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Nano rare earth zirconate ceramic powder material for high temperature heat barrier coat and preparation method thereof

A nano-rare earth and ceramic powder technology, which is applied in the field of rare earth zirconate ceramic powder materials and preparations for high-temperature thermal barrier coatings, can solve the problems of thermal expansion mismatch, phase change failure, and high thermal conductivity of the substrate, and achieve particle diameter The effect of small size, high melting point and low thermal conductivity

Inactive Publication Date: 2008-01-16
HARBIN INST OF TECH
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  • Application Information

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Problems solved by technology

[0004] In order to solve the problems of phase transformation failure, severe sintering, high thermal conductivity and mismatch with the thermal expansion of the substrate existing in the existing ceramic materials for high temperature thermal barrier coatings, the present invention provides a nano rare earth ceramic material for high temperature thermal barrier coatings Zirconate ceramic powder material and preparation method

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  • Nano rare earth zirconate ceramic powder material for high temperature heat barrier coat and preparation method thereof
  • Nano rare earth zirconate ceramic powder material for high temperature heat barrier coat and preparation method thereof

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specific Embodiment approach 1

[0015] Specific implementation mode 1: The chemical molecular formula of the nanometer rare earth zirconate ceramic powder material for high temperature thermal barrier coating in this implementation mode is Ln 2 Zr 2 o 7 , wherein the Ln is a combination of one or more rare earth elements in Gd, Sm, Nd or Yb.

[0016] The preparation method of the nano rare earth zirconate ceramic powder material for high temperature thermal barrier coating in this embodiment is as follows:

[0017] Step 1, at room temperature, dissolve rare earth oxides with dilute nitric acid or dissolve soluble salts containing rare earth elements with deionized water to obtain Ln-containing 3+ solution, dissolving soluble zirconium salts with deionized water to obtain Zr 4+ The solution, the concentration of the two solutions is the same, both 0.1 ~ 1.0M;;

[0018] Step 2, mixing the two solutions obtained in step 1 to prepare a solution containing Ln 3+ and Zr 4+ A 1:1 mixed solution, the molar con...

specific Embodiment approach 2

[0028] Embodiment 2: The difference between this embodiment and the nano-rare earth zirconate ceramic powder material for high-temperature thermal barrier coatings described in Embodiment 1 is that the Ln is Gd or Sm or Nd or Yb.

[0029] In this embodiment, Gd is used 2 o 3 Extract Gd as raw material 3+ ions, using Sm 2 o 3 Extract Sm as raw material 3+ Ions; using Nd 2 o 3 Extract Nd as raw material 3+ ion; using Yb 2 o 3 Extract Yb as raw material 3+ ion.

[0030] Gd described in this embodiment mode 2 Z r 2O 7 The ceramic material has a single pyrochlore phase structure, as shown in Figure 1, and its particle size is about 40 nm, as shown in Figure 2; Gd after drying at 80 °C 2 Zr 2 o 7 The TG-DTA curve of the precipitate is shown in Figure 3. It is found that the precipitate undergoes dehydration reaction around 150°C, organic matter decomposes around 300°C, and crystallizes around 600°C. No phase change, no weight loss, suitable as high temperature therm...

specific Embodiment approach 3

[0031] Embodiment 3: The difference between this embodiment and the nano-rare earth zirconate ceramic powder material for high-temperature thermal barrier coatings described in Embodiment 1 is that the Ln is Gd x SM 1-x or Nd x Yb 1-x or Gd x Nd 1-x or Gd x Yb 1-x or Sm x Nd 1-x or Sm x Yb 1-x , where x is 0.1 or 0.3 or 0.5 or 0.7 or 0.9.

[0032] The difference between the method for preparing the ceramic powder material described in this embodiment and the method described in Embodiment 1 is that in step 1, the soluble salt solution prepared by using rare earth oxides contains Gd 3+ 、Sm 3+ 、Nd 3+ and Yb 3+ Any two of them, the ratio of the two ions in the soluble salt solution is: x:(1-x).

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Abstract

Disclosed are a nano-rare earth zirconate ceramic powder material for high-temperature thermal barrier coatings, and the preparation method, relating to a nano-rare earth zirconate ceramic powder material for high-temperature thermal barrier coatings, and the preparation method. The invention solves the problems that the existing ceramic materials for high-temperature thermal barrier coatings are of phase change failure, serious sintering, and too high thermal conductivity and mismatch with the matrix thermal expansion. The chemical formula of the nano-rare earth zirconate ceramic powder material for high-temperature thermal barrier coatings is Ln2Zr2O7, wherein, Ln is the combination of one or more rare earth elements among Gd, Sm, Nd or Yb. The preparation method is that rare earth oxide or soluble salt and zirconium salt containing rare earth oxides are used to respectively prepare the solution containing Ln3 + and the solution containing Zr4 +; the two solutions are mixed and added with surfactant under the ongoing mixing conditions; the mixed solution is dropped into precipitator to get sediment; after repeated washing, the sediment is dried, grinded and calcined. The invention can effectively protect high temperature alloy.

Description

technical field [0001] The invention belongs to the field of material synthesis, and relates to a rare earth zirconate ceramic powder material for a high-temperature thermal barrier coating and a preparation method thereof. Background technique [0002] With the rapid development of the aerospace industry, the performance requirements of the engine are getting higher and higher. To make the engine have a high thrust-to-weight ratio and a large driving force, one of the important means is to increase the inlet temperature of the superalloy turbine blade. For engines developed abroad in the 1970s, the gas inlet temperature in front of the turbine blades has reached above 1600K; in the 1990s, the gas inlet temperature in front of the turbine blades has reached 1850-1950K, and the existing high-temperature alloys and cooling technologies have been difficult to meet the requirements. In order to achieve such a high gas temperature, there are three corresponding measures: one is t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/48C04B35/50C04B35/622
Inventor 欧阳家虎刘占国周玉
Owner HARBIN INST OF TECH
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