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Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine

a technology of thermal barrier coating and gas turbine, which is applied in the direction of superimposed coating process, machines/engines, mechanical equipment, etc., can solve the problems of increased thermal conductivity of topcoat, reduced peeling resistance, and increased cost of large-scale gas turbines or the like, so as to achieve adsorption and peeling resistance. high, the effect of high peeling resistan

Inactive Publication Date: 2010-03-11
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The present invention provides a thermal barrier coating material that has a high thermal barrier property and peeling resistance, as well as a method of producing the coating. The coating material consists of a metal binding layer and a ceramic layer that is partially stabilized zirconia with microcracks that extend in the thickness direction. The ceramic layer has a porosity of 1-30% and a density of 4-6.5 g / mm3. The thermal conductivity of the ceramic layer is 0.5-5 w / m·K. The coating material can be used on gas turbine members to improve durability in high-temperature environments. The invention also provides a method of producing the coating and a raw material for thermal spraying the coating.

Problems solved by technology

However, since the application process for the electron beam physical vapor deposition requires a large amount of time, application to a large-scale gas turbine or the like is difficult in terms of cost.
Since the thermal conductivity of the obtained film becomes approximately 30% greater than that of porous ceramic, the film thickness must be made large, thus presenting a further difficulty in use.
As for the method of laminating the ceramic layer while forming the microcracks by thermal spraying, the formation of the microcracks requires a dense ceramic layer, leading to the problem that the topcoat is increased in thermal conductivity and thus lowered in thermal barrier property.
Furthermore, the microcracks are frequently formed not only in the thickness direction but also in the layer direction, leading to the problem that the ceramic layer peels in layers.
However, in these methods, the mixing of zirconia and yttria is not uniform due to the diffusion rate of zirconia being slower and the like.
Thus, it is difficult to produce completely stabilized zirconia.

Method used

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  • Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine
  • Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine
  • Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine

Examples

Experimental program
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Effect test

examples 1 to 15

[0116]The sample Nos. 1 to 15 described below were prepared.

(Sample No. 1)

[0117]The surface of the base material was grid-blasted with Al2O3 particles and put in a state suitable for low pressure plasma spraying. A CoNiCrAlY alloy layer was then formed to a thickness of 0.1 mm by the low pressure plasma spraying. A ceramic layer comprising porous and partially stabilized ZrO2, which had been partially stabilized by 8 wt % of Y2O3 as an additive, was then formed to a thickness of 0.5 mm by atmospheric pressure plasma spraying. Then, while cooling the rear surface of the base material, the top surface of the ceramic layer was subject to 30 seconds×100 times of irradiations of a laser beam from a carbon dioxide laser. Thus, the heat cycle was repeated. In this process, the top surface of the ceramic layer was heated to a maximum temperature of 1400° C. The irradiation area per spot of the laser beam was 177 mm2 (beam diameter: 15 mm). The entire sample was then cooled to room temperatu...

examples 101 to 136

[0141]Sample Nos. 101 to 136, described below, were prepared.

(Sample No. 101)

[0142]The top surface of the base material was grid-blasted with Al2O3 grains and put in a state suitable for low pressure plasma spraying. A CoNiCrAlY alloy layer was then formed to a thickness of 0.1 mm by the low pressure plasma spraying. A ZrO2-10 wt % Dy2O3-0.1 wt % Yb2O3 layer was then formed to a thickness of 0.5 mm by atmospheric pressure plasma spraying.

(Sample No. 102)

[0143]The top surface of the base material was grid-blasted with Al2O3 grains and put in a state suitable for low pressure plasma spraying. A CoNiCrAlY alloy layer was then formed to a thickness of 0.1 mm by the low pressure plasma spraying. A ZrO2-10 wt % Dy2O3-6 wt % Yb2O3 layer was then formed to a thickness of 0.5 mm by atmospheric pressure plasma spraying.

(Sample No. 103)

[0144]The top surface of the base material was grid-blasted with Al2O3 grains and put in a state suitable for low pressure plasma spraying. A CoNiCrAlY alloy la...

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Abstract

A thermal barrier coating material, containing a metal binding layer laminated on a base material and ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrO2 which is partially stabilized by additives of Dy2O3 and Yb2O3.

Description

[0001]This is a divisional application of U.S. application Ser. No. 10 / 478,690, filed Dec. 8, 2003, which is a 371 of PCT / JP02 / 05945 filed on Jun. 14, 2002.TECHNICAL FIELD[0002]The invention relates to a thermal barrier coating material, a method of production thereof, and a gas turbine member and a gas turbine to which the thermal barrier coating material is applied, and relates to useful arts which are applicable, for example, to thermal barrier coatings for rotor blades and stator blades of industrial gas turbines as well as for combustors and other parts used in high-temperature environments.BACKGROUND ART[0003]Since high-temperature parts, such as rotor blades and stator blades of industrial gas turbines, and flame tubes, tail pipes, and split rings of combustors, etc., are used in high-temperature environments, they are generally provided with a thermal barrier coating on the surface.[0004]FIG. 11 is a sectional view of a conventional thermal barrier coating.[0005]The conventi...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): B05D1/08B05D3/06C23C4/08C23C4/10C23C4/18C23C28/00F01D5/28
CPCC23C4/085C23C4/105C23C4/18F01D5/288F05D2230/40C23C28/3455F05D2230/312F05D2230/311F05D2230/90F05D2300/2118C23C28/3215F05D2230/31C23C4/11C23C4/073
Inventor TORIGOE, TAIJIMORI, KAZUTAKAOKADA, IKUOAOKI, SUNAOTAKAHASHI, KOUJIOHARA, MINORUHIRATA, TAKEHIKOKANEKO, HIDEAKI
Owner MITSUBISHI HEAVY IND LTD
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