Thermal protection coating with component gradient change and preparation method

A composition gradient and thermal protection technology, applied in coating, metal material coating process, fusion spraying, etc., can solve problems such as easy phase change, large difference in thermal expansion coefficient, coating failure, etc., and achieve high hardness and strength , Excellent thermal shock resistance, and the effect of reducing the concentration of thermal stress

Inactive Publication Date: 2010-07-07
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For example, the commonly used YSZ(Y 2 o 3 Stable ZrO 2 ) has a thermal expansion coefficient that matches the metal substrate very well, but it is easy to phase change above 1200 °C; while La 2 Zr 2 o 7 Although it has v...

Method used

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  • Thermal protection coating with component gradient change and preparation method
  • Thermal protection coating with component gradient change and preparation method
  • Thermal protection coating with component gradient change and preparation method

Examples

Experimental program
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Effect test

Embodiment 1

[0042] Embodiment 1: plasma spraying La on Ni-based superalloy substrate 2 Zr 2 o 7 -YSZ gradient coating, the coating consists of six layers of La 2 Zr 2 o 7 -YSZ composite material composition, from the bottom layer to the outer layer by mass percentage, the composition is as follows:

[0043] The first layer: YSZ 100%;

[0044] Second floor: YSZ 80%, La 2 Zr 2 o 7 20%;

[0045] The third floor: YSZ 60%, La 2 Zr 2 o 7 40%;

[0046] Fourth floor: YSZ 40%, La 2 Zr 2 o 7 60%;

[0047] Fifth floor: YSZ 20%, La 2 Zr 2 o 7 80%;

[0048] The sixth floor: La 2 Zr 2 o 7 100%.

[0049] Among them, the used M1 is YSZ, M2 is La 2 Zr 2 o 7 , the substrate is a Ni-based superalloy base, where the coefficient of thermal expansion of M1 (M 1 )=10.7×10-6 / °C, M 2 Coefficient of thermal expansion (M 2 )=8×10-6 / ℃, the coefficient of thermal expansion of the substrate (S)=10.1×10-6 / ℃, there is the following relationship among the three: |(M 1 )-(S)|2 )-(S)|, a...

Embodiment 2

[0058] The difference between this embodiment and the gradient coating design described in embodiment 1 is: La 2 Zr 2 o 7 -YSZ gradient coating consists of six layers of La 2 Zr 2 o 7 -YSZ composite material composition, from the bottom layer to the outer layer by mass percentage, the composition is as follows:

[0059] The first layer: YSZ 100%;

[0060] Second layer: YSZ 70%, La 2 Zr 2 o 7 30%;

[0061] Third floor: YSZ 55%, La 2 Zr 2 o 7 45%;

[0062] Fourth layer: YSZ 45%, La 2 Zr 2 o 7 55%;

[0063] Fifth floor: YSZ 30%, La 2 Zr 2 o 7 70%;

[0064] The sixth floor: La 2 Zr 2 o 7 100%.

[0065] From the temperature-thermal conductivity curve, it can be calculated that the thermal conductivity of the gradient coating is 0.85J / (g·K), and after 20 thermal shock experiments (T=1200℃), the mass change of the coating is only 0.6 %, and there are only sporadic small areas peeling off on the surface, indicating that the gradient coating prepared in th...

Embodiment 3

[0067] The difference between this embodiment and the gradient coating design described in embodiment 1 is: La 2 Zr 2 o 7 -YSZ gradient coating consists of six layers of La 2 Zr 2 o 7 -YSZ composite material composition, from the bottom layer to the outer layer by mass percentage, the composition is as follows:

[0068] The first layer: YSZ 100%;

[0069] Second layer: YSZ 75%, La 2 Zr 2 o 7 25%;

[0070] The third layer: YSZ 65%, La 2 Zr 2 o 7 35%;

[0071] Fourth floor: YSZ 35%, La 2 Zr 2 o 7 65%;

[0072] Fifth floor: YSZ 25%, La 2 Zr 2 o 7 75%;

[0073]The sixth floor: La 2 Zr 2 o 7 100%.

[0074] From the temperature-thermal conductivity curve, it can be calculated that the thermal conductivity of the gradient coating is 0.85J / (g·K), and after 20 thermal shock experiments (T=1200℃), the mass change of the coating is only 0.5 %, and there are only sporadic small areas peeling off on the surface, indicating that the gradient coating prepared in...

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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 [0001] The invention belongs to the field of inorganic materials, and in particular relates to a heat protection coating with a composition gradient change and a preparation method. Background technique [0002] With the continuous development of gas turbines towards high thrust-to-weight ratio and high efficiency, the inlet temperature of gas needs to be further increased, so that the components in the combustion chamber will bear greater threat of high temperature failure. This threat not only includes the melting of components at high temperature , phase change, and there are also threats from water vapor and corrosive impurities in the gas environment. At present, the most feasible and effective solution is to deposit a layer of thermal protective coating on the surface of these substrates to form a barrier between the substrate and the gas environment, hindering the direct impact of the gas environment on the substrate material, thereby prolonging the se...

Claims

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Application Information

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IPC IPC(8): C09D1/00C09D5/00C23C4/10C23C4/11C23C4/134
Inventor 高彦峰陈宏飞刘云罗宏杰
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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