CN105441860A - Novel SiC whisker reinforced gas turbine blade composite coating and preparation method thereof - Google Patents
Novel SiC whisker reinforced gas turbine blade composite coating and preparation method thereof Download PDFInfo
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- CN105441860A CN105441860A CN201510770746.5A CN201510770746A CN105441860A CN 105441860 A CN105441860 A CN 105441860A CN 201510770746 A CN201510770746 A CN 201510770746A CN 105441860 A CN105441860 A CN 105441860A
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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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
-
- 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
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- 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
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/341—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one carbide layer
-
- 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
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
Abstract
The invention provides a novel SiC whisker reinforced gas turbine blade composite coating. The composite coating comprises a MCrAlY layer, a SiC whisker layer and a ceramic layer which are coated on a gas turbine blade high-temperature alloy base body in sequence. The invention further discloses a preparation method of the composite coating. The method comprises the steps that 1, the MCrAlY layer prepared through MCrAlY is sprayed on the gas turbine blade high-temperature alloy base body; 2, SiC powder is pressed into a powder layer on the MCrAlY layer through the cold isostatic pressing method, and then the powder layer is vertically irradiated through laser beams, so that the SiC whisker layer grows and is formed in the home position of the SiC powder; and 3, the ceramic layer is coated on the surface of the SiC whisker layer. The SiC whisker layer has the higher roughness, the composite coating composed of the MCrAlY layer and the SiC whisker layer serves as the bonding layer of a thermal barrier coating, and thus the cohesive force of the thermal barrier coating can be improved, and the thermal barrier coating is prevented from being peeled off untimely; in addition, SiC whisker has the excellent heat resistance and corrosion resistance, so that the high-temperature oxidation resistance of blades is improved.
Description
Technical field
The present invention relates to a kind of New Si C whisker reinforcement gas turbine blades compound coating and preparation method thereof, can be used as the tack coat of internal combustion turbine stator blades and rotor blade thermal barrier coating, the high temperature oxidation resistance of high-temperature alloy blades and the cohesiveness of thermal barrier coating can be improved.
Background technology
Current, the economic situation of China's fast development for the demand sustainable growth of electric power, but mainly to use and the coal-fired steam turbine of being on active service exists the series of problems such as inefficiency, the wasting of resources now.The problem of environmental pollution thereupon produced constantly was worsening especially in recent years, and haze weather is day by day serious.And address these problems one large outlet uses efficient joint cycle combustion turbine group to substitute conventional vapor turbine exactly.As the core component of internal combustion turbine, under blade needs to be exposed to high-temperature and high-stress environment usually, so the high temperature alloy being used for manufacturing gas turbine blades needs to have the mechanical properties such as excellent high temperature creep-resisting, require again outstanding high temperature oxidation resistance simultaneously.Therefore, in order to improve the mechanical behavior under high temperature of material, often need to add the alloying elements such as vanadium, molybdenum, tungsten in the base, reduce the content of aluminium (effect of resistance to high temperature corrosion can be played) element simultaneously, cause the alloy material prepared to be difficult to have good mechanical behavior under high temperature and resistance to high temperature corrosion performance simultaneously.As terms of settlement, generally can apply the coating of high temperature oxidation corrosion resistance at matrix surface, thus play the effect that protection has the superalloy matrix of excellent high temperature mechanical property.
Be applied to the coating of gas turbine blades high temperature oxidation protection mainly using MCrAlY as the thermal barrier coating system of tack coat; MCrAlY coating M refers to Fe, Ni, Co etc., and Cr is exactly Metal Cr, and Al is exactly metal A l; Y refers to rare earth element y, is exactly the high aluminide coating that rare earth element improves.Under gas turbine engine working conditions, tack coat temperature has exceeded 700 DEG C, and tack coat can be caused to be oxidized, and forms 1-10 μm of thick thermal growth oxide (TGO) at tack coat and ceramic layer.(main component is Al to form TGO layer fine and close continuously at tack coat and ceramic layer interface
2o
3), can slow down oxidation rate, be useful to the oxidation-resistance improving tack coat.But, formation due to TGO is a volume expansion process, interface can limit this volume change, and the thermal expansivity of TGO and tack coat metal differs greatly, therefore, when TGO is formed, unrelieved stress can be there is therein thereupon, when being cooled to envrionment temperature, the unrelieved stress that thermal mismatching causes can increase further, and stress is increased to and to a certain degree will forms hierarchical crack at tack coat/ceramic layer interface and cause disbonding to lose efficacy.So in blade military service process, tack coat/ceramic layer interface is the weak link of thermal barrier coating.
Summary of the invention
First object of the present invention is to provide a kind of and has excellent bonding force and high temperature oxidation protective value thus the New Si C whisker reinforcement gas turbine blades compound coating avoided thermal barrier coating to peel off too early and lost efficacy.
First object of the present invention is realized by following technical measures: a kind of New Si C whisker reinforcement gas turbine blades compound coating, is characterized in that: it comprises the MCrAlY layer, SiC whisker layer and the ceramic layer that are coated in successively on gas turbine blades superalloy matrix.
The present invention adopts SiC whisker layer, it has higher roughness than conventional MCrAlY layer, the compound coating be made up of MCrAlY layer and SiC whisker layer is as the tack coat of thermal barrier coating, the cohesive force of thermal barrier coating can be improved, prevent thermal barrier coating from peeling off too early, SiC whisker has excellent thermotolerance and erosion resistance simultaneously, improves the high temperature oxidation resistance of blade.
Principle of the present invention is: under arms in process, in SiC whisker coating, long whisker hinders germinating and the expansion of tack coat/ceramic layer interface debonding crackle by bridge joint, the mechanism of extracting etc., thus improve the bonding force of tack coat and ceramic layer, solve existing tack coat/ceramic layer interface and easily generate hierarchical crack and cause the problem of disbonding.
As one embodiment of the present invention, in described MCrAlY layer, M refers to the combination of Ni or Co or NiCo, become to be grouped into (mass percent): M (10 ~ 30Cr) (5 ~ 15Al) (0.5 ~ 1Y), remaining as Ni or Co or NiCo combination; The composition of SiC whisker layer is (mass percent): Si50C50; The composition of ceramic layer is (mass percent) 6 ~ 8%Y
2o
3partially stabilized ZrO
2.
As a kind of preferred implementation of the present invention, described MCrAlY layer thickness is 100 ~ 200 microns.
As a kind of preferred implementation of the present invention, described SiC whisker layer thickness is 40 ~ 100 microns.
As a kind of preferred implementation of the present invention, described ceramic layer thickness is 100 ~ 300 microns.
Second object of the present invention is the preparation method providing a kind of above-mentioned New Si C whisker reinforcement gas turbine blades compound coating.
Second object of the present invention is realized by following technical measures: a kind of preparation method of above-mentioned New Si C whisker reinforcement gas turbine blades compound coating, is characterized in that comprising the following steps:
(1) gas turbine blades superalloy matrix sprays MCrAlY and prepare MCrAlY layer;
(2) on MCrAlY layer, adopt cold isostatic pressing process that SiC powder is pressed into bisque, then use laser beam vertical irradiation bisque, make SiC powder growth in situ form SiC whisker layer;
(3), at the surface-coated ceramic layer of SiC whisker layer, obtain New Si C whisker reinforcement gas turbine blades compound coating.
As a modification of the present invention, before preparation MCrAlY layer, gas turbine blades superalloy matrix is heat-treated and shot blasting on surface process, meets the requirements to make its surface quality.
As one embodiment of the present invention, described MCrAlY layer is by carrying out low-voltage plasma spraying at superalloy matrix surface or hypersonic flame spraying prepares.
As one embodiment of the present invention, the compound coating that MCrAlY layer and SiC whisker layer are formed prepares ZrO by plasma spray coating process
2base ceramic layer.
As a kind of preferred implementation of the present invention, described MCrAlY layer thickness is 100 ~ 200 microns, and described SiC whisker layer thickness is 40 ~ 100 microns, and described ceramic layer thickness is 100 ~ 300 microns.
Compared with prior art, the present invention has following significant effect:
The present invention adopts SiC whisker layer, it has higher roughness than conventional MCrAlY layer, the compound coating be made up of MCrAlY layer and SiC whisker layer is as the tack coat of thermal barrier coating, the cohesive force of thermal barrier coating can be improved, prevent thermal barrier coating from peeling off too early, SiC whisker has excellent thermotolerance and erosion resistance simultaneously, improves the high temperature oxidation resistance of blade.Under arms in process, in SiC whisker coating, long whisker hinders germinating and the expansion of tack coat/ceramic layer interface debonding crackle by bridge joint, the mechanism of extracting etc., thus improve the bonding force of tack coat and ceramic layer, solve existing tack coat/ceramic layer interface and easily generate hierarchical crack and cause the problem of disbonding.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Fig. 1 is structural representation of the present invention.
Embodiment
The present embodiment is using the MGA1400 high-temperature alloy blades of Mitsubishi's combustion engine use as superalloy matrix 1, and its concrete composition (weight percent) is as follows:
| Element | Co | Cr | Mo | W | Al | Ti | Ta | C | Zr |
| Wt％ | 10 | 14 | 1.5 | 4 | 4 | 3 | 5 | 0.08 | 0.03 |
(table 1)
As shown in Figure 1, be a kind of New Si C whisker reinforcement of the present invention gas turbine blades compound coating, it comprises the MCrAlY layer 2, SiC whisker layer 3 and the ceramic layer 4 that are coated in successively on gas turbine blades superalloy matrix 1 (MGA1400 high-temperature alloy blades).In MCrAlY layer, M refers to the combination of Ni or Co or NiCo, composition range (mass percent): M (10 ~ 30Cr) (5 ~ 15Al) (0.5 ~ 1Y), remaining as Ni or Co or NiCo combination; The composition of SiC whisker layer is (mass percent): Si50C50; The composition of ceramic layer is (mass percent) 6-8%Y
2o
3partially stabilized ZrO
2.MCrAlY layer thickness is 100 ~ 200 microns, and SiC whisker layer thickness is 40 ~ 100 microns, and ceramic layer thickness is 100 ~ 300 microns.
A preparation method for above-mentioned New Si C whisker reinforcement gas turbine blades compound coating, comprises the following steps:
(1) MGA1400 high-temperature alloy blades is heat-treated as requested and the process such as shot blasting on surface, meet the requirements to make its surface quality, gas turbine blades superalloy matrix sprays MCrAlY and prepares MCrAlY layer, specifically: the high-temperature alloy blades handled well prepares by low-voltage plasma spraying or hypersonic flame spraying the MCrAlY layer that thickness is 100 ~ 200 microns, M selects Ni, the elements such as Co, in the present embodiment, specifically select NiCoCrAlY layer.
(2) on MCrAlY layer, adopt cold isostatic pressing process that SiC powder is pressed into bisque, then use laser beam vertical irradiation bisque, make SiC powder growth in situ form SiC whisker layer.Specifically: on MCrAlY upper layer, suppress the SiC powder that one deck median size is 20nm by cold isostatic pressing process at blade surface, thickness is 100 microns, more at the uniform velocity irradiates perpendicular to blade surface with laser beam, make SiC whisker in-situ grow to form.Laser parameter: sweep velocity is 0.1m/s, spot diameter is 0.2mm, and laser power is 400W.
(3), at the surface-coated ceramic layer of SiC whisker layer, the compound coating specifically formed at MCrAlY layer and SiC whisker layer prepares ZrO by plasma spray coating process
2base ceramic layer, obtains New Si C whisker reinforcement gas turbine blades compound coating.
Principle of the present invention is: under arms in process, in SiC whisker coating, long whisker hinders germinating and the expansion of tack coat/ceramic layer interface debonding crackle A by bridge joint, the mechanism of extracting etc., thus improve the bonding force of tack coat and ceramic layer, stop peeling off in advance of thermal barrier coating.
Embodiments of the present invention are not limited thereto; according to foregoing of the present invention; according to ordinary technical knowledge and the customary means of this area; do not departing under the present invention's above-mentioned basic fundamental thought prerequisite; the present invention can also make the amendment of other various ways, replacement or change, all drops within rights protection scope of the present invention.
Claims (10)
1. a New Si C whisker reinforcement gas turbine blades compound coating, is characterized in that: it comprises the MCrAlY layer, SiC whisker layer and the ceramic layer that are coated in successively on gas turbine blades superalloy matrix.
2. New Si C whisker reinforcement gas turbine blades compound coating according to claim 1, it is characterized in that: in described MCrAlY layer, M refers to the combination of Ni or Co or NiCo, composition range (mass percent): M (10 ~ 30Cr) (5 ~ 15Al) (0.5 ~ 1Y), remaining as Ni or Co or NiCo combination; The composition of SiC whisker layer is (mass percent): Si50C50; The composition (mass percent) of ceramic layer is 6 ~ 8%Y
2o
3partially stabilized ZrO
2.
3. New Si C whisker reinforcement gas turbine blades compound coating according to claim 1 and 2, is characterized in that: described MCrAlY layer thickness is 100 ~ 200 microns.
4. New Si C whisker reinforcement gas turbine blades compound coating according to claim 3, is characterized in that: described SiC whisker layer thickness is 40 ~ 100 microns.
5. New Si C whisker reinforcement gas turbine blades compound coating according to claim 4, is characterized in that: described ceramic layer thickness is 100 ~ 300 microns.
6. the feature of a New Si C whisker reinforcement gas turbine blades compound coating according to claim 1 is to comprise the following steps:
(1) on gas turbine blades superalloy matrix, spray MCrAlY and prepare MCrAlY layer;
(2) on MCrAlY layer, adopt cold isostatic pressing process that SiC powder is pressed into bisque, then use laser beam vertical irradiation bisque, make SiC powder growth in situ form SiC whisker layer;
(3), at the surface-coated ceramic layer of SiC whisker layer, obtain New Si C whisker reinforcement gas turbine blades compound coating.
7. preparation method according to claim 6, is characterized in that: before preparation MCrAlY layer, heat-treat and shot blasting on surface process, meet the requirements to make its surface quality to gas turbine blades superalloy matrix.
8. preparation method according to claim 7, is characterized in that: described MCrAlY layer is by carrying out low-voltage plasma spraying at superalloy matrix surface or hypersonic flame spraying prepares.
9. preparation method according to claim 8, is characterized in that: on the compound coating that MCrAlY layer and SiC whisker layer are formed, prepare ZrO by plasma spray coating process
2base ceramic layer.
10. the preparation method according to any one of claim 6 ~ 9, is characterized in that: described MCrAlY layer thickness is 100 ~ 200 microns, and described SiC whisker layer thickness is 40 ~ 100 microns, and described ceramic layer thickness is 100 ~ 300 microns.
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| CN201510770746.5A CN105441860A (en) | 2015-11-12 | 2015-11-12 | Novel SiC whisker reinforced gas turbine blade composite coating and preparation method thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109207900A (en) * | 2018-11-12 | 2019-01-15 | 中国兵器工业第五九研究所 | Composite coating and preparation method thereof, surface treatment method of titanium alloy and application |
| CN109608176A (en) * | 2018-12-18 | 2019-04-12 | 辽宁省轻工科学研究院有限公司 | A kind of novel ablation dimension shape fiber coat and preparation, construction method |
| CN111848196A (en) * | 2020-07-24 | 2020-10-30 | 北京航空航天大学 | Preparation method of in-situ silicon carbide nanowire toughened silicon carbide ceramic |
| CN112095100A (en) * | 2020-08-20 | 2020-12-18 | 西安交通大学 | Blade tip cutting coating with super-strong physical wettability and preparation method thereof |
| CN112321331A (en) * | 2020-11-18 | 2021-02-05 | 江西信达航科新材料科技有限公司 | High-temperature-resistant antioxidant composite coating and preparation process thereof |
| CN113564512A (en) * | 2021-07-23 | 2021-10-29 | 中国民航大学 | Method for preparing whisker toughened plasma spraying ceramic matrix sealing coating |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109207900A (en) * | 2018-11-12 | 2019-01-15 | 中国兵器工业第五九研究所 | Composite coating and preparation method thereof, surface treatment method of titanium alloy and application |
| CN109608176A (en) * | 2018-12-18 | 2019-04-12 | 辽宁省轻工科学研究院有限公司 | A kind of novel ablation dimension shape fiber coat and preparation, construction method |
| CN109608176B (en) * | 2018-12-18 | 2021-11-05 | 辽宁省轻工科学研究院有限公司 | Ablation fiber-shaped coating and preparation and construction methods thereof |
| CN111848196A (en) * | 2020-07-24 | 2020-10-30 | 北京航空航天大学 | Preparation method of in-situ silicon carbide nanowire toughened silicon carbide ceramic |
| CN112095100A (en) * | 2020-08-20 | 2020-12-18 | 西安交通大学 | Blade tip cutting coating with super-strong physical wettability and preparation method thereof |
| CN112095100B (en) * | 2020-08-20 | 2021-12-28 | 西安交通大学 | Blade tip cutting coating with super-strong physical wettability and preparation method thereof |
| CN112321331A (en) * | 2020-11-18 | 2021-02-05 | 江西信达航科新材料科技有限公司 | High-temperature-resistant antioxidant composite coating and preparation process thereof |
| CN113564512A (en) * | 2021-07-23 | 2021-10-29 | 中国民航大学 | Method for preparing whisker toughened plasma spraying ceramic matrix sealing coating |
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