Zirconium oxide thermal barrier coating for turbine buckets of gas turbine and preparation method thereof

A technology of gas turbines and thermal barrier coatings, which is applied to coatings, mechanical equipment, machines/engines, etc., can solve the problems of difficult control and the influence of high-temperature corrosion resistance of coatings, so as to improve service life and facilitate control of process parameters , good plasticity and long-term high-temperature oxidation corrosion resistance

Active Publication Date: 2011-06-15
沈阳天贺新材料开发有限公司
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AI Technical Summary

Problems solved by technology

However, the liquid phase precursor will undergo complex transitions in the flame flow, among which the plasma chemical reaction is the most critical and complex change, so it is difficult to control; and when the precursor sol is prepared, Cl - Ions and other harmful ions and impurities have a great influence on the high temperature corrosion resistance of the coating

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] The base body of the gas turbine blade is K452 alloy, and the bonding layer material is Co-20.5, Cr-22.4, Al-8.56, Y-0.78, Ni-balance; the ceramic layer material is yttria-stabilized zirconia (ZrO 2 / (5~8%)Y 2 o 3 ).

[0034] A method of preparing a thermal barrier coating for a gas turbine blade has the following steps:

[0035] (1) Preparation of material rods for evaporation: the metal targets are NiCoCrAlY and (ZrO 2 / (5~8%)Y 2 o 3 ) alloy rods, using a vacuum induction furnace to repeatedly smelt the alloy rods at 1600°C for 3 times, with a melting power of 40KW, a working frequency of 4KHz, a vacuum degree of 0.3Pa, a diameter of 70mm, and a length of 200mm;

[0036] (2) Pretreatment of the substrate: After the substrate is polished with 800# sandpaper, it is ultrasonically cleaned in acetone and absolute ethanol for 10 minutes, dried and installed on the substrate support frame, and the substrate support is sent into the vacuum chamber ;

[0037] (3) Place...

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PUM

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Abstract

The invention relates to a zirconium oxide thermal barrier coating for turbine buckets of a gas turbine and a preparation method thereof. The zirconium oxide thermal barrier coating for the turbine buckets of the gas turbine is characterized in that adhesive layer materials and ceramic layer materials are plated on a metal surface; the adhesive layer materials include the following materials in percentage by weight: 15-30% of Co, 20-30% of Cr, 6-16% of Al, 0.2-1.0% of Y, and the balance of Ni; and the ceramic layer materials are zirconium oxide (ZrO2/(5-8%)Y2O3) with stable yttrium oxide. The prepared zirconium oxide thermal barrier coating has compactness, good combining capacity with a base body and good thermal cycle resisting capacity and high temperature corrosion resisting capacity.

Description

technical field [0001] The invention relates to a high temperature protection method, in particular to a zirconia thermal barrier coating for gas turbine blades coated with a layer of bonding layer material and ceramic layer material on the metal surface by electron beam physical vapor deposition technology And preparation method, belong to the C23C4 / 10(2006.01)I technical field in the International Patent Classification. Background technique [0002] Gas turbine blades face harsh service environments. The operating temperature range of gas turbine blades for general purposes is 960°C to 1100°C, and the gas temperature of gas turbines in military aircraft is as high as 1600°C. However, the maximum working temperature of nickel-based superheat-resistant alloys used to produce turbine blades is only 1100 °C. With the increase of gas temperature in gas turbines, compared with the development of new high-temperature heat-resistant alloy material substrates, the cost of devotin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C14/06C23C14/30F01D5/28
CPCY02T50/60
Inventor 高淑春胡金玲杨升山
Owner 沈阳天贺新材料开发有限公司
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