company | Method for making or repairing a gas turbine engine component |
| US20100062173A1 (en) * | 2001-06-15 | 2010-03-11 | Mitsubishi Heavy Industries Ltd. | Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine |
| US20090017260A1 (en) * | 2001-08-02 | 2009-01-15 | Kulkarni Anand A | Segmented thermal barrier coating |
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