A double ceramic layer thermal barrier coating system and its composite preparation process

A thermal barrier coating and preparation process technology, applied in metal material coating process, coating, melt spraying and other directions, can solve the problems of low thermal expansion coefficient of LCO, cracking and peeling of ceramic layer and bonding layer, etc. Good thermal cycle damage performance, improve anti-oxidation performance and prolong service life

Active Publication Date: 2020-04-28
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The lanthanum cerate (LCO) thermal barrier coating developed by the corresponding technology research and development team is an important breakthrough in the development of 1300°C thermal barrier coating material technology. Cracking and spalling due to residual thermal stress due to mismatch

Method used

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  • A double ceramic layer thermal barrier coating system and its composite preparation process
  • A double ceramic layer thermal barrier coating system and its composite preparation process
  • A double ceramic layer thermal barrier coating system and its composite preparation process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047] A dual ceramic layer thermal barrier coating system comprising a bond coat, a YSZ coating and a lanthanum cerate coating on a superalloy substrate;

[0048] Described bonding layer is MCrAlY bonding layer;

[0049] The YSZ coating is a yttria stabilized zirconia coating, namely ZrO 2 +8wt.%Y 2 o 3 ; Among them, the other ingredients and mass percentage contained are SiO 2 1.5%, Fe 2 o 3 0.9%, CaO 1.2%, MgO 1.0%, HfO 2 2.8%;

[0050] The MCrAlY bonding layer is a NiCrAlY bonding layer, the mass percent of each metal element is 25% for Cr, 10% for Al, 0.8% for Y, and the balance is Ni.

[0051] The thickness of the bonding layer is 85 μm, the thickness of the YSZ coating is 120 μm, and the thickness of the lanthanum cerate coating is 80 μm.

[0052] A composite preparation process of a double-ceramic layer thermal barrier coating system. According to the results of process optimization tests, the process parameters of each layer of the thermal barrier coating syst...

Embodiment 2

[0069] A dual ceramic layer thermal barrier coating system comprising a bond coat, a YSZ coating and a lanthanum cerate coating on a superalloy substrate;

[0070] Described bonding layer is MCrAlY bonding layer;

[0071] The YSZ coating is a yttria stabilized zirconia coating, namely ZrO 2 +7wt.%Y 2 o 3 ; Among them, the other ingredients and mass percentage contained are SiO 2 1.2%, Fe 2 o 3 0.7%, CaO 1.3%, MgO 1.2%, HfO 2 2.4%;

[0072] When the MCrAlY bonding layer is a NiCoCrAlTaY bonding layer, the mass percent of each metal element is 30% for Co, 25% for Cr, 12% for Al, 7.0% for Ta, 0.4% for Y, and the balance For you.

[0073] The thickness of the bonding layer is 200 μm, the thickness of the YSZ coating is 150 μm, and the thickness of the lanthanum cerate coating is 120 μm.

[0074] A composite preparation process of a double ceramic layer thermal barrier coating system is carried out according to the following steps:

[0075] Step 1, superalloy substrate pr...

Embodiment 3

[0089] A dual ceramic layer thermal barrier coating system comprising a bond coat, a YSZ coating and a lanthanum cerate coating on a superalloy substrate;

[0090] Described bonding layer is MCrAlY bonding layer;

[0091] The YSZ coating is a yttria stabilized zirconia coating, namely ZrO 2 +9wt.%Y 2 o 3 ; Among them, the other ingredients and mass percentage contained are SiO 2 1.6%, Fe 2 o 3 0.9%, CaO 1.0%, MgO 1.4%, HfO 2 2.9%;

[0092] When the MCrAlY bonding layer is a NiCrAlY bonding layer, the mass percent of each metal element is 20% for Cr, 14% for Al, 0.4% for Y, and the balance is Ni.

[0093] The thickness of the bonding layer is 200 μm, the thickness of the YSZ coating is 100 μm, and the thickness of the lanthanum cerate coating is 120 μm.

[0094] A composite preparation process of a double ceramic layer thermal barrier coating system is carried out according to the following steps:

[0095] Step 1, superalloy substrate pretreatment

[0096] Carry out t...

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Abstract

The invention provides a double-ceramic-layer thermal barrier coating system and a composite preparation technology thereof, and belongs to the technical field of coating. The double-ceramic-layer thermal barrier coating system includes a bonding layer on a high temperature alloy basal body, a YSZ coating and a lanthanum-cerium oxide coating. The composite preparation technology includes the stepsthat after the high temperature alloy basal body is preprocessed, a dense MCrAlY bonding layer is sprayed on the high temperature alloy basal body by a supersonic speed flame spraying device or explosive spraying, so that the MCrAlY bonding layer is obtained, wherein the HV0.3 of the MCrAlY bonding layer is 300-380, and the surface roughness Ra of the bonding layer is 5.0-9.0[mu]m; and the YSZ coating is sprayed on the surface of the MCrAlY bonding layer by an atmospheric plasma spraying device, and the double-ceramic-layer thermal barrier coating system is obtained. The thermal barrier coating system prepared by the technology has both super-high temperature resistance and satisfactory coating thermal cycling performance, and the thermal cycling life of the thermal barrier coating is prolonged.

Description

technical field [0001] The invention relates to the technical field of coating, in particular to a double ceramic layer thermal barrier coating system and a composite preparation process thereof. Background technique [0002] The high-temperature protection of the hot-end parts of the aero-engine is one of the key technologies in the manufacture of the aero-engine. The thermal barrier coating is made of high-temperature-resistant, low-thermal-conduction ceramic material and metal in the form of a coating to reduce the metal surface in high-temperature environments. A thermal protection technique for temperature. In advanced aero-engines, thermal barrier coatings can significantly reduce the surface temperature of the blade alloy, greatly prolong the working life of the blade, and improve the thrust and efficiency of the engine. In particular, the thermal barrier coating of the high-pressure turbine guide vane of the new advanced aero-engine needs to withstand the operating ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/129C23C4/126C23C4/134C23C4/073C23C4/11C22C19/05C22C19/03
CPCC22C19/03C22C19/058C23C4/073C23C4/11C23C4/126C23C4/129C23C4/134
Inventor 袁福河程玉贤张佳平王璐芦国强
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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