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Rare earth modified barium lanthanum titanium composite oxide heat-barrier coating ceramic layer material and its preparation method

A technology of titanium composite oxides and rare earth oxides, applied in the field of barium lanthanum titanium composite oxide thermal barrier coating ceramic layer materials, can solve the problems of increased engine load, stress concentration, and increased difficulty in blade manufacturing, and achieve the goal of preventing oxidation Effect

Inactive Publication Date: 2007-05-23
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The use of film cooling technology can reduce the surface temperature of high-temperature components to increase their applicable temperature, but the film cooling technology will inevitably lose a large part of energy while reducing the temperature of the blades, which will increase the burden on the engine; Cooling air flow holes at the leading edge make the blade more difficult to manufacture, and these holes can also cause stress concentrations and reduce the service life of the blade

Method used

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  • Rare earth modified barium lanthanum titanium composite oxide heat-barrier coating ceramic layer material and its preparation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Embodiment 1: make Ba 0.9 Gd 0.1 La 2 (Ti 0.9 SM 0.1 ) 3 o 10 ceramic layer material

[0027] The first step: commercially available barium carbonate BaCO 3 , titanium dioxide TiO 2 , Lanthanum trioxide La 2 o 3 , Gadolinium trioxide Gd 2 o 3 and samarium trioxide Sm 2 o 3 After grinding for 45 minutes by wet ball milling method, a fine powder with a particle size of less than 1 micron was obtained; after drying in a drying oven at 120°C for 180 minutes, a dry fine powder was obtained, which was taken out for use;

[0028] The second step: take the dry fine powder after the first step treatment, 177.61g of barium carbonate, 215.73g of titanium dioxide, 18.12g of digadolinium trioxide, 325.80g of dilanthanum trioxide and 52.32g of disamarium trioxide, and mix them uniformly to obtain Precursor;

[0029] The third step: Put the precursor obtained in the second step into the SSX high-temperature furnace of Shanghai Experimental Electric Furnace Factory, adju...

Embodiment 2

[0033] Embodiment 2: make Ba 0.91 Y 0.03 Nd 0.03 SM 0.03 La 2 (Ti 0.91 Ce 0.03 SM 0.03 Gd 0.03 ) 3 o 10 ceramic layer material

[0034] The first step: commercially available barium carbonate BaCO 3 , Diyttrium trioxide Y 2 o 3 , Neodymium trioxide Nd 2 o 3 , Lanthanum trioxide La 2 o 3 , Samarium trioxide Sm 2 o 3 , titanium dioxide TiO 2 , cerium oxide Ce 2 o 3 and gadolinium trioxide Gd 2 o 3 After grinding for 50 minutes by wet ball milling, a fine powder with a particle size of less than 1 micron was obtained; after drying in a drying oven at 180°C for 110 minutes, a dry fine powder was obtained for use;

[0035] The second step: Weigh the dry fine powder after the first step treatment, barium carbonate 179.58g, diyttrium trioxide 3.39g, dineodymium trioxide 5.05g, dilanthanum trioxide 325.80g, disamarium trioxide 41.86g, titanium dioxide 218.12g, 14.77g of dicerium oxide and 16.31g of digadolinium oxide were mixed uniformly to prepare the precurso...

Embodiment 3

[0040] Embodiment 3: make Ba 0.91 SM 0.09 La 2 Ti 3 o 10 ceramic layer material

[0041] The first step: commercially available barium carbonate BaCO 3 , Lanthanum trioxide La 2 o 3 , Samarium trioxide Sm 2 o 3 and titanium dioxide TiO 2 After grinding by wet ball milling for 60 minutes, a fine powder with a particle size of less than 1 micron was obtained; after drying in a drying oven at 170° C. for 150 minutes, a dry fine powder was obtained, which was taken out for use;

[0042] The second step: Weigh the dry fine powder after the first step treatment, barium carbonate 179.58g, titanium dioxide 239.70g, dilanthanum trioxide 325.80g and samarium trioxide 15.70g, mix uniformly to prepare the precursor;

[0043] The third step: Put the precursor obtained in the second step into the SSX high-temperature furnace of Shanghai Experimental Electric Furnace Factory, adjust the temperature to 1480°C, keep it at 1480°C for 60 hours, and then cool down to room temperature wi...

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Abstract

The invention disclosed a kind of rare earth reshaped barium, lanthanum and titanium compound oxide heat-proof smear layer and ceramic layer material. The chemical formula of the material is Ba1-xLnxLa2 (Ti1-yLny) 3O10 in which Ln stands for one kind, two kinds or three kinds of Y,Sm,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 180h 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 0.48-0.68 Wm-1K-1, the coefficient of thermal expansion (1200 Deg C) interval is 11.8-14.2 10-6K-1.

Description

technical field [0001] The invention relates to a ceramic layer material used as a thermal barrier coating and a preparation method thereof, more particularly to a rare earth modified barium lanthanum titanium composite oxide ceramic layer material for a thermal barrier coating. Background technique [0002] With the development of aero turbine engines towards high flow ratio and high thrust-to-weight ratio, the design inlet temperature also increases, so higher requirements are placed on the high temperature resistance of high temperature components of the engine. The design inlet temperature of an aero-engine with a thrust-to-weight ratio of 10 has reached 1577°C, which is a working temperature that any superalloy can hardly bear. Although after years of research, the applicable temperature of superalloys used in turbine blades has been increased to about 1000 °C, but it is still difficult to meet the design requirements of modern aero-engines. The use of film cooling tec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/462C04B35/622
Inventor 徐惠彬车平郭洪波宫声凯郭林
Owner BEIHANG UNIV