Anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and preparation method thereof

A thermal barrier coating and long-life technology, applied in the coating, metal material coating process, superimposed layer plating, etc., can solve the problems of YSZ coating corrosion, short thermal cycle life of thermal barrier coating, etc., to achieve Ease of preparation, improved CMAS corrosion resistance, and improved thermal shock life

Active Publication Date: 2016-08-17
TIANJIN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] In view of the existing problems in the existing technology, in the existing 2 Zr 2 o 7 On the basis of the TEC and fracture toughness of the coating material, the present invention proposes a long-life thermal barrier coating resistant to CMAS corrosion and ultra-high temperature and its preparation method, which not only improves the RE 2 Zr 2 o 7 The thermal insulation and CMAS corrosion resistance of the coating also solves the RE 2 Zr 2 o 7 Short Thermal Cycle Life of Thermal Barrier Coatings and Problems of Existing YSZ Coatings Suffering from CMAS Corrosion

Method used

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  • Anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and preparation method thereof
  • Anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and preparation method thereof
  • Anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and preparation method thereof

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preparation example Construction

[0041] The invention provides a method for preparing a long-life thermal barrier coating resistant to CMAS corrosion and ultra-high temperature, comprising the following steps:

[0042] Step 1, substrate preparation and pretreatment

[0043] Select the high-temperature alloy with the grade of IN600, K3 or DD6 as the substrate, polish the substrate with 200#, 400#, 600#, and 800# sandpaper in sequence, put the polished substrate into the acetone solution, clean it with ultrasonic waves, and then dry it. Sandblast the substrate to make its surface roughness Ra>15.

[0044] Step 2, prepare the MCrAlX bonding layer on the surface of the substrate

[0045] A) Preparation of MCrAlX bonding layer by electron beam physical vapor deposition

[0046] a) Prepare the target for the bonding layer

[0047] The material of the bonding layer is MCrAlX alloy, M is Ni, Co or a combination of the two, X is one of Y, Hf, Si, Pt or a combination of both, and the bonding layer is weighed in prop...

Embodiment 1

[0069] When the thermal barrier coating TC2(La 0.99 sc 0.01 ) 2 Zr 2 o 7 For / TC1 YSZ / BC, the specific steps are as follows:

[0070] Step 1: Substrate preparation and pretreatment

[0071] Choose IN600 nickel-based superalloy as the substrate, polish the substrate with 200#, 400#, 600#, and 800# sandpaper in sequence, put the polished substrate in acetone, clean it with ultrasonic waves, dry it, and then sandblast the substrate Treatment to make the surface roughness Ra>15. Step 2: Deposit a bonding layer on the surface of the substrate

[0072] 1) Prepare the target for the bonding layer

[0073]The material of the bonding layer is a NiCoCrAlY alloy, and the composition (percentage by weight) is 54.2% Ni, 18.2% Co, 19.6% Cr, 7.0% Al, 1.0% Y, and the bond is weighed according to the proportion The components of the alloy in the material of the layer are smelted at 1600°C to obtain the target material of the bonding layer.

[0074] 2) Deposition of the bonding layer ...

Embodiment 2

[0086] When the thermal barrier coating TC2(Nd 0.5 sc 0.5 ) 2 Zr 2 o 7 When / TC1 YSZ / BC, specifically include the following

[0087] Step 1: Substrate preparation and pretreatment

[0088] Select K3 high-temperature alloy as the substrate, polish the substrate with 200#, 400#, 600#, and 800# sandpaper in sequence, put the polished substrate in acetone, clean it with ultrasonic waves and dry it, and then sandblast the substrate. Make its surface roughness Ra>15. Step 2: Deposit a bonding layer on the surface of the substrate

[0089] 1) Prepare the target for the bonding layer

[0090] The material of the bonding layer is CoCrAlY alloy, and its composition (weight percentage) is 67.4% Co, 22% Cr, 8.6% Al, and 2.0% Y. The components of the alloy in the material of the bonding layer are weighed according to the proportion, and the target material of the bonding layer obtained is melted at 1600°C.

[0091] 2) Deposition of the bonding layer

[0092] The main process para...

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Abstract

The invention relates to an anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and a preparation method thereof. The thermal barrier coating is sequentially provided with a binding layer, a first ceramic layer and a second ceramic layer on a matrix from bottom to top, the binding layer is made of an MCrAlX alloy, M refers to Ni, or Co or a composition of Ni and Co, X refers to one of or a composition of two of Y, Hf, Si and Pt, the first ceramic layer is made of YSZ, and the second ceramic layer is rare earth zirconate with Sc2O3. The preparation method includes that an electron beam physical vapor deposition method or an atmosphere plasma spraying method are adopted. Sc2O3 is doped in a rare earth zirconate coating, so that heat conductivity of the coating can be further lowered, toughness of the coating is improved, anti-CMAS-corrosion capability of the coating is improved, thermal cycling life of the coating can be prolonged, and high-temperature stability of the coating under CMAS coupling action can be improved.

Description

technical field [0001] The invention relates to the technical field of high-temperature corrosion and protection of thermal barrier coatings and its preparation, and specifically refers to a doped Sc coating with anti-CMAS corrosion, high heat insulation and long thermal cycle life. 2 o 3 Rare earth zirconate thermal barrier coatings and methods for their preparation. Background technique [0002] Thermal barrier coatings (TBCs) are high temperature resistant, corrosion resistant, high heat insulating ceramic films coated on the surface of superalloy components. Research has found that the turbine blades of aero-engines will not only be subjected to high temperature, thermal fatigue and mechanical loads, but also be subjected to chemical corrosion, erosion and erosion, which will eventually lead to the failure of the coating. Among them, CaO, MgO, Al 2 o 3 and SiO 2 (referred to as CMAS) composed of environmental deposits have a great impact on the life of thermal barri...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C28/00C23C14/30C23C4/134C23C14/08C23C14/14C23C14/16C23C4/073C23C4/11
CPCC23C14/08C23C14/083C23C14/14C23C14/16C23C14/30C23C28/3215C23C28/3455
Inventor 郭磊李明珠赵孝祥王彩妹叶福兴
Owner TIANJIN UNIV
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