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Thermal barrier coating and preparation method thereof

A technology of thermal barrier coating and heat insulation layer, which is applied in coating, metal material coating process, air transportation, etc., can solve problems such as thermal expansion coefficient mismatch, and achieve the effect of reasonable composition and simple preparation process

Active Publication Date: 2015-11-11
江苏海泰新材料科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention provides a thermal barrier coating and a preparation method thereof which solves the problem of thermal expansion coefficient mismatch between coating materials in the prior art

Method used

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  • Thermal barrier coating and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] see figure 1 , the base layer 2 is pure metal Mo; the first transition layer 3 between the thermal insulation layer 5 and the base layer 2 is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 25%, the thickness is 0.1mm; the second transition layer 4 between the thermal insulation layer 5 and the base layer 2 is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 40%, the thickness is 0.1mm; the heat insulation layer is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 85%, the thickness is 0.4mm; the second transition layer 4 between the heat insulation layer 5 and the protective layer 6 is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 40%, the thickness is 0.12mm; the first transition layer 3 between the heat insulation layer 5 and the protective layer 6 is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 25%, and the thickness is 0.1mm. The protective layer is a pure metal Mo coating.

Embodiment 2

[0034] and figure 1 The structure shown is different, the base layer 2 is pure metal Mo; a single-layer transition structure (that is, only one filter layer) is adopted between the heat insulation layer 5 and the base layer 2, which is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 45%, the thickness is 0.15mm; the heat insulation layer is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 95%, and the thickness is 0.6mm; the single-layer transition layer structure (that is, only one filter layer) is also adopted between the heat insulation layer 5 and the protective layer 6, which is Mo and ZrO 2 mixed layer of ZrO 2 The content is 55%, and the thickness is 0.14mm; the protective layer 6 is a pure metal Mo coating.

Embodiment 3

[0036] Different from Example 1 and Example 2, the base layer 2 is pure metal Mo; the first transition layer 3 between the heat insulating layer 5 and the base layer 2 is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 30%, the thickness is 0.1mm; the heat insulation layer is Mo and ZrO 2 hybrid coating of ZrO 2 The content is 60%, and the thickness is 0.3 mm; there is no transition layer between the heat insulation layer 5 and the protective layer 6; the protective layer 6 is a pure metal Mo coating.

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Abstract

The invention provides a thermal barrier coating which comprises a base layer, a heat-isolation layer and a protective layer. At least one transition layer is arranged between the base layer and the heat-isolation layer. According to the thermal barrier coating, component preparation of the coating is reasonable, the preparation process is simple and convenient, and the transition layer and the heat-isolation layer of the coating contain oxides capable of forming oxidation films easily. Besides, the content of the oxides has gradient changes, so that the thermal barrier coating has good thermal shock resistance. Meanwhile, high-temperature particle erosion resistance is outstanding.

Description

technical field [0001] The invention relates to the technical field of cermet coatings, in particular to a thermal barrier coating and a preparation method thereof. Background technique [0002] Thermal barrier coating (Thermal Barrier Coating) is a layer of ceramic coating, which is deposited on the surface of high-temperature resistant metals or superalloys. Devices (such as engine turbine blades) can operate at high temperatures, and can improve the thermal efficiency of devices (engines, etc.) to more than 60%. [0003] In recent years, with the development of aero-engines towards high flow ratio, high thrust-to-weight ratio and high turbine inlet temperature, the gas temperature and gas pressure in the engine combustion chamber have been continuously increasing. When the thrust-to-weight ratio of the engine reaches 20, the gas inlet temperature will exceed 2000°C. This temperature has exceeded the temperature that the nickel-based superalloy used to manufacture turbine...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/06
CPCY02T50/60
Inventor 郑华龙
Owner 江苏海泰新材料科技有限公司
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