A kind of protective coating for single crystal superalloy and preparation method thereof

A technology of superalloy and protective coating, applied in the direction of metal material coating process, coating, metal layered products, etc., can solve the problems of limited application, easy peeling and failure of coating, thermal-mechanical fatigue, etc., to improve strain tolerance , Solve the problem of poor interface bonding force and improve the effect of interface bonding force

Active Publication Date: 2015-08-05
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

During service, the surface of MCrAlY coating cannot rapidly form continuous and dense Al 2 o 3 film, and the YSZ ceramic surface layer prepared by the atmospheric plasma spraying method has a lamellar structure, which is easy to cause thermal fatigue under the condition of cold and hot cycles, and makes the coating easy to peel off and fail, which limits its application on high-speed rotating turbine blades

Method used

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  • A kind of protective coating for single crystal superalloy and preparation method thereof
  • A kind of protective coating for single crystal superalloy and preparation method thereof
  • A kind of protective coating for single crystal superalloy and preparation method thereof

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Embodiment Construction

[0032] A protective coating for single crystal superalloy, the protective coating is composed of a PtAl metal bottom layer and a columnar crystal structure YSZ ceramic surface layer. Wherein the PtAl metal bottom layer is a platinum-modified aluminide coating, and the columnar crystal structure YSZ ceramic surface layer is 6-8%Y 2 o 3 Partially stabilized ZrO 2 Columnar crystal structure ceramic surface layer.

[0033] A method for preparing the protective coating for the above-mentioned single crystal superalloy, the preparation method comprises the steps of:

[0034] (1) Preparation steps of the PtAl metal bottom layer

[0035] The preparation steps of the PtAl metal bottom layer are as follows: first, a 10 μm Pt layer is prepared on the surface of the single crystal superalloy blade substrate by electroplating, and then aluminized to the Pt layer by an embedding method, and the thickness of the prepared PtAl metal bottom layer is 50μm;

[0036] (2) Post-treatment steps...

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Abstract

The invention relates to a protective coating of a single crystal high-temperature alloy as well as a preparation method thereof. The technical scheme is as follows: the protective coating of the single crystal high-temperature alloy consists of a PtAl metal bottom layer and an YSZ (Yttria Stabilized Zirconia) ceramic surface layer in a columnar crystal structure. The preparation method of the protective coating of the single crystal high-temperature alloy comprises the following steps: a preparation step of the PtAl metal bottom layer, a post-treatment step of the PtAl metal bottom layer, a preparation step of the YSZ ceramic surface layer in the columnar crystal structure, and a post-treatment step of the YSZ ceramic surface layer in the columnar crystal structure. The invention can provide the protective coating of the single crystal high-temperature alloy, which is good in interface bonding, excellent in oxidation resistance and high in stress tolerance, as well as the preparation method thereof.

Description

technical field [0001] The invention relates to a protective coating and a preparation method thereof, in particular to a protective coating for a single crystal superalloy and a preparation method thereof. Background technique [0002] In order to continuously improve the performance of aero-engines (high thrust-to-weight ratio, low fuel consumption), it is required to continuously increase the gas temperature at the turbine inlet. The turbine blades, the core components of the engine, serve in very harsh environments. In addition to bearing aerodynamic loads and centrifugal loads, they are also subjected to the impact and erosion of high-temperature gas for a long time. Although single crystal superalloy blades have excellent high-temperature mechanical properties, their high-temperature oxidation resistance cannot meet the needs of use. The surfaces of advanced aero-engine turbine blades at home and abroad are coated with protective coatings without exception to improve ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B15/04B32B18/00C23C14/06C23C14/30
Inventor 程玉贤袁福河王璐张春刚刘艳
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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