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A composite adhesive layer material resistant to 1200°C high temperature oxidation and gas thermal corrosion resistance and its preparation method

A high-temperature oxidation and bonding layer technology, which is applied in chemical instruments and methods, metal material coating technology, coatings, etc., can solve the problem of reducing the mechanical properties of high-temperature alloy substrates, coating resistance to high-temperature oxidation, and unable to cope with the working environment of turbine engines Marine corrosive environment, coating thickness, microstructure and chemical composition cannot be precisely controlled to achieve the effect of improving anti-oxidation performance, inhibiting the formation and reducing growth rate

Inactive Publication Date: 2016-01-20
BEIHANG UNIV
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Problems solved by technology

But it has great disadvantages at the same time: First, a large number of voids are formed at the metal / oxide film interface during high temperature oxidation, which affects the adhesion of the oxide film and causes the oxide film to detach (Reference 1: J.A.Haynes, B.A.Pint, K.L.More, Y . Zhang, I.G. Wright. Influence of sulfur, platinum, and hafnium on the oxidation behavior of CVDNi Albond coatings. Oxidation of Metals, 58 (2002): 513-544.)
Refractory elements (such as W, Mo, Ta, Re, etc.) in the substrate diffuse to the coating, and Al elements in the coating diffuse to the substrate, resulting in the formation of the Secondary Reaction Zone (SRZ) (Reference 2: WalstonW. S.,SchaefferJ.C.,MurphyW.H..ANewTypeofMicrostructuralInstabilityinSuperalloys-SRZ[J].Superalloys1996,ed.KissingerR.D., etal.:9-18), seriously reduced the mechanical properties of the superalloy matrix and the coating High temperature oxidation resistance
The modification methods of the existing NiAl coating usually only focus on the improvement of its oxidation resistance, ignoring the importance of improving its thermal corrosion resistance, and cannot cope with the actual working environment of the turbine engine, especially the marine corrosion environment, so that the NiAl system metal Practical performance of the tie layer is greatly compromised
However, the traditional Cr / Si method to prepare coatings cannot accurately control the coating thickness, structure and chemical composition. This technical problem has always hindered the development of this type of coating.

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  • A composite adhesive layer material resistant to 1200°C high temperature oxidation and gas thermal corrosion resistance and its preparation method
  • A composite adhesive layer material resistant to 1200°C high temperature oxidation and gas thermal corrosion resistance and its preparation method
  • A composite adhesive layer material resistant to 1200°C high temperature oxidation and gas thermal corrosion resistance and its preparation method

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preparation example Construction

[0040] To prepare the Ni(Ru)Al / NiAlHfCrSi double-layer structure bonding layer, the present invention adopts the electron beam physical vapor deposition method to prepare, and the preparation method includes the following steps:

[0041] The first step is to prepare the substrate and evaporation rod;

[0042] (A) Grind the substrate with 150#, 400#, 800# SiC water abrasive paper, so that the surface roughness of the substrate is Ra<0.8; clean the polished substrate with acetone and ethanol for about 10 minutes, and dry it for later use.

[0043] (B) Using high-purity nickel (Ni), high-purity aluminum (Al), pure chromium (Cr), pure silicon (Si) and hafnium (Hf) with a purity of 99.7% (mass percentage), according to the designed composition ratio, Al The content is 40-55 at%, the content of Hf is 0.05-0.5 at%, the content of Cr is 0.5-2 at%, the content of Si is 1-3 at%, and the balance is Ni. Polish the surface of the nickel block and the aluminum block to ensure that there is...

Embodiment 1

[0057] The first step is to prepare the substrate and evaporation rod;

[0058] (A) The substrate is a Ni-based single crystal superalloy, the brand is N5, and the size is 10×10×2mm; use 150#, 400#, 800# SiC water abrasive paper to polish the substrate so that the surface roughness of the substrate is Ra<0.8; Ultrasonic cleaning for 10 minutes.

[0059] (B) Using high-purity nickel (Ni), high-purity aluminum (Al), pure chromium (Cr), pure silicon (Si) and hafnium (Hf) with a purity of 99.7%, according to the designed composition ratio, the Al content is 40at% , the Hf content is 0.05at%, the Cr content is 0.5at%, the Si content is 1at%, and the balance is Ni. Polish the surface of nickel block and aluminum block to ensure the existence of fresh oxide film on the metal surface, then ultrasonically clean it with absolute ethanol and acetone for about 15 minutes, dry it, and finally make the target material by arc melting method. spare.

[0060] In the second step, a Ru layer ...

Embodiment 2

[0074] The first step, prepare the substrate and evaporation rod

[0075] (A) The substrate is a Ni-based superalloy, the brand is DZ125, and the size is 10×8×3mm; the substrate is polished with 150#, 400#, 800# SiC water abrasive paper to make the surface roughness of the substrate Ra<0.8; acetone and Ultrasonic cleaning with absolute ethanol for 10 minutes.

[0076] (B) Using high-purity nickel (Ni), high-purity aluminum (Al), pure chromium (Cr), pure silicon (Si) and hafnium (Hf) with a purity of 99.7%, according to the designed composition ratio, the Al content is 45at% , the Hf content is 0.1at%, the Cr content is 1at%, the Si content is 1at%, and the balance is Ni. Polish the surface of the nickel block and the aluminum block to ensure that there is no oxide film on the metal surface, then ultrasonically clean it with absolute ethanol and acetone for about 15 minutes, and dry it. .

[0077] In the second step, a Ru layer is deposited on the substrate;

[0078] (A) If...

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Abstract

The invention discloses a compound binding layer material with 1200 DEG C high-temperature oxidization resistance and fuel gas thermal corrosion resistance and a preparation method of the compound binding layer material. The preparation method comprises the following steps of firstly, depositing a layer of Ru on a base body by adopting an electroplating or electron beam physical vapor deposition method; then, depositing a layer of NiAlHfCrSi on the Ru layer by adopting the electron beam physical vapor deposition method; and finally, carrying out thermal treatment to obtain a Ni(Ru)Al / NiAlHfCrSi double-layer structure binding layer, wherein the content of Ru in the Ni(Ru) Al layer is gradually reduced from a base body surface layer to an outer layer direction in a gradient manner. The double-layer structure binding layer can be used for effectively blocking mutual diffusion between the base body and a coating to restrain formation of a second reaction region (SRZ), restrain formation of similar spinel in a thermal corrosion process and improve high temperature oxidization resistance and thermal corrosion resistance of a high-temperature alloy, and therefore, the double-layer structure binding layer is a novel thermal barrier coating binding layer material. The binding layer material can reach the anti-oxidation grade at 1200 DEG C, does not have the second reaction region by vacuum diffusion for 100 hours at 1100 DEG C; meanwhile, fuel gas thermal corrosion resistance is much higher than that of a common NiAl-series metal binding layer.

Description

technical field [0001] The present invention relates to a new thermal barrier coating bonding layer material and its preparation method, more specifically to a thermal barrier with a double-layer structure that is resistant to high temperature oxidation at 1200°C and resistant to gas thermal corrosion by applying electroplating and electron beam physical vapor deposition. Coating tie layer material. Background technique [0002] In order to meet the development needs of aero-engines, the materials used for turbine blades have developed from superalloys and directionally solidified crystalline alloys to single-crystal superalloys. The service temperature of materials has increased by nearly 300°C, which is close to the service limit temperature of metals. However, the new generation of gas turbine engines requires the turbine blades and guide vanes to work at temperatures between 1500°C and 1600°C for a long time. The service environment is extremely harsh, and the existing a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C14/34C25D3/50C23F17/00B32B5/14B32B15/01
Inventor 郭洪波潘露露宫声凯彭徽徐惠彬
Owner BEIHANG UNIV
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