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Novel coating with composite structure and preparation method thereof

A composite structure and coating technology, applied in coating, metal material coating process, superimposed layer plating, etc., can solve the problem of lack of high temperature resistance, oxidation resistance and thermal erosion resistance, restriction of engine turbine performance, adhesion Oxidation failure of the layer and other problems, to achieve the effect of improving the thermal cycle resistance and the overall performance of the equipment, improving the industrial production efficiency, and improving the film adhesion

Inactive Publication Date: 2012-07-04
BEIJING GENERAL RES INST OF MINING & METALLURGY
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Problems solved by technology

In the existing technical solutions, the commonly used porous zirconia ceramic materials can meet the high-temperature heat insulation and sealing functions of the coating, but the porous structure is easily eroded by high-pressure air flow, and the oxidizing atmosphere is easy to pass through the pores to reach the bonding layer. , resulting in the oxidation failure of the bonding layer
In the prior art, there is a lack of special thermal barrier sealing coatings with high temperature resistance, oxidation resistance, thermal erosion resistance and good dynamic sealing performance, which restricts the performance of the engine turbine

Method used

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  • Novel coating with composite structure and preparation method thereof
  • Novel coating with composite structure and preparation method thereof
  • Novel coating with composite structure and preparation method thereof

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preparation example Construction

[0033] The embodiment of the present invention also provides a kind of preparation method of novel composite structural coating, such as figure 2 Shown is a schematic flow chart of the preparation method of the novel composite structural coating provided by the embodiment of the present invention, figure 2 Including:

[0034] Step 21: Carry out pretreatment of oil removal, rust removal, sandblasting or shot blasting on the surface of the turbine alloy substrate.

[0035] In this step, the alloy matrix includes iron-based alloys, cobalt-based superalloys, nickel-based superalloys, or cobalt-nickel superalloys with different mass ratios (wherein, Ni: 30-74.5wt%, Co: 25-66.5wt%) %).

[0036] Step 22: Spray on the pre-treated surface to prepare a bonding primer.

[0037] In this step, in the bonding bottom layer (ie MCrAlY layer), M is cobalt Co, nickel Ni or cobalt Co, nickel Ni alloy; Cr is chromium; Al is aluminum; Y is yttrium.

[0038] The specific spraying method is: u...

specific Embodiment approach 1

[0047]In this embodiment, first, pretreatment is carried out on the surface of the cobalt superalloy substrate by degreasing and derusting shot blasting methods; secondly, supersonic flame spraying is used on the pretreated surface to prepare a NiCrAlY bonding bottom layer with a thickness of 160 μm; and then on the NiCrAlY A zirconia ceramic layer was prepared by low-pressure plasma spraying on the surface of the bonded bottom layer, with a thickness of 800 μm; finally, a thin-film aluminum layer was prepared on the surface of the zirconia ceramic layer by chemical vapor deposition technology, and oxidized to obtain Al 2 o 3 For a dense surface layer, the oxidation temperature is 200°C, the oxygen pressure is 1.0MPa, and the thickness is 5μm.

specific Embodiment approach 2

[0049] In this embodiment, first, pretreatment is carried out on the surface of cobalt and nickel superalloy substrates by degreasing and derusting shot blasting methods, wherein Ni: 50wt%, Co: 50wt%; secondly, explosive spraying is used on the pretreated surface to prepare The NiCoCrAlY bonded bottom layer has a thickness of 250 μm; then supersonic plasma spraying is used on the surface of the NiCrAlY bonded bottom layer to prepare a zirconia ceramic layer with a thickness of 700 μm; finally, a thin film aluminum layer is prepared on the surface of the zirconia ceramic layer by chemical vapor deposition technology, And oxidized to prepare Al 2 o 3 For a dense surface layer, the oxidation temperature is 220°C, the oxygen pressure is 1.0MPa, and the thickness is 4μm.

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Abstract

Embodiments of the invention discloses a novel coating with a composite structure and a preparation method thereof; the coating is a composite coating with a three-layer structure, wherein a bonding layer is prepared on a turbine alloy substrate surface by a high speed flame spraying method; a porous zirconia ZrO2 ceramic layer is prepared on the bonding layer surface by plasma spraying; a film aluminium layer is prepared on the ceramic layer surface by vapour deposition technology, and is oxidized into a dense alumina Al2O3 surface layer. The composite coating prepared by the method can reduce oil consumption of the turbine engine, and increase engine efficiency and thermal cycling resistance; and the service life of the turbine and the whole performance of the equipment are improved.

Description

technical field [0001] The invention relates to the technical field of turbine engines, in particular to a novel composite structural coating and a preparation method thereof. Background technique [0002] At present, in the development of high-performance turbine engines (such as aviation, power plants, and ships), it is an eternal pursuit to increase the inlet temperature and pressure of the engine. The engine turbine is one of the key components to increase the temperature and pressure of the engine inlet. Its material properties and mechanical properties must meet the requirements of high temperature resistance, high pressure gas erosion and harsh environments. The design temperature and pressure of the turbine engine are increased, which can no longer meet the urgent needs of the engine only by relying on the cooling system and the development of new materials. The use of coating protection technology is a research focus in this field. Coating protection can meet the re...

Claims

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Application Information

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IPC IPC(8): C23C28/00C23C4/06C23C4/10C23C14/08C23C4/073C23C4/11C23C4/129C23C4/134
Inventor 袁建鹏章德铭沈婕任先京高峰张乐
Owner BEIJING GENERAL RES INST OF MINING & METALLURGY
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