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A kind of anti-CMAS corrosion micro-nano composite structure thermal barrier coating and preparation method thereof

A technology of composite structure and thermal barrier coating, which is applied in the coating, metal material coating process, superimposed layer plating, etc., can solve the problems of inconsistent thermal expansion coefficient, cracks in the dense layer, and no large-scale application. Achieve the effect of good bonding force, low price, and reduce spraying cost

Inactive Publication Date: 2019-01-15
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] There are a large number of patent applications for the above three aspects at home and abroad, the essence of which is to form a dense protective layer on the surface of the ceramic layer, so that the molten CMAS cannot penetrate through to resist the corrosion of CMAS
But no matter how it is designed, the thermal expansion coefficient of the dense layer must be inconsistent with the underlying ceramic layer. Under high temperature thermal cycle conditions, the dense layer is more prone to cracks and failures
Therefore, the above-mentioned CMAS protection technology has not been applied on a large scale in actual production

Method used

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  • A kind of anti-CMAS corrosion micro-nano composite structure thermal barrier coating and preparation method thereof
  • A kind of anti-CMAS corrosion micro-nano composite structure thermal barrier coating and preparation method thereof
  • A kind of anti-CMAS corrosion micro-nano composite structure thermal barrier coating and preparation method thereof

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preparation example Construction

[0046] The invention provides a method for preparing a CMAS corrosion-resistant micro-nano composite structure thermal barrier coating, comprising the following steps:

[0047] The first step, substrate pretreatment;

[0048] The surface of the superalloy substrate is polished on 200#, 400#, 600#, 800# sandpaper in turn, then ultrasonically cleaned for 10 minutes, and sandblasting pretreatment to make the surface roughness Ra<2. The high temperature alloy matrix is ​​K3 alloy.

[0049] The second step is to prepare NiAlX (X selects Dy, Hf or Zr, etc.), NiCoCrAlY or NiAlPt bonding layer on the substrate.

[0050] (A) NiAlX (X selects Dy, Hf or Zr, etc.) or NiCoCrAlY bonding layer prepared by low-pressure plasma spraying method;

[0051] Install the substrate pretreated in the first step in the fixture of the low-pressure plasma spraying equipment, and then install it on the automatic workpiece moving table in the vacuum chamber, and adjust the main process parameters: the cur...

Embodiment 1

[0080]Embodiment 1: Preparation on the surface of the superalloy substrate: low-pressure plasma spraying NiCoCrAlY bonding layer+plasma evaporation deposition of the first ceramic layer YSZ+plasma evaporation deposition of the thermal barrier coating of the second ceramic layer YSZ, the specific steps are as follows:

[0081] In the first step, the surface of the superalloy substrate is polished on 200#, 400#, 600#, and 800# sandpaper in sequence, then ultrasonically cleaned for 10 minutes, and pretreated by sandblasting to make the surface roughness Ra<2. The high temperature alloy is K3 alloy.

[0082] In the second step, a NiCoCrAlY bonding layer is prepared on the substrate by low-pressure plasma spraying.

[0083] Install the alloy substrate in the fixture of the low-pressure plasma spraying equipment, and then install it on the automatic workpiece moving table in the vacuum chamber, adjust the main process parameters: the current is 600A, the voltage is 40kw, the powder ...

Embodiment 2

[0095] Embodiment 2: Preparation on the surface of the superalloy substrate: electron beam physical vapor deposition NiAlDy bonding layer+electron beam physical vapor deposition first ceramic layer YSZ+plasma evaporation deposition thermal barrier coating of the second ceramic layer YSZ, the specific steps are as follows:

[0096] In the first step, the surface of the superalloy substrate is polished on 200#, 400#, 600#, and 800# sandpaper in sequence, then ultrasonically cleaned for 10 minutes, and pretreated by sandblasting to make the surface roughness Ra<2. The high temperature alloy is K3 alloy.

[0097] In the second step, an electron beam physical vapor deposition method is used to prepare a NiAlDy bonding layer on the substrate, and the preparation steps are as follows:

[0098] (1) Use high-purity nickel (Ni), high-purity aluminum (Al) and dysprosium (Dy) with a purity of 99.7wt.%. According to the design distribution ratio, the Al content is 50mol%, the Dy content is...

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Abstract

The invention discloses a preparation method of a CMAS corrosion-resistance micronanometer composite thermal barrier coating layer. The thermal barrier coating layer includes a bonding layer prepared on an alloy basal body, a first ceramic layer and a second ceramic layer; the first ceramic layer is a yttrium oxide part stable zirconium oxide coating layer, can be prepared by atmosphere plasma spraying, an electronic beam physical vapor deposition method or a plasma evaporation deposition method, and has a thickness of 50-200 microns; and the second ceramic layer is a CMAS-resistance coating layer prepared by a plasma evaporation deposition system, and has a thickness of 1-100 microns. At high temperature, molten CMAS is not wet on the surface of the prepared second ceramic layer. The prepared multi-layer thermal barrier coating layer system including the bonding layer, the first ceramic layer and the CMAS-resistance second ceramic layer can effectively stop permeation of molten CMAS, and is excellent in molten CMAS corrosion resistance.

Description

technical field [0001] The invention relates to the technical field of thermal barrier coating corrosion and protection, in particular to a CMAS corrosion-resistant thermal barrier coating with a micro-nano composite structure and a preparation method thereof. Background technique [0002] Thermal Barrier Coatings (TBCs for short) is one of the key technologies of advanced aero-engine hot-end components. With the increase of engine thrust-to-weight ratio, the gas inlet temperature before the turbine has also increased significantly. By the time of the fourth-generation fighter jets, the gas inlet temperature has reached 1650°C. It is difficult to meet the development requirements of aero-engines solely by relying on high-temperature alloy single crystal technology. Later, NASA of the United States proposed the concept of thermal barrier coating, which is to prepare a layer of high temperature resistant and high heat insulation protective coating on the surface of superalloy ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/134C23C14/32C23C14/30C23C14/02C23C14/08C23C4/11C23C28/00C23C4/08C23C4/073C23C14/16C25D3/50C23C10/48
CPCC23C4/08C23C10/48C23C14/025C23C14/081C23C14/083C23C14/16C23C14/30C23C14/32C23C28/321C23C28/3215C23C28/3455C25D3/50Y02T50/60
Inventor 郭洪波邓阳丕魏亮亮
Owner BEIHANG UNIV
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