CN1966461A - Rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material and its preparation method - Google Patents
Rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material and its preparation method Download PDFInfo
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Abstract
The invention disclosed a kind of rare earth reshaped barium, Sm and titanium compound oxide heat-proof smear layer and ceramic layer material. The chemical formula of the material is Ba1-xLnxSm2 (Ti1-yLny) 3O10 in which Ln stands for one kind, two kinds or three kinds of Y,La,Ce,Gd and Nd and 0<=x<=0.12,0<=y<=0.12. Because of the adulteration of rare earth ion and the lamellar structure of the calcium and titanium mine, the material has lower heat conductivity and higher coefficient of thermal expansion compared to the zirconium oxide which is stabilized by 7-8% yttrium oxide. After annealing the material at 1500 Deg C for 168h the material can still maintain stable. The material can be designed to be heat-proof smear layer materials. The using temperature interval is ambient temperature to 1500 Deg C, and the heat conductivity (1200 Deg C) interval is 0.47-0.70 Wm-1K-1, the coefficient of thermal expansion (1200 Deg C) interval is 11.5-14.0 10-6K-1.
Description
Technical field
The present invention relates to a kind of material that is used as heat-barrier coating ceramic layer and preparation method thereof, more particularly say, be meant a kind of rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material.
Background technology
Along with aero-turbine develops to the direction of high flow capacity than, high thrust-weight ratio, the design inlet temperature also improves thereupon, therefore the heat-resisting ability of the high-temperature component of engine is also had higher requirement.The design inlet temperature of the aircraft engine of thrust-weight ratio 10 has reached 1577 ℃, and this is that present any superalloy all is difficult to the working temperature of bearing.Though through years of researches, the Applicable temperature that is used for the superalloy of turbine blade has been increased to about 1000 ℃, but still the difficult design requirements of satisfying modern aeroengine.Thereby the surface temperature that adopts the air film cooling technology can reduce high-temperature component improves its Applicable temperature, but the air film cooling technology has lost energy greatly inevitably when reducing leaf temperature, make the burden of engine; The cooling draught hole of opening simultaneously at blade inlet edge increases the manufacture difficulty of blade, and these holes also can cause stress concentration, the work-ing life of shortening blade.
From the middle of last century, people begin to attempt using thermal barrier coating (TBC) technology further to improve the working temperature of engine.The design philosophy of thermal barrier coating is performances such as high temperature resistant, corrosion-resistant, wear-resistant and low heat conduction of utilizing some stupalith superior, with coating form that pottery is mutually compound with matrix, when improving metal fever end pieces resistance to high temperature corrosion ability, making it can bear higher use temperature, is a kind of possible technique that reduces the blade working temperature.Have data to show, after ceramic heat-barrier coating is coated on the Turbine Blade surface, can make cooling air delivery reduce 50%, specific fuel consumption reduces 1～2%, and leaf longevity improves several times.Only reduce one of oil consumption, for bigger company of civil aviaton an of family, annual with regard to cost-saved more than 1,000 ten thousand dollars.Particularly, the thermal barrier coating ceramic material that Applicable temperature is higher can improve the working temperature of engine, makes the engine of a new generation obtain bigger thrust-weight ratio and more energy-conservation and environmental protection.
Summary of the invention
One of purpose of the present invention provides a kind of rare earth modified barium scythe titanium composite oxide heat-barrier coating material, by adding rare earth element, has improved the thermal expansivity of heat barrier coat material effectively, and has reduced thermal conductivity.
Another object of the present invention is to propose a kind of method for preparing rare earth modified barium scythe titanium composite oxide heat-barrier coating material, adopts in high-temperature reaction process and controls heat-up rate stage by stage, makes reaction be more prone to carry out.
The present invention is a kind of rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material, and the chemical formula of its compound is Ba
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10, Ln is one or both or three kinds of combinations of Y, La, Ce, Gd, Nd, 0≤x≤0.12,0≤y≤0.12.
Heat-barrier coating ceramic layer material of the present invention is BaSm when not adding its compound of rare earth element
2Ti
3O
10
The advantage of the barium scythe titanium composite oxide heat-barrier coating material that the present invention is rare earth modified is: the thermal conductivity of the zirconia material of ratio 7～8% stabilized with yttrium oxide is lower, and thermal expansivity is higher, and thermal conductivity (1200 ℃) is 0.47～0.70Wm
-1K
-1, thermal expansivity (1200 ℃) is 11.5～14.0 10
-6K
-1Can under 1500 ℃ of hot conditionss, use.This material is non-oxygen ion conductor, can prevent tack coat and superalloy oxidation effectively.
Preparation method's advantage of the present invention is: undertaken to such an extent that be more prone to carry out by the gradient increased temperature reaction.
Description of drawings
Fig. 1 is Ba
0.88Y
0.12Sm
2(Ti
0.9La
0.1)
3O
10Polycrystal powder and after 1500 ℃ of long heat treatment the XRD spectra of sample, as can be seen from the figure behind 1500 ℃ of long term annealings, it is stable that structures of samples still keeps, and do not have phase transformation to take place.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention is a kind of rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material, and the chemical formula of its compound is: Ba
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10, Ln is one or both or three kinds of combinations of Y, La, Ce, Gd, Nd, 0≤x≤0.12,0≤y≤0.12.
A kind of method for preparing rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material of the present invention includes following preparation steps:
First step: with powder material BaCO
3, TiO
2, Sm
2O
3, Y
2O
3, La
2O
3, Ce
2O
3, Gd
2O
3And Nd
2O
3Adopt the wet ball-milling method to grind after 40～70 minutes respectively, make particle diameter less than 1 micron fine powder; In 70～300 ℃ loft drier, take out after dry 60～300 minutes, make dried fine powder, stand-by;
Second step: take by weighing the BaCO that first step makes
3Dried fine powder 15～30wt%, TiO
2Dried fine powder 15～30wt%, Sm
2O
3The dried fine powder rare earth oxide of dried fine powder 40～50wt% and surplus; Make precursor through mixing;
Described rare earth oxide is Y
2O
3, La
2O
3, Ce
2O
3, Gd
2O
3And Nd
2O
3In one or both or two or more combinations, wherein, its metal ion number ratio is 1: 1 when choosing two kinds of rare earth oxides, its metal ion number ratio is 1: 1: 1 when choosing three kinds of rare earth oxides.
Third step: the precursor that second step makes is put into High Temperature Furnaces Heating Apparatus, and furnace cooling is to room temperature after reacting 32～60 hours under 1460 ℃～1800 ℃ conditions; Take out below the ball milling to 5 micron, and in 70～300 ℃ loft drier, after dry 60～300 minutes, promptly get Ba
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10Heat-barrier coating ceramic layer material.
In the present invention, choose shown in compound that the different material component makes please see the following form:
| Chemical formula | Thermal conductivity (Wm -1K -1， 1200℃) | Thermal expansivity (10 -6K -1， 1200℃) |
| Ba 0.88Y 0.04Nd 0.04La 0.04Sm 2(Ti 0.88Ce 0.04La 0.04Gd 0.04) 3O 10 | 0.61 | 12.5 |
| Ba 0.88Ce 0.04La 0.04Gd 0.04Sm 2(Ti 0.88Y 0.04Nd 0.04La 0.04) 3O 10 | 0.58 | 12.7 |
| Ba 0.88Y 0.06Nd 0.06Sm 2(Ti 0.9Ce 0.05La 0.05) 3O 10 | 0.63 | 14 |
| Ba 0.88Gd 0.06Ce 0.06Sm 2(Ti 0.9Nd 0.05La 0.05) 3O 10 | O.59 | 13 |
| Ba 0.88La 0.06Nd 0.06Sm 2(Ti 0.9Ce 0.05Gd 0.05) 3O 10 | 0.60 | 12.8 |
| Ba 0.9Y 0.1Sm 2(Ti 0.88Ce 0.12) 3O 10 | 0.52 | 13 |
| Ba 0.9La 0.1Sm 2(Ti 0.9Gd 0.1) 3O 10 | 0.62 | 13.5 |
| Ba 0.9Ce 0.1Sm 2(Ti 0.9La 0.1) 3O 10 | 0.60 | 12.0 |
| Ba 0.9Gd 0.1Sm 2(Ti 0.9La 0.1) 3O 10 | 0.50 | 13.5 |
| Ba 0.9Nd 0.1Sm 2(Ti 0.9La 0.1) 3O 10 | 0.49 | 11.5 |
| Ba 0.95La 0.05Sm 2(Ti 0.95Y 0.05) 3O 10 | 0.69 | 11.9 |
| BaSm 2(Ti 0.9Ce 0.1) 3O 10 | 0.63 | 13 |
| BaSm 2(Ti 0.9La 0.1) 3O 10 | 0.51 | 12 |
| BaSm 2(Ti 0.9Y 0.1) 3O 10 | 0.56 | 12.5 |
| BaSm 2(Ti 0.9Gd 0.1) 3O 10 | 0.50 | 11.8 |
| BaSm 2(Ti 0.9Nd 0.1) 3O 10 | 0.62 | 13.6 |
| BaSm 2(Ti 0.95Ce 0.05) 3O 10 | 0.52 | 12.3 |
| BaSm 2(Ti 0.95La 0.05) 3O 10 | 0.49 | 12.5 |
| BaSm 2(Ti 0.95Y 0.05) 3O 10 | 0.58 | 11.7 |
| BaSm 2(Ti 0.95Gd 0.05) 3O 10 | 0.61 | 12.4 |
| BaSm 2(Ti 0.95Nd 0.05) 3O 10 | 0.63 | 13 |
| Ba 0.9La 0.1Sm 2Ti 3O 10 | 0.66 | 12.9 |
| Ba 0.9Ce 0.1Sm 2Ti 3O 10 | 0.47 | 11.6 |
| Ba 0.9Y 0.1Sm 2Ti 3O 10 | 0.65 | 13 |
| Ba 0.9Gd 0.1Sm 2Ti 3O 10 | 0.70 | 12.1 |
| Ba 0.9Nd 0.1Sm 2Ti 3O 10 | 0.58 | 11.8 |
| Ba 0.95La 0.05Sm 2Ti 3O 10 | 0.55 | 12.4 |
| Ba 0.95Ce 0.05Sm 2Ti 3O 10 | 0.57 | 12.7 |
| Ba 0.95Y 0.05Sm 2Ti 3O 10 | 0.60 | 12.5 |
| Ba 0.95Gd 0.05Sm 2Ti 3O 10 | 0.59 | 11.9 |
| Ba 0.95Nd 0.05Sm 2Ti 3O 10 | 0.51 | 11.7 |
By the stupalith of the disclosed different components of last table, its thermal conductivity (1200 ℃) is 0.47～0.70Wm
-1K
-1, thermal expansivity (1200 ℃) is 11.5～14.010
-6K
-1Because comparing with the zirconium white of 7～8% stabilized with yttrium oxide that generally use at present, the doping of rare earth ion and the laminated perovskite structure of himself, this material have lower thermal conductivity and the thermal expansivity of Geng Gao.1500 ℃ of annealing 168 hours, it is mutually stable that this material still keeps.This material can be designed to heat barrier coat material, and the use temperature interval is a room temperature to 1500 ℃.
Heat-barrier coating ceramic layer material thermal conductivity involved in the present invention is low, and (M=Co, Ni) tack coat thermal expansion matching can improve the Applicable temperature of superalloy effectively with MCrAlY.This material is non-oxygen ion conductor, can protect tack coat and superalloy not oxidized, prolongs the work-ing life of high-temperature component.The synthetic used prices of raw and semifnished materials of this material are cheap, and market is easy to get; The deposited coatings method is simple, and equipment used is easy to get.
Embodiment 1: system Ba
0.9Gd
0.1Sm
2(Ti
0.9La
0.1)
3O
10Ceramic layer material
The first step: with commercially available barium carbonate BaCO
3, titanium dioxide TiO
2, Gadolinium trioxide Gd
2O
3, lanthanum sesquioxide La
2O
3With samarium sesquioxide Sm
2O
3Adopt the wet ball-milling method to grind after 45 minutes respectively, make particle diameter less than 1 micron fine powder; In 100 ℃ loft drier, make dried fine powder after dry 240 minutes, take out stand-by;
Second step: take by weighing the dried fine powder after the first step is handled, barium carbonate 177.61g, titanium dioxide 215.73g, Gadolinium trioxide 18.12g, lanthanum sesquioxide 48.87g and samarium sesquioxide 348.4g mix and make precursor;
The 3rd step: second precursor that make of step is put into the Shanghai SSX of experimental electric furnace factory type High Temperature Furnaces Heating Apparatus, adjusts the temperature to 1500 ℃, 1500 ℃ of insulations after 48 hours furnace cooling make reaction product to room temperature.
The 4th step: take out the 3rd reaction product that make of step below ball milling to 5 micron, in 100 ℃ loft drier, after dry 240 minutes, make Ba
0.9Gd
0.1Sm
2(Ti
0.9La
0.1)
3O
10Ceramic layer material.
In above-mentioned preparation method's the 3rd step, temperature of reaction can be a graded, regulates reaction in furnace temperature to 1500 ℃, and wherein, temperature is when room temperature rises to 1450 ℃ in the stove, and temperature rise rate is 5 ℃/min; 1450 ℃ of insulations 2 hours; During temperature, temperature rise rate is 1 ℃/min from 1450 ℃ to 1500 ℃.
With the above-mentioned Ba that makes
0.9Gd
0.1Sm
2(Ti
0.9La
0.1)
3O
10It is consistent with the following formula component that ceramic layer material adopts chemical analysis method to survey component; (Sweden), the thermal conductivity that obtains is 0.50Wm for TPS 2500 system, HotDisk AB to adopt the transient state plane heat source method to measure thermal conductivity
-1K
-1(1200 ℃); Adopting German NetzschDIL 402 E type high temperature dilatometers to record thermal expansivity is 13.5 10
-6K
-1(1200 ℃).
Embodiment 2: system Ba
0.91Y
0.03Nd
0.03La
0.03Sm
2(Ti
0.91Ce
0.03La
0.03Gd
0.03)
3O
10Ceramic layer material
The first step: with commercially available barium carbonate BaCO
3, yttrium oxide Y
2O
3, neodymium sesquioxide Nd
2O
3, lanthanum sesquioxide La
2O
3, samarium sesquioxide Sm
2O
3, titanium dioxide TiO
2, cerous oxide Ce
2O
3With Gadolinium trioxide Gd
2O
3Adopt the wet ball-milling method to grind after 45 minutes respectively, make particle diameter less than 1 micron fine powder; After dry 120 minutes, it is stand-by to make dried fine powder in 150 ℃ loft drier;
Second step: take by weighing the dried fine powder after the first step is handled, barium carbonate 179.58g, yttrium oxide 3.39g, neodymium sesquioxide 5.05g, lanthanum sesquioxide 19.55g, samarium sesquioxide 348.4g, titanium dioxide 218.12g, cerous oxide 14.77g and Gadolinium trioxide 16.31g mix and make precursor;
The 3rd step: second precursor that makes is put into the Shanghai SSX of experimental electric furnace factory type High Temperature Furnaces Heating Apparatus, adjust the temperature to 1650 ℃, cool to room temperature with the furnace after 36 hours, make reaction product 1650 ℃ of insulations;
The 4th step: take out the 3rd reaction product that make of step below ball milling to 5 micron, in 150 ℃ loft drier, after dry 120 minutes, make Ba
0.91Y
0.03Nd
0.03La
0.03Sm
2(Ti
0.91Ce
0.03La
0.03Gd
0.03)
3O
10Ceramic layer material.
In above-mentioned preparation method's the 3rd step, temperature of reaction can be a graded, and regulating the reaction in furnace temperature is 1650 ℃, and wherein, temperature is when room temperature rises to 1450 ℃ in the stove, and temperature rise rate is 5 ℃/min; 1450 ℃ of insulations 2 hours; During from 1450 ℃ to 1650 ℃, temperature rise rate is 1 ℃/min.
With the above-mentioned Ba that makes
0.91Y
0.03Nd
0.03La
0.03Sm
2(Ti
0.91Ce
0.03La
0.03Gd
0.03)
3O
10It is consistent with the following formula component that ceramic layer material adopts chemical analysis method to survey component; (Sweden), the thermal conductivity that obtains is 0.52Wm for TPS2500 system, Hot DiskAB to adopt the transient state plane heat source method to measure thermal conductivity
-1K
-1(1200 ℃); Adopting German Netzsch DIL 402 E type high temperature dilatometers to record thermal expansivity is 13 10
-6K
-1(1200 ℃).
Embodiment 3: system Ba
0.91La
0.09Sm
2Ti
3O
10Ceramic layer material
The first step: with commercially available barium carbonate BaCO
3, lanthanum sesquioxide La
2O
3, samarium sesquioxide Sm
2O
3With titanium dioxide TiO
2Adopt the wet ball-milling method to grind after 65 minutes respectively, make particle diameter less than 1 micron fine powder; In 150 ℃ loft drier, make dried fine powder after dry 180 minutes, take out stand-by;
Second step: take by weighing the dried fine powder after the first step is handled, barium carbonate 179.58g, titanium dioxide 239.70g, lanthanum sesquioxide 14.66g and samarium sesquioxide 348.6g mix and make precursor;
The 3rd step: second precursor that make of step is put into the Shanghai SSX of experimental electric furnace factory type High Temperature Furnaces Heating Apparatus, adjusts the temperature to 1480 ℃, 1480 ℃ of insulations after 58 hours furnace cooling make reaction product to room temperature.
The 4th step: take out the 3rd reaction product that make of step below ball milling to 5 micron, in 120 ℃ loft drier, after dry 200 minutes, make Ba
0.91La
0.09Sm
2Ti
3O
10Ceramic layer material.
In above-mentioned preparation method's the 3rd step, temperature of reaction can be a graded, and regulating the reaction in furnace temperature is 1480 ℃, and wherein, temperature is when room temperature rises to 1450 ℃ in the stove, and temperature rise rate is 5 ℃/min; 1450 ℃ of insulations 2 hours; During from 1450 ℃ to 1480 ℃, temperature rise rate is 1 ℃/min.
With the above-mentioned Ba that makes
0.9La
0.09Sm
2Ti
3O
10It is consistent with the following formula component that stupalith adopts chemical analysis method to survey component; (Sweden), the thermal conductivity that obtains is 0.53Wm for TPS 2500 system, Hot Disk AB to adopt the transient state plane heat source method to measure thermal conductivity
-1K
-1(1200 ℃); Adopting German Netzsch DIL 402 E type high temperature dilatometers to record thermal expansivity is 13.6 10
-6K
-1(1200 ℃).
The condition that the ceramic layer material of screening thermal barrier coating need satisfy is: have high melt point, and do not have phase transformation in room temperature to the use temperature interval; Lower thermal conductivity and higher thermal expansivity; Chemical property is stable and have a low sintering rate; Have and metallic matrix binding ability and good thermal shock resistance etc. preferably.The compd B a that the present invention relates to
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10, Ln is one or both or three kinds of combinations of Y, La, Ce, Gd, Nd, wherein, 0≤x≤0.12,0≤y≤0.12, preparation-obtained stupalith has than lower thermal conductivity of YSZ and the thermal expansivity of Geng Gao.Ba
0.88Y
0.12Sm
2(Ti
0.9La
0.1)
3O
10Can be at 1500 ℃ of condition life-time service (as shown in Figure 1), therefore can replace YSZ and become the ceramic layer material of aircraft engine thermal barrier coating of new generation.
In isolator and general semi-conductor, thermal conduction mainly relies on the thermal conductance of lattice.The mean atomic weight of atom affected lattice vibration during material was formed; And defective is determining the mean free path of phonon by the scattering to phonon.Material involved in the present invention is formed by heavy atom, and mean atomic weight is bigger, so material has lower thermal conductivity; When the rare earth ion of different concns replaced barium ion, because the defective that rare earth ion and barium ion ionic radius and charge differences are produced is to the scattering process of phonon, the thermal conductivity of material further reduced.Simultaneously, this material has lamellated crystalline structure, this make it thermal expansivity and McrAlY (M=Co, Ni) tack coat mates more.
Claims (10)
1, a kind of rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material is characterized in that: the chemical formula of compound is Ba
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10, Ln is one or both or three kinds of combinations of Y, La, Ce, Gd, Nd, 0≤x≤0.12,0≤y≤0.12.
2, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound is BaSm
2Ti
3O
10
3, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound has Ba
0.88Y
0.04Nd
0.04La
0.04Sm
2(Ti
0.88Ce
0.04La
0.04Gd
0.04)
3O
10Or Ba
0.88Ce
0.04La
0.04Gd
0.04Sm
2(Ti
0.88Y
0.04Nd
0.04La
0.04)
3O
10
4, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound has Ba
0.88Y
0.06Nd
0.06Sm
2(Ti
0.9Ce
0.05La
0.05)
3O
10Or Ba
0.88Gd
0.06Ce
0.06Sm
2(Ti
0.9Nd
0.05La
0.05)
3O
10Or Ba
0.88La
0.06Nd
0.06Sm
2(Ti
0.9Ce
0.05Gd
0.05)
3O
10
5, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound has Ba
0.9Y
0.1Sm
2(Ti
0.88Ce
0.12)
3O
10Or Ba
0.9La
0.1Sm
2(Ti
0.9Gd
0.1)
3O
10Or Ba
0.9Ce
0.1Sm
2(Ti
0.9La
0.1)
3O
10Or Ba
0.9Gd
0.1Sm
2(Ti
0.9La
0.1)
3O
10Or Ba
0.9Nd
0.1Sm
2(Ti
0.9La
0.1)
3O
10Or Ba
0.95La
0.05Sm
2(Ti
0.95Y
0.05)
3O
10
6, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound has BaSm
2(Ti
0.9Ce
0.1)
3O
10Or BaSm
2(Ti
0.9La
0.1)
3O
10Or BaSm
2(Ti
0.9Y
0.1)
3O
10Or BaSm
2(Ti
0.9Gd
0.1)
3O
10Or BaSm
2(Ti
0.9Nd
0.1)
3O
10Or BaSm
2(Ti
0.95Ce
0.05)
3O
10Or BaSm
2(Ti
0.95La
0.05)
3O
10Or BaSm
2(Ti
0.95Y
0.05)
3O
10Or BaSm
2(Ti
0.95Gd
0.05)
3O
10Or BaSm
2(Ti
0.95Nd
0.05)
3O
10
7, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: described compound has Ba
0.9La
0.1Sm
2Ti
3O
10Or Ba
0.9Ce
0.1Sm
2Ti
3O
10Or Ba
0.9Y
0.1Sm
2Ti
3O
10Or Ba
0.9Gd
0.1Sm
2Ti
3O
10Or Ba
0.9Nd
0.1Sm
2Ti
3O
10Or Ba
0.95La
0.05Sm
2Ti
3O
10Or Ba
0.95Ce
0.05Sm
2Ti
3O
10Or Ba
0.95Y
0.05Sm
2Ti
3O
10Or Ba
0.95Gd
0.05Sm
2Ti
3O
10Or Ba
0.95Nd
0.05Sm
2Ti
3O
10
8, heat-barrier coating ceramic layer material according to claim 1 is characterized in that: its thermal conductivity (1200 ℃) is 0.47～0.70Wm
-1K
-1, thermal expansivity (1200 ℃) is 11.5～14.0 10
-6K
-1
9, a kind of method for preparing rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material is characterized in that following preparation steps is arranged:
First step: with powder material BaCO
3, TiO
2, Sm
2O
3, Y
2O
3, La
2O
3, Ce
2O
3, Gd
2O
3And Nd
2O
3Adopt the wet ball-milling method to grind after 40～70 minutes respectively, make particle diameter less than 1 micron fine powder; In 70～300 ℃ loft drier, take out after dry 60～300 minutes, make dried fine powder, stand-by;
Second step: take by weighing the BaCO that first step makes
3Dried fine powder 15～30wt%, TiO
2Dried fine powder 15～30wt%, Sm
2O
3The dried fine powder rare earth oxide of dried fine powder 40～50wt% and surplus; Make precursor through mixing;
Described rare earth oxide is Y
2O
3, La
2O
3, Ce
2O
3, Gd
2O
3And Nd
2O
3In the combination of one or both or three kinds, wherein, its metal ion number ratio is 1: 1 when choosing two kinds of rare earth oxides, its metal ion number ratio is 1: 1: 1 when choosing three kinds of rare earth oxides;
Third step: the precursor that second step makes is put into High Temperature Furnaces Heating Apparatus, and furnace cooling is to room temperature after reacting 32～60 hours under 1460 ℃～1800 ℃ conditions; Take out below the ball milling to 5 micron, and in 70～300 ℃ loft drier, after dry 60～300 minutes, promptly get Ba
1-xLn
xSm
2(Ti
1-yLn
y)
3O
10Thermal barrier coating ceramic material.
10, the method for the rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material of preparation according to claim 8, it is characterized in that: in the 3rd step, temperature of reaction can be a graded, the conditioned reaction temperature is 1460 ℃～1800 ℃, wherein, temperature is when room temperature rises to 1450 ℃ of temperature in the stove, and temperature rise rate is 5 ℃/min; 1450 ℃ of insulations 2 hours; During temperature, temperature rise rate is 1 ℃/min from 1450 ℃ to 1800 ℃.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006101440377A CN100463877C (en) | 2006-11-24 | 2006-11-24 | Rare earth modified barium scythe titanium composite oxide heat-barrier coating ceramic layer material and its preparation method |
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| CN107904546A (en) * | 2017-11-30 | 2018-04-13 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of preparation method of aero-engine hot-end component thermal barrier coating |
| CN116143517A (en) * | 2023-03-06 | 2023-05-23 | 上海交通大学 | Ceramic material with high reflectivity in visible near infrared band, preparation method and application |
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| JPS5937526B2 (en) * | 1980-07-01 | 1984-09-10 | 松下電器産業株式会社 | dielectric magnetic composition |
| JPH0612916A (en) * | 1991-08-14 | 1994-01-21 | Denki Kagaku Kogyo Kk | Dielectric porcelain composition |
| CN1772698A (en) * | 2005-09-30 | 2006-05-17 | 福州大学 | High-dielectric constant environment friendly microwave dielectric ceramic |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107904546A (en) * | 2017-11-30 | 2018-04-13 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of preparation method of aero-engine hot-end component thermal barrier coating |
| CN116143517A (en) * | 2023-03-06 | 2023-05-23 | 上海交通大学 | Ceramic material with high reflectivity in visible near infrared band, preparation method and application |
| CN116143517B (en) * | 2023-03-06 | 2024-05-31 | 上海交通大学 | Ceramic material with high reflectivity in visible near infrared band, preparation method and application |
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