CN103774082A - Preparation method of thermal barrier coating - Google Patents
Preparation method of thermal barrier coating Download PDFInfo
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- CN103774082A CN103774082A CN201410060589.4A CN201410060589A CN103774082A CN 103774082 A CN103774082 A CN 103774082A CN 201410060589 A CN201410060589 A CN 201410060589A CN 103774082 A CN103774082 A CN 103774082A
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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
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses a preparation method of a thermal barrier coating, belonging to the field of preparation of thermal barrier coatings, and the method comprises the following steps: preparing a MCrAlY material bonding coating on a thermal barrier coating area on a workpiece by adopting an HVOF spraying mode or an LPPS spraying mode; on the prepared MCrAlY material bonding coating, taking YSZ ceramic powder with a nano structure as a spraying material, spraying by a three-anode plasma spray gun according to specific process parameters, and forcibly cooling the surface of a workpiece by using compressed air in the spraying process to keep the temperature of a substrate of the workpiece below 150 ℃; spraying to the set coating thickness, stopping the forced cooling of the compressed air, and naturally cooling the workpiece and the coating to finish the preparation of the thermal barrier coating. The method can realize the rapid preparation of the super-thick and large-porosity nano-structure thermal barrier coating with the thickness of more than 2000 microns and the porosity of more than 30 percent.
Description
Technical field
The present invention relates to the preparation field of thermal barrier coating, particularly relate to the method for the ceramic heat-barrier coating of super thick, the open grain of a kind of quick preparation.
Background technology
Thermal Barrier Coating Technologies obtains and develops rapidly from late nineteen eighties to the early 1990s, and be widely used in Aeronautics and Astronautics, the field such as naval vessel, and play a part more and more important in continental rise internal combustion turbine industrial aspect.The heavy duty gas turbine of developed country and advanced engine thermal end pieces nearly all adopt Thermal Barrier Coating Technologies.Key part wherein, for example turbine blade (comprising turning vane and working-blade) working temperature generally all approaches the allowable temperature of its material, if 15 ℃ of now every reductions of turbine blade approximately extend 1 times its creep rupture life.According to NASA experimental result, the temperature that adopts thermal barrier coating can produce 100～300 ℃ is fallen.
The current thermal barrier coating double-deck systems (ceramic coating and metal bonding coating) that adopt more; bonding coat direct and substrate contact is MCrAlY alloy; in order to improve the adhesive property of ceramic topcoats and metallic matrix; protect nickel based super alloy matrix to avoid oxidation simultaneously, conventionally adopt hypersonic flame spraying (HVOF) technology or the preparation of low-voltage plasma spraying (LPPS) technology.Ceramic coating is Y
2o
3partially stabilized ZrO
2(YSZ), be mainly the thermal part under protection hot environment, play heat-blocking action, conventionally utilize the preparation of air plasma spraying (APS) technology.
Research shows that the major cause of thermal barrier coating spalling failure is the stress producing in its military service process: do not mated the thermal stresses and thermal growth oxide (TGO) layer transformation stress producing that cause by thermograde and thermal expansion.
Research shows that the heat-proof quality of thermal barrier coating and its thickness and porosity (hole cumulative volume accounts for the ratio of coating cumulative volume) have direct relation.Thickness is larger, and porosity is higher, and coating heat-proof quality is better.For the ceramic topcoats with same thickness, its porosity improves 1%, and coating thermal conductivity reduces approximately 10%.200～350 microns of aircraft engine thermal barrier coating thickness general requirements, continental rise heavy duty gas turbine engine thermal barrier coating thickness general requirement is greater than 1000 microns.But because heat input is large, hot expansibility such as does not mate at the reason, adopts common plasma spraying to be difficult to obtain thicker thermal barrier coating.Improve the thickness that coating porosity can reduce required thermal barrier coating.
The YSZ coating porosity that adopts traditional normal atmospheric plasma spray coating process to prepare is on the low side, is generally 3.5～10%.Traditional common plasma spraying technology exists electric arc to make spray parameters poor stability in the drift of anode root, (beam spot diameter, is little for powder jet temperature lack of homogeneity, fringing effect is remarkable), ceramic coated material powder feeding rate low (about 40g/min) causes that production efficiency is low, spray distance is short (about 90mm), spray time length causes the problems such as the input of matrix heat is large.And then unrelieved stress to coating, bonding strength, homogeneity, heat-proof quality and matrix thermal distortion produce larger negative effect.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of preparation method of thermal barrier coating, can prepare the thermal barrier coating of super thick, open grain, thereby it is long to solve existing thermal barrier coating spray time, the problem that thickness is little, porosity is on the low side of coating.
For solving the problems of the technologies described above, the invention provides a kind of preparation method of thermal barrier coating, comprising:
On workpiece, preparing thermal barrier coating region adopts HVOF spraying method or LPPS spraying method to prepare MCrAlY material binding coating;
In the MCrAlY material binding coating completing in described preparation, take nanostructure YSZ ceramic powder as spray material, spray with setup parameter by three anode plasma gunes, in spraying process, adopt pressurized air to force described workpiece surface cooling, the substrate temperature of described workpiece is maintained lower than 150 ℃;
Be sprayed into the coat-thickness of setting, stop pressurized air pressure cooling, make workpiece and coating naturally cooling, complete the preparation of thermal barrier coating.
Beneficial effect of the present invention is: owing to adopting MCrAlY material to prepare bonding coat, and spray nanostructure YSZ ceramic powder by three anode plasma gunes and prepare thermal barrier coating, can realize and prepare fast thickness and be greater than the nanostructured thermal barrier coatings that 2000 microns, porosity are greater than 30% super thick, open grain.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, below the accompanying drawing of required use during embodiment is described is briefly described, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, do not paying under the prerequisite of creative work, can also obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 is the microstructure figure of porosity prepared by the method for the embodiment of the present invention heat barrier ceramic coating that is 40.5%.
Embodiment
Below the technical scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is only the present invention's part embodiment, rather than whole embodiment.Based on embodiments of the invention, those of ordinary skills, not making the every other embodiment obtaining under creative work prerequisite, belong to protection scope of the present invention.
The embodiment of the present invention provides a kind of preparation method of thermal barrier coating, can prepare fast super thick, open grain thermal barrier coating, and the method comprises the following steps:
On workpiece, preparing thermal barrier coating region adopts HVOF spraying method or LPPS spraying method to prepare MCrAlY material binding coating;
In the MCrAlY material binding coating completing in described preparation, take nanostructure YSZ ceramic powder as spray material, spray with setup parameter by three anode plasma gunes, in spraying process, adopt pressurized air to force described workpiece surface cooling, the substrate temperature of described workpiece is maintained lower than 150 ℃;
Be sprayed into the coat-thickness of setting, stop described compressed-air actuated pressure cooling, make described workpiece and coating naturally cooling, complete the preparation of thermal barrier coating.
In above-mentioned preparation method, before preparation MCrAlY material binding coating, comprising: adopt thermospray special protection adhesive tape or mechanical protection mode to protect to the region of preparing on workpiece outside thermal barrier coating region.
In above-mentioned preparation method, the nanostructure YSZ ceramic powder of employing is that spray material is: powder granularity is distributed as 15～125 microns, and powder chemical composition is 6～9Wt.% } Y
2o
3partially stabilized ZrO
2, powder grain size is nano level spray material.
In above-mentioned preparation method, the nanostructure YSZ ceramic powder that nanostructure YSZ ceramic powder adopts Beijing Mine and Metallurgy General Inst to produce.
In above-mentioned preparation method, the parameter spraying by three anode plasma gunes is: powder jet speed is 200～300m/s, and powder feeding rate is 100～300g/min, and spray distance is 120～50mm.
Method of the present invention, employing has nanostructure YSZ powder and the three anode plasma spray systems that particular size distributes, prepared thermal barrier coating thickness can be greater than 2000 microns, porosity is greater than 30%, powder feeding rate is up to the more than 3 times of common plasma spray coating process, realized the object of super thick, the open grain thermal barrier coating of quick preparation; Because spray time shortens and spray distance prolongation, can effectively reduce matrix heat input (substrate temperature is lower than 150 ℃), reduce workpiece deformation, and then improved the work-ing life of coating.Can mainly apply but be not limited to the heat insulation protection of various aircraft engines, continental rise gas turbine engine hot-end component, thereby reduced, the heat input of basic material of blade is reduced to coating residualinternal stress, preparation porosity is greater than 30%, the thermal barrier coating that thickness is greater than 2000 microns.Solve the problem of super thick, the open grain thermal barrier coating of how fast preparation.There is higher production efficiency, coat-thickness homogeneity.Heat-proof quality and the work-ing life of coating are improved.
Below in conjunction with specific embodiment, the invention will be further described
Preparation method of the present invention, before spraying, adopt HVOF technology or LPPS technology to prepare MCrAlY material binding coating at workpiece surface, before preparation MCrAlY material binding coating, to adopting thermospray special protection adhesive tape or mechanical means to protect without coating area;
Adopt Beijing Mine and Metallurgy General Inst to produce the nanostructure YSZ ceramic powder of (or thering is equal performance perameter), the three anode plasma gunes (DELTA) by multi-spindle machining hand (also can adopt craft) clamping spray with setup parameter, in spraying process, adopt pressurized air to force workpiece surface cooling, substrate temperature is maintained below 150 ℃;
Continuous spray, to the coat-thickness of setting, stops pressurized air pressure cooling, makes workpiece and coating naturally cooling;
Remove protection adhesive tape and other safety guards, complete the preparation of thermal barrier coating.
The method can realize to be prepared fast thickness and is greater than the nanostructured thermal barrier coatings (signal of preparation coating is referring to Fig. 1) that 2000 microns, porosity are greater than 30% super thick, open grain.
Embodiment 1
First adopt appropriate ways to be installed workpiece to be sprayed fixing, dry up surface with pure pressurized air, and the matrix of workpiece is protected without coating position with thermospray special protection adhesive tape or other mechanical means;
Thorough cleaning powder feeder, powder conveying pipe, spray gun, and keep spraying clean environment pollution-free, in spraying process, keep larger ventilation and dust removal air quantity, guarantee the introducing of spraying process inclusion-free;
Adopt Beijing Mine and Metallurgy General Inst to produce the nanostructure YSZ ceramic powder of (or thering is equal performance perameter), spray with setup parameter by three anode plasma gunes (DELTA) of multi-spindle machining hand (also can adopt craft) clamping.In spraying process, adopt pressurized air to force workpiece surface cooling, the substrate temperature of workpiece is maintained below 150 ℃;
Be sprayed into the coat-thickness of setting, stop pressurized air pressure cooling, make workpiece and coating naturally cooling.
Remove protection adhesive tape and other safety guards, complete the preparation of thermal barrier coating.
The above; only for preferably embodiment of the present invention, but protection scope of the present invention is not limited to this, is anyly familiar with in technical scope that those skilled in the art disclose in the present invention; the variation that can expect easily or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (5)
1. a preparation method for thermal barrier coating, is characterized in that, comprising:
On workpiece, preparing thermal barrier coating region adopts HVOF spraying method or LPPS spraying method to prepare MCrAlY material binding coating;
In the MCrAlY material binding coating completing in described preparation, take nanostructure YSZ ceramic powder as spray material, spray by setup parameter by three anode plasma gunes, in spraying process, adopt pressurized air to force described workpiece surface cooling, the substrate temperature of described workpiece is maintained lower than 150 ℃;
Be sprayed into the coat-thickness of setting, stop described compressed-air actuated pressure cooling, make described workpiece and coating naturally cooling, complete the preparation of thermal barrier coating.
2. the preparation method of barrier coating as claimed in claim 1 generates heat; it is characterized in that; before preparation MCrAlY material binding coating, comprising: adopt thermospray special protection adhesive tape or mechanical protection mode to protect to the region of preparing on workpiece outside thermal barrier coating region.
3. generate heat the as claimed in claim 1 preparation method of barrier coating, is characterized in that, the nanostructure YSZ ceramic powder of described employing is that spray material is: powder granularity is distributed as 15～125 microns, and powder chemical composition is 6～9Wt.% } Y
2o
3partially stabilized ZrO
2, powder grain size is nano level spray material.
4. generate heat as described in claim 1 or 3 preparation method of barrier coating, is characterized in that the nanostructure YSZ ceramic powder that described nanostructure YSZ ceramic powder adopts Beijing Mine and Metallurgy General Inst to produce.
5. generate heat the as claimed in claim 1 preparation method of barrier coating, is characterized in that, the described setup parameter spraying by three anode plasma gunes is:
Powder jet speed is 200～300m/s, and powder feeding rate is 100～300g/min, and spray distance is 120～50mm.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104357785A (en) * | 2014-11-14 | 2015-02-18 | 北京矿冶研究总院 | Method for rapidly preparing high-purity yttrium oxide coating for plasma etching machine |
| CN104451526A (en) * | 2014-11-17 | 2015-03-25 | 北京理工大学 | Preparation method of high-emissivity ceramic coating |
| CN105506532A (en) * | 2015-12-08 | 2016-04-20 | 中国航空工业集团公司成都飞机设计研究所 | Cooling method for thermal spraying |
| CN106867284A (en) * | 2016-12-29 | 2017-06-20 | 陕西华秦科技实业有限公司 | The preparation method of the effective protective coating material of zirconium alloy cladding |
| CN113929474A (en) * | 2021-12-16 | 2022-01-14 | 矿冶科技集团有限公司 | Particulate matter for thermal barrier coating, preparation method of particulate matter, thermal barrier coating and engine |
| CN114686794A (en) * | 2022-03-30 | 2022-07-01 | 北京科技大学 | Preparation method of nano YSZ/NiCoCrAlYTa composite coating on TiAl alloy surface |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104357785A (en) * | 2014-11-14 | 2015-02-18 | 北京矿冶研究总院 | Method for rapidly preparing high-purity yttrium oxide coating for plasma etching machine |
| CN104451526A (en) * | 2014-11-17 | 2015-03-25 | 北京理工大学 | Preparation method of high-emissivity ceramic coating |
| CN104451526B (en) * | 2014-11-17 | 2017-01-25 | 北京理工大学 | Preparation method of high-emissivity ceramic coating |
| CN105506532A (en) * | 2015-12-08 | 2016-04-20 | 中国航空工业集团公司成都飞机设计研究所 | Cooling method for thermal spraying |
| CN106867284A (en) * | 2016-12-29 | 2017-06-20 | 陕西华秦科技实业有限公司 | The preparation method of the effective protective coating material of zirconium alloy cladding |
| CN106867284B (en) * | 2016-12-29 | 2019-03-08 | 陕西华秦科技实业有限公司 | The preparation method of the effective protective coating material of zirconium alloy cladding |
| CN113929474A (en) * | 2021-12-16 | 2022-01-14 | 矿冶科技集团有限公司 | Particulate matter for thermal barrier coating, preparation method of particulate matter, thermal barrier coating and engine |
| CN113929474B (en) * | 2021-12-16 | 2022-03-04 | 矿冶科技集团有限公司 | Particulate matter for thermal barrier coating, preparation method of particulate matter, thermal barrier coating and engine |
| CN114686794A (en) * | 2022-03-30 | 2022-07-01 | 北京科技大学 | Preparation method of nano YSZ/NiCoCrAlYTa composite coating on TiAl alloy surface |
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Application publication date: 20140507 |