CN101768380B - Thermal protection coating with component gradient change and preparation method - Google Patents
Thermal protection coating with component gradient change and preparation method Download PDFInfo
- Publication number
- CN101768380B CN101768380B CN200910247732.XA CN200910247732A CN101768380B CN 101768380 B CN101768380 B CN 101768380B CN 200910247732 A CN200910247732 A CN 200910247732A CN 101768380 B CN101768380 B CN 101768380B
- Authority
- CN
- China
- Prior art keywords
- thermal protection
- protection coating
- layer
- substrate
- preparation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Coating By Spraying Or Casting (AREA)
Abstract
The invention belongs to the field of inorganic materials, particularly relates to a thermal protection coating with component gradient change and a preparation method. The thermal protection coating comprises two components of M1 and M2, wherein the M1 is selected from one of YSZ, lanthanum aluminate, mulite or BSAS, the M2 is selected from one of Ln2Zr2O7, Ln2Ce2O7, Ln2SiO5, Ln2Si2O7 or MoSi2, and Ln is selected from rare earth elements the atom coefficients of which are 57-71, Y or Sc. The thermal protection coating has the characteristics of good coating compactness, high bonding strength with a substrate, low thermal conductivity and the like and has favorable thermal shock resistance.
Description
Technical field
The invention belongs to field of inorganic materials, be specifically related to thermal protection coating and the preparation method of the change of a kind of component gradient.
Background technology
Along with internal combustion turbine is towards the development in high thrust-weight ratio, high efficiency direction, the inlet temperature of combustion gas needs to improve further, parts in combustion chamber are threatened bearing larger high temperature failure, this threat not only comprises parts melting at high temperature, phase transformation, also has the threat from the water vapor in combustion gas environment, corrosive impurity simultaneously.The most feasible, the most effective terms of settlement deposits one deck thermal protection coating at these substrate surfaces, barrier together with being formed between substrate with combustion gas environment exactly at present, hinders combustion gas environment to the direct impact of base material, thus the work-ing life of elongate member.
At present, the coating of single-material is widely used, although can alleviate above-mentioned threat to a certain extent, its obstruction ability and all receive the restriction of material self character work-ing life, also exists some shortcomings part.Such as conventional YSZ (Y
2o
3stable ZrO
2) there is the thermal expansivity mated very much with metal base, but easy phase transformation more than 1200 DEG C; And La
2zr
2o
7although there is very excellent high-temperature-phase stability but comparatively large with the thermal expansion coefficient difference of substrate, easily after repeatedly thermal cycling, produces microstress, cause coating failure.
So, how to fully utilize the advantage of various material, learn from other's strong points to offset one's weaknesses, prepare and both there is good heat-proof quality, the coating can mated with the physics of substrate, chemical property again, alleviating the thermal stresses of coating and substrate, coating and painting interlayer, is the current important directions studied.
Functionally gradient coating is a class by the continuous or quasi-continuous change of structure and element, obtain performance corresponding to structure and the change of composition the inhomogeneous composite materials of gradual change.In thermal protection coating, introduce the thought of gradient cladding, coated component and textural element are changed gradually along its thickness direction, coating performance is continuous gradient change, is slow down coat inside stress concentration, improves one of effective method of anchoring strength of coating.
Summary of the invention
The object of the present invention is to provide the thermal protection coating that a kind of component gradient changes, this thermal protection coating is applicable to superalloy substrate, carbon fibre reinforced silicon carbide (C/SiC) substrate, silicon carbide fiber reinforced silicon carbide substrate (SiC/SiC) or Si
3n
4substrate; And this thermal protection coating comprises two kinds of composition: M1 and M2; Described M1 is selected from YSZ (that is: Yttria-Stabilized Zirconia, Yttria stabilized zirconia), lanthanum aluminate, (chemical formula is Al to mullite
xsi
2-xo
5.5-0.5x, wherein x represents mol ratio, and x preferable range is 0.2 ~ 1.8, more preferably 0.5 ~ 1.5) or BSAS (BaO-SrO-Al
2o
3-SiO
2) in one; M
2be selected from: Ln
2zr
2o
7, Ln
2ce
2o
7, Ln
2siO
5, Ln
2si
2o
7or MoSi
2in one, wherein Ln is selected from rare earth element, Y or Sc of atom coefficient 57 ~ 71.
Preferably, described superalloy substrate is selected from: the titanium alloy-based end, TiAl alloy substrate, TiAlV alloy substrates or TiAlNb alloy substrates.
Preferably, described lanthanum aluminate is selected from: lanthanum titanium aluminate (LaTi
2al
9o
19) or lanthanum zirconium aluminate (ZrTi
2al
9o
19).
Preferably, described Ln is preferably: La, Gd, Sm or Yb.
Preferably, described M2 is selected from La
2zr
2o
7, La
2ce
2o
7, Gd
2zr
2o
7, Sm
2zr
2o
7, MoSi
2, Yb
2si
2o
7, Yb
2siO
5, Sm
2zr
2o
7in one.
Preferably, described thermal protection coating is made up of the matrix material of 2 ~ 10 layers, and from the 1st layer to last one deck, M
1mass percentage successively successively decrease from 100% ~ 0%, M
2mass percentage successively increase progressively from 0% ~ 100%; In every layer, M
1with M
2mass percentage sum be 100%.
Described the first layer refers to the one deck directly contacted with base material, and described last one deck refers to and base material distance one deck farthest.
Preferably, described M
1thermal expansivity (M
1), M
2thermal expansivity (M
2), there is following relation between the thermal expansivity (S) of substrate: | (M
1)-(S) | < | (M
2)-(S) |, and (M
1) ≈ (S), further preferably, meet | (M1)-(S) |≤5 × 10
-6/ DEG C.
The thermal expansivity of above-mentioned M1, M2 and S the reason of condition that meets be: the thermal expansivity of M1 layer and the thermal expansivity of substrate should as much as possible close to or identical, M2 plays the stable effect of high-temperature-phase on this basis, difference of thermal expansion coefficient between this high-temperature stable phase and substrate must be greater than the difference between M1 and substrate, can while playing high-temperature-phase stabilization, make coated material and substrate match like this.
Preferably, the total thickness of described thermal protection coating is greater than 100 μm, more preferably 200 μm ~ 900 μm.
Preferably, the thickness of every one deck matrix material of described thermal protection coating is 20 ~ 400 μm, and meets total thickness and be greater than 100 μm.
The preparation method of the thermal protection coating of component gradient change of the present invention comprises the steps:
(1) preparation of composite granule: in proportion by M
1powder, M
2powder mixes with mixed pulvis and carries out ball milling, and powder is mixed, and after drying, granulation obtains composite granule, and each layer composite granule is prepared respectively;
(2) pre-treatment is sprayed: pre-treatment is carried out to substrate surface;
(3) spray gradient cladding: adopt plasma spraying method, by step 1) in composite granule after obtained granulation to be successively sprayed in pretreated substrate i.e. this thermal protection coating obtained successively.
Preferably, described step 1) in mixed pulvis be selected from one or both mixture in second alcohol and water.
Preferably, described step 1) in, and mixed pulvis compares M
1powder and M
2the ratio of powder quality sum is 1: 3 ~ 8, more preferably 1: 5.
Preferably, described step 1) in the particle diameter of composite granule be 30 μm ~ 100 μm.
Preferably, described step 1) drying temperature be 80 DEG C ~ 110 DEG C, time of drying is 2 ~ 5 hours.
Preferably, described step 2) in, when adopting alloy substrates, described pre-treatment step comprises: oil removing and sandblasting alligatoring, that is: in the molten oil-based solvent wiping alloy substrates of use, then spray one deck transition layer NiCoCrAlY at alloy substrates surface plasma, thickness is 30 ~ 80 μm; When adopting silicon based composite material substrate, described pre-treatment step comprises: sandblasting alligatoring, that is: direct spraying transition layer SiO
2.
Preferably, described molten oiliness reagent is ethanol.
Preferably, described sandblasting alligatoring is this area routine techniques, and those skilled in the art can determine according to prior art.
Preferably, described step 3) in the processing parameter of spraying be: electric current 500A ~ 700A, ar pressure is 0.70Mpa ~ 0.9Mpa, and hydrogen pressure is 0.2Mpa ~ 0.4Mpa, and spray distance is 70mm ~ 150mm.
Preferably, described step 3) in, the total thickness of thermal protection coating is 200 μm ~ 900 μm, and the thickness of each individual layer is equal.
The thermal protection coating of component gradient change of the present invention has following advantage:
1. coating thermal conductivity is low: the thermal conductivity measurement of gradient cladding is 0.85J/ (gK), suitable with the thermal conductivity of stack pile pure M2 coating;
2. coating microtexture is even, without component segregation, and the microdefects such as non-microcracked, pore;
3. combining M1 and M2 bi-material advantage separately, by regulating the graded of component to make the thermal expansivity of coating also present graded from inside to outside, thus reducing the thermal stresses concentration problem between coating and substrate;
4. the present invention design gradient cladding and existing single ceramic coating, double ceramic coating system is compared, and its thermal shock resistance is more excellent, and has higher hardness and intensity;
5. preparation technology of coating of the present invention is simple, and repeatability is good.
Accompanying drawing explanation
Fig. 1: La
2zr
2o
7the scanning electron microscopic picture in-YSZ gradient cladding cross section.
Fig. 2: La
2zr
2o
7the electron probe microanalysis (EPMA) figure in-YSZ gradient cladding cross section.
Fig. 3: La
2zr
2o
7temperature-thermal conductivity the curve of-YSZ gradient cladding.
Fig. 4: La
2zr
2o
7-YSZ gradient cladding thermal shock number of times-mass-change curve.
Fig. 5: La before and after experiment
2zr
2o
7the contrast of-YSZ gradient cladding surface topography.
Embodiment
The present invention is further illustrated below by embodiment and comparative example.
Embodiment 1: at Ni based high-temperature alloy substrate upper plasma spraying La
2zr
2o
7-YSZ gradient cladding, coating is by six layers of La
2zr
2o
7-YSZ matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 80%, La
2zr
2o
720%;
Third layer: YSZ 60%, La
2zr
2o
740%;
4th layer: YSZ 40%, La
2zr
2o
760%;
Layer 5: YSZ 20%, La
2zr
2o
780%;
Layer 6: La
2zr
2o
7100%.
Wherein, the M1 used for YSZ, M2 be La
2zr
2o
7, substrate is Ni based high-temperature alloy base, wherein M1 thermal expansivity (M
1)=10.7 × 10-6/ DEG C, M
2thermal expansivity (M
2)=8 × 10-6/ DEG C, between three, there is following relation in thermal expansivity (S)=10.1 × 10-6/ DEG C of substrate: | (M
1)-(S) | < | (M
2)-(S) |, and | (M
1)-(S) |≤5 × 10
-6/ DEG C.
Its preparation method is:
(1) by the YSZ powder of 80% and the La of 20%
2zr
2o
7powder puts into ball mill, adds mixed pulvis (ethanol) and carries out ball milling, and the mass ratio of ethanol and powder is 1: 5.Put it into baking oven inner drying after powder mixes, temperature 100 DEG C, be incubated 5 hours.Obtain 60%YSZ and 40%La in the same way again
2zr
2o
7powder mix; 40%YSZ and 60%La
2zr
2o
7powder mix; 20%YSZ and 80%La
2zr
2o
7powder mix.By above-mentioned mixed powder granulation, its particle diameter is made to be 30 μm ~ 100 μm.
(2) alloy substrate surface carries out oil removing, and sandblasting alligatoring pre-treatment.Afterwards at substrate surface plasma spraying layer of Ni CoCrAlY transition layer, thickness is 50 μm.
(3) adopt plasma spraying method, the above-mentioned composite granule mixed is sprayed in pretreated substrate successively: the first layer 100%YSZ; The second layer 80%YSZ, 20%La
2zr
2o
7; Third layer 60%YSZ, 40%La
2zr
2o
7; 4th layer of 40%YSZ, 60%La
2zr
2o
7; Layer 5 20%YSZ, 80%La
2zr
2o
7; Layer 6 100%La
2zr
2o
7.The processing parameter of spraying is: electric current 600A, ar pressure is 0.8Mpa, and hydrogen pressure is 0.3Mpa, and spray distance is 100mm, total coating thickness 200 μm.
Prepare gained coating as shown in Figure 1, coating cross sections is typical plasma spraying stratiform structure, and microtexture is even, without the tiny crack that unrelieved stress causes.Fig. 2 is the elemental line scan result of gradient cladding interface, wherein: the region of 2 (a) line sweep; The distribution in the coating of 2 (b) La element; The distribution in the coating of 2 (c) Y element.As seen from the figure: the La representated by La element
2zr
2o
7with the YSZ representated by Y element, component presents graded separately along vertical substrate direction, illustrates that the bi-material of composition coating is as being engineered in gradual change in the other direction.
Can be calculated by Fig. 3: the thermal conductivity of gradient cladding is 0.85J/ (gK), with single La
2zr
2o
7the thermal conductivity of coating is suitable, illustrates that gradient cladding remains La
2zr
2o
7the advantage of lower thermal conductivity.
Fig. 4 is La
2zr
2o
7-YSZ gradient cladding thermal shock number of times-mass-change curve.Wherein, thermal shock experiment condition is: rise to 1200 DEG C fast with the temperature rise rate of 10 DEG C/min, and the water putting into about 3 DEG C after being incubated half an hour is extremely cold.As can be seen from curve: after 20 thermal shocks experiment, the quality change of coating only 0.6%.After 20 thermal shocks experiment (T=1200 DEG C), quality change only 0.6% (Fig. 4) of coating, and surface only has fragmentary small area to peel off (Fig. 5), illustrate that the gradient cladding designed by the present invention has good thermal shock resistance.
Embodiment 2:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: La
2zr
2o
7-YSZ gradient cladding is by six layers of La
2zr
2o
7-YSZ matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 70%, La
2zr
2o
730%;
Third layer: YSZ 55%, La
2zr
2o
745%;
4th layer: YSZ 45%, La
2zr
2o
755%;
Layer 5: YSZ 30%, La
2zr
2o
770%;
Layer 6: La
2zr
2o
7100%.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 3:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: La
2zr
2o
7-YSZ gradient cladding is by six layers of La
2zr
2o
7-YSZ matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 75%, La
2zr
2o
725%;
Third layer: YSZ 65%, La
2zr
2o
735%;
4th layer: YSZ 35%, La
2zr
2o
765%;
Layer 5: YSZ 25%, La
2zr
2o
775%;
Layer 6: La
2zr
2o
7100%.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.5%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 4:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: La
2zr
2o
7-YSZ gradient cladding is by ten layers of La
2zr
2o
7-YSZ matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 90%, La
2zr
2o
710%;
Third layer: YSZ 80%, La
2zr
2o
720%;
4th layer: YSZ 70%, La
2zr
2o
730%;
Layer 5: YSZ 60%, La
2zr
2o
740%;
Layer 6: YSZ 500%, La
2zr
2o
750%;
Layer 7: YSZ 40%, La
2zr
2o
760%;
8th layer: YSZ 30%, La
2zr
2o
770%;
9th layer: YSZ 20%, La
2zr
2o
780%;
Tenth layer: La
2zr
2o
7100%.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 5:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: La
2ce
2o
7-YSZ gradient cladding is by ten layers of La
2ce
2o
7-YSZ matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 90%, La
2ce
2o
710%;
Third layer: YSZ 80%, La
2ce
2o
720%;
4th layer: YSZ 70%, La
2ce
2o
730%;
Layer 5: YSZ 60%, La
2ce
2o
740%;
Layer 6: YSZ 50%, La
2ce
2o
750%;
Layer 7: YSZ 40%, La
2ce
2o
760%;
8th layer: YSZ 30%, La
2ce
2o
770%;
9th layer: YSZ 20%, La
2ce
2o
780%;
Tenth layer: La
2ce
2o
7100%.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.5%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 6
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: the total thickness of gradient cladding is 500 μm.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 7:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: the bi-material of institute's compound is Gd
2zr
2o
7-YSZ.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.5%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 8:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: the bi-material of institute's compound is Sm
2zr
2o
7-YSZ.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 9: the difference that described in the present embodiment and embodiment 1, gradient cladding designs is: the bi-material of institute's compound is La
2ce
2o
7-YSZ.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 10:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: base material used is Si
3n
4, in preprocessing process, transition layer used is SiO
2, the bi-material of institute's compound is mullite-MoSi
2.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.5%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 11:
The difference that described in the present embodiment and embodiment 1, gradient cladding designs is: the bi-material of institute's compound is Sm
2zr
2o
7-lanthanum aluminate.
Can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 12: at Ni based high-temperature alloy substrate upper plasma spraying Y
2zr
2o
7-lanthanum aluminate gradient cladding, coating is by six layers of Y
2zr
2o
7-lanthanum aluminate matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: lanthanum aluminate 100%;
The second layer: lanthanum aluminate 80%, Y
2zr
2o
720%;
Third layer: lanthanum aluminate 60%, Y
2zr
2o
740%;
4th layer: lanthanum aluminate 40%, Y
2zr
2o
760%;
Layer 5: lanthanum aluminate 20%, Y
2zr
2o
780%;
Layer 6: Y
2zr
2o
7100%.
Its preparation method is:
(1) by the lanthanum aluminate powder of 80% and the Y of 20%
2zr
2o
7powder puts into ball mill, adds mixed pulvis (ethanol) and carries out ball milling, and the mass ratio of ethanol and powder is 1: 5.Put it into baking oven inner drying after powder mixes, temperature 110 DEG C, be incubated 2 hours.Obtain the powder mix of other each layers more in the same way.By above-mentioned mixed powder granulation, its particle diameter is made to be 30 μm ~ 100 μm.
(2) alloy substrate surface carries out oil removing, and sandblasting alligatoring pre-treatment.Afterwards at substrate surface plasma spraying layer of Ni CoCrAlY transition layer, thickness is 80 μm.
(3) adopt plasma spraying method, the above-mentioned composite granule mixed is sprayed in pretreated substrate successively.The processing parameter of spraying is: electric current 500A, ar pressure is 0.7Mpa, and hydrogen pressure is 0.2Mpa, and spray distance is 70mm, total coating thickness 900 μm, and the thickness of each individual layer is equal.
Finally obtained gradient cladding, can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Embodiment 13: at silicon carbide fiber reinforced silicon carbide substrate (SiC/SiC) upper plasma spraying Sc
2zr
2o
7-YSZ gradient cladding, coating is by six layers of Y
2zr
2o
7-lanthanum aluminate matrix material forms, and from the bottom to the outer by mass percentage, its composition is respectively:
The first layer: YSZ 100%;
The second layer: YSZ 80%, Sc
2zr
2o
720%;
Third layer: YSZ 60%, Sc
2zr
2o
740%;
4th layer: YSZ 40%, Sc
2zr
2o
760%;
Layer 5: YSZ 20%, Sc
2zr
2o
780%;
Layer 6: Sc
2zr
2o
7100%.
Its preparation method is:
(1) by the YSZ powder of 80% and Sc
2zr
2o
7powder puts into ball mill, adds mixed pulvis (ethanol) and carries out ball milling, and the mass ratio of ethanol and powder is 1: 5.Put it into baking oven inner drying after powder mixes, temperature 80 DEG C, be incubated 3 hours.Obtain the powder mix of other each layers more in the same way.By above-mentioned mixed powder granulation, its particle diameter is made to be 30 μm ~ 100 μm.
(2) at substrate surface plasma spraying one deck SiO
2transition layer, thickness is 30 μm.
(3) adopt plasma spraying method, the above-mentioned composite granule mixed is sprayed in pretreated substrate successively.The processing parameter of spraying is: electric current 700A, ar pressure is 0.9Mpa, and hydrogen pressure is 0.4Mpa, and spray distance is 150mm, total coating thickness 800 μm, and the thickness of each individual layer is equal.
Finally obtained gradient cladding, can be calculated by temperature-thermal conductivity curve: the thermal conductivity of gradient cladding is 0.85J/ (gK), and after 20 thermal shocks experiment (T=1200 DEG C), the quality change of coating only 0.6%, and surface only has fragmentary small area to peel off, illustrate that the gradient cladding obtained by the present embodiment has good thermal shock resistance.
Comparative example:
Adopt plasma spray coating process condition identical in embodiment 1, alloy substrates sprays single La
2zr
2o
7coating, thickness is identical with gradient cladding thickness in embodiment 1, is 200 μm.Gained coating is carried out to the thermal shock experiment of the same terms, experimental result is as shown in table 1.
The single La of table 1
2zr
2o
7coating and La
2zr
2o
7the thermal shock resistance contrast of-YSZ gradient cladding
| Thermal shock number of times | Peel off area (%) | Quality change (%) | |
| La 2Zr 2O 7Coating | 9 | 20 | 4.5 |
| La 2Zr 2O 7-YSZ gradient cladding | 20 | 2.4 | 0.6 |
As can be seen from Table 1, single La
2zr
2o
7just there is the surfacial spalling of about 20% and the quality change of 4.5% after have passed through the thermal shock experiment of only nine times in coating, performance can not show a candle to gradient cladding obtained in the present embodiment.
Claims (8)
1. a thermal protection coating for component gradient change, this thermal protection coating comprises two kinds of composition: M
1and M
2;
Described M
1be selected from YSZ; M
2be selected from: Ln
2zr
2o
7, Ln
2ce
2o
7, Ln
2siO
5, Ln
2si
2o
7in one, wherein Ln is: La, Gd, Sm, Yb, Y or Sc;
Described thermal protection coating is made up of the matrix material of 6 ~ 10 layers, and from the 1st layer to last one deck, M
1mass percentage successively successively decrease from 100% ~ 0%, M
2mass percentage successively increase progressively from 0% ~ 100%; In every layer, M
1with M
2mass percentage sum be 100%; Described the first layer refers to the one deck directly contacted with base material, and described last one deck refers to and base material distance one deck farthest;
The thermal protection coating of described component gradient change is obtained by the preparation method of following steps:
1) preparation of composite granule: in proportion by M
1powder, M
2powder mixes with mixed pulvis and carries out ball milling, and powder is mixed, and after drying, granulation obtains composite granule, and each layer composite granule is prepared respectively;
2) pre-treatment is sprayed: pre-treatment is carried out to substrate surface;
3) spray gradient cladding: adopt plasma spraying method, by step 1) in composite granule after obtained granulation to be successively sprayed in pretreated substrate i.e. this thermal protection coating obtained successively; Described substrate is selected from superalloy substrate, carbon fibre reinforced silicon carbide substrate, silicon carbide fiber reinforced silicon carbide substrate or Si
3n
4substrate.
2. the preparation method of the thermal protection coating of component gradient change as claimed in claim 1, is obtained by following steps:
1) preparation of composite granule: in proportion by M
1powder, M
2powder mixes with mixed pulvis and carries out ball milling, and powder is mixed, and after drying, granulation obtains composite granule, and each layer composite granule is prepared respectively;
2) pre-treatment is sprayed: pre-treatment is carried out to substrate surface;
3) spray gradient cladding: adopt plasma spraying method, by step 1) in composite granule after obtained granulation to be successively sprayed in pretreated substrate i.e. this thermal protection coating obtained successively.
3. the preparation method of the thermal protection coating of as described in claim 2 component gradient change, is characterized in that, described step 1) in mixed pulvis be ethanol or water, and mixed pulvis compares M
1powder and M
2the ratio of powder quality sum is 1:5.
4. the preparation method of the thermal protection coating of as described in claim 2 component gradient change, is characterized in that, described step 1) in the particle diameter of composite granule be 30 μm ~ 100 μm.
5. the preparation method of the thermal protection coating of component gradient change as described in claim 2, it is characterized in that, described step 2) in, when adopting alloy substrates, described pre-treatment step comprises: oil removing and sandblasting alligatoring, that is: in the molten oil-based solvent wiping alloy substrates of use, then spray one deck transition layer NiCoCrAlY at alloy substrates surface plasma, thickness is 30 ~ 80 μm; When adopting silicon based composite material substrate, described pre-treatment step comprises: sandblasting alligatoring, that is: direct spraying transition layer SiO
2.
6. the preparation method of the thermal protection coating of component gradient change as described in claim 2, it is characterized in that, described step 3) in the processing parameter of spraying be: electric current 500A ~ 700A, ar pressure is 0.70MPa ~ 0.9MPa, hydrogen pressure is 0.2MPa ~ 0.4MPa, and spray distance is 70mm ~ 150mm.
7. the preparation method of the thermal protection coating of component gradient change as described in claim 2, is characterized in that, described step 3) in, the total thickness of thermal protection coating is 200 μm ~ 900 μm, and the thickness of each individual layer is equal.
8. the thermal protection coating of component gradient change as claimed in claim 1 protects for the high-temperature hot of base material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910247732.XA CN101768380B (en) | 2009-12-30 | 2009-12-30 | Thermal protection coating with component gradient change and preparation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910247732.XA CN101768380B (en) | 2009-12-30 | 2009-12-30 | Thermal protection coating with component gradient change and preparation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101768380A CN101768380A (en) | 2010-07-07 |
| CN101768380B true CN101768380B (en) | 2014-12-17 |
Family
ID=42501488
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910247732.XA Expired - Fee Related CN101768380B (en) | 2009-12-30 | 2009-12-30 | Thermal protection coating with component gradient change and preparation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101768380B (en) |
Families Citing this family (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9096763B2 (en) * | 2011-12-19 | 2015-08-04 | Praxair S.T. Technology, Inc. | Aqueous slurry for the production of thermal and environmental barrier coatings and processes for making and applying the same |
| CN102676972A (en) * | 2012-05-30 | 2012-09-19 | 重庆国际复合材料有限公司 | Treatment method for platinum rhodium bushing |
| CN102786303A (en) * | 2012-08-07 | 2012-11-21 | 内蒙古工业大学 | Ceramic nanometer composite material for heat barrier coating and preparation method of ceramic nanometer composite material |
| CN102828137B (en) * | 2012-08-31 | 2014-06-11 | 华南理工大学 | High-temperature alloy surface nanometer composite coating and preparation method thereof |
| CN103058654A (en) * | 2012-12-26 | 2013-04-24 | 上海大学 | Gradient nano-coating used for thermal barrier coating anti-corrosion function and preparation method thereof |
| CN104446670B (en) * | 2014-11-28 | 2016-10-05 | 中国人民解放军国防科学技术大学 | C/SiC composite material surface coating system and preparation method thereof |
| CN104775086A (en) * | 2015-04-30 | 2015-07-15 | 苏州统明机械有限公司 | Ceramic coating for metal-based thermal spraying and spraying method thereof |
| CN106757020B (en) * | 2016-05-30 | 2018-04-06 | 北京航空航天大学 | A kind of multi-layer high-temperature coating of thermostructural composite for continuous lod and preparation method thereof |
| CN106116586B (en) * | 2016-06-14 | 2019-01-18 | 中南大学 | A kind of molybdenum alloy MoSi2-ZrO2-Y2O3Coating and its preparation method and application |
| DE102016007231A1 (en) * | 2016-06-15 | 2017-12-21 | Forschungszentrum Jülich GmbH | Self-healing thermal barrier coatings and methods of making same |
| FR3061710B1 (en) | 2017-01-06 | 2019-05-31 | Safran Ceramics | PART COMPRISING A SUBSTRATE AND AN ENVIRONMENTAL BARRIER |
| CN107245687A (en) * | 2017-06-09 | 2017-10-13 | 天津大学 | A kind of toughness rare earth phosphate/zirconates composite thermal barrier coating and preparation method thereof |
| CN108468011B (en) * | 2018-03-15 | 2020-04-14 | 北京矿冶科技集团有限公司 | Gradient thermal barrier coating with continuously-changed interface components of double ceramic layers and preparation method thereof |
| CN110894164B (en) * | 2018-09-13 | 2021-07-13 | 中国科学院上海硅酸盐研究所 | Rare earth silicate laminar-distributed silicon carbide ceramic matrix composite and preparation method thereof |
| CN109704775B (en) * | 2018-12-13 | 2021-09-07 | 湖南泽睿新材料有限公司 | Beryllium-gradient-distributed continuous silicon carbide fiber and preparation method thereof |
| CN110002900B (en) * | 2019-05-14 | 2022-01-18 | 中国人民解放军国防科技大学 | Environment barrier-infrared stealth integrated coating, coated composite material and preparation method thereof |
| CN110484854B (en) * | 2019-07-22 | 2021-04-23 | 中国航发北京航空材料研究院 | Preparation method of thermal barrier coating with self-repairing and temperature-sensitive functions |
| CN111233498A (en) * | 2020-03-06 | 2020-06-05 | 中南大学 | Environmental barrier coating and preparation method and application thereof |
| CN111908921B (en) * | 2020-08-28 | 2021-09-14 | 昆明理工大学 | Rare earth tantalate RE3TaO7Thermal barrier coating and method for producing the same |
| CN111960822A (en) * | 2020-08-28 | 2020-11-20 | 昆明理工大学 | Non-stoichiometric gadolinium niobate ceramic coating with continuous components and preparation method thereof |
| CN111943672B (en) * | 2020-08-28 | 2021-08-31 | 昆明理工大学 | Preparation method of aluminum oxide toughened aluminum niobate ceramic coating with continuously-changed components |
| CN111960837B (en) * | 2020-08-28 | 2021-10-26 | 昆明理工大学 | Preparation method of rare earth tantalate or niobate thermal barrier coating |
| CN111960863B (en) * | 2020-08-28 | 2022-03-29 | 昆明理工大学 | Ultrahigh-temperature corrosion-resistant composite material and preparation method thereof |
| CN113025945A (en) * | 2021-03-02 | 2021-06-25 | 中国科学院长春应用化学研究所 | Preparation method of high-temperature oxidation-resistant rare earth silicate thermal barrier coating on surface of titanium alloy composite material |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101378132A (en) * | 2007-08-31 | 2009-03-04 | 丹麦技术大学 | Horizontally graded structures for electrochemical and electronic devices |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050013993A1 (en) * | 2003-07-16 | 2005-01-20 | Honeywell International Inc. | Environmental & thermal barrier coating |
-
2009
- 2009-12-30 CN CN200910247732.XA patent/CN101768380B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101378132A (en) * | 2007-08-31 | 2009-03-04 | 丹麦技术大学 | Horizontally graded structures for electrochemical and electronic devices |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101768380A (en) | 2010-07-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101768380B (en) | Thermal protection coating with component gradient change and preparation method | |
| US20210261465A1 (en) | Ceramic material for high temperature service | |
| Hardwicke et al. | Advances in thermal spray coatings for gas turbines and energy generation: a review | |
| Zhou et al. | Thermophysical properties and cyclic lifetime of plasma sprayed SrAl12O19 for thermal barrier coating applications | |
| Afrasiabi et al. | A comparative study on hot corrosion resistance of three types of thermal barrier coatings: YSZ, YSZ+ Al2O3 and YSZ/Al2O3 | |
| Bakan et al. | High-temperature materials for power generation in gas turbines | |
| Ghosh | Thermal barrier ceramic coatings—a review | |
| EP1577499A2 (en) | Turbine components with thermal barrier coatings | |
| CN101405423A (en) | Heat shield coating member, process for producing the same, heat shield coat material, gas turbine and sintered body | |
| Zhou et al. | Characterization of multi-scale synergistic toughened nanostructured YSZ thermal barrier coatings: From feedstocks to coatings | |
| US11851770B2 (en) | Thermal barrier coatings for components in high-temperature mechanical systems | |
| US9139477B2 (en) | Ceramic powders and methods therefor | |
| CN111004990A (en) | MAX phase coating for thermal barrier coating anti-melting CMAS corrosion and thermal spraying preparation method | |
| EP2778250A2 (en) | Coating systems and methods therefor | |
| Jude et al. | Thermal barrier coatings for high-temperature application on superalloy substrates-A review | |
| JP2021191899A (en) | Adhesion promoter layer for joining high-temperature protection layer to substrate, and method for producing the same | |
| Tailor et al. | Effect of controlled segmentation on the thermal cycling behavior of plasma sprayed YSZ thick coatings | |
| Zhang et al. | Cyclic oxidation performances of new environmental barrier coatings of HfO2-SiO2/Yb2Si2O7 coated SiC at 1375° C and 1475° C in the air environment | |
| Song et al. | Hot corrosion behavior in thermal barrier coatings with heterogeneous splat boundary | |
| Zhu et al. | Furnace cyclic behavior of plasma–sprayed zirconia–yttria and multi–component rare earth oxide doped thermal barrier coatings | |
| CN112204163B (en) | CMAS resistant, high strain resistant and low thermal conductivity thermal barrier coatings and thermal spray methods | |
| Fang et al. | Thermal cycling behavior of plasma-sprayed yttria-stabilized zirconia thermal barrier coating with La0. 8Ba0. 2TiO3− δ top layer | |
| Zhao et al. | Thermal barrier coatings on nickel superalloy substrates | |
| Bhatty et al. | Behavior of calcia-stabilized zirconia coating at high temperature, deposited by air plasma spraying system | |
| Smialek et al. | Durability of YSZ coated Ti2AlC in 1300° C high velocity burner rig tests |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141217 Termination date: 20201230 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |