Reflective coatings to reduce radiation heat transfer

Details Reflective coatings to reduce radiation heat transfer Reflective coatings to reduce radiation heat transfer

2001-07-06

2003-11-25

Jones, Deborah (Department: 1775)

Stock material or miscellaneous articles

All metal or with adjacent metals

Composite; i.e., plural, adjacent, spatially distinct metal...

C428S632000, C428S633000, C428S655000, C428S680000, C428S469000, C428S699000, C428S701000, C428S702000, C428S698000, C428S336000, C416S24100B, C416S24100B

Reexamination Certificate

active

06652987

ABSTRACT:

BACKGROUND OF THE INVENTION
The present invention relates to an article having a coating for reducing radiation heat transfer, in particular a reflective ceramic coating, and to a method for forming the coated article.
The application of thermal barrier coatings to turbine components is an effective method for increasing the working temperature of the turbine section and for improving overall engine efficiency. Thermal barrier coatings reduce the substrate temperatures of cooled articles, thereby increasing component service life while maintaining a given efficiency. They also maximize the effectiveness and efficiency of compressor exit air used to cool turbine components. Although surface temperatures of a turbine component may be higher than 2000° F., the surface temperature of the overlying ceramic thermal barrier coating will be as much as 300° F. hotter or more.
A typical state-of-the-art zirconium oxide-based thermal barrier coating
10
applied by electron beam physical vapor deposition to a nickel-based alloy substrate
12
is illustrated in FIG.
1
. Prior to deposition of the coating, a metallic bond layer
14
is usually applied to the surface of the substrate. With electron beam physical vapor deposition processing, the oxide ceramic of the coating usually acquires a columnar morphology during growth. Yttrium, magnesium, calcium and/or other suitable oxide is typically added to the zirconium oxide to stabilize the tetragonal and/or cubic crystal structure required for coating durability.
The primary benefits of such zirconium oxide-based ceramic thermal barrier coatings are reduced metal temperatures and reduced cooling requirements. These benefits are derived from the inherently low thermal conductivity of the coating material. At higher-temperature, heat transport through a conventional ceramic thermal barrier coating occurs via conduction and radiation. Whereas the conduction of heat through these materials via phonon transport remains quite low over a wide range of temperature, the translucent nature of ceramic materials can allow for significant levels of heat transfer via radiation as the temperature increases. The heat transfer problems associated with thermal radiation are exacerbated in modern aircraft engines because of their high combustor pressures, which maximize the production of efficiently radiating carbon particulates, and their high peak combustion temperatures. Thermal radiation can contribute as much or even more to overall heat transfer than convective processes in these engines, particularly as temperatures increase.
Unlike metallic materials which are opaque, the translucent nature of oxide ceramics allows for direct heat transfer via radiation over certain wavelengths. The amount of heat transferred through the ceramic via radiation during service at high temperature depends upon the predominant wavelengths of the incident radiation, the optical properties, such as emissivity and absorption coefficient, of the coating material, and the coating thickness. The optical transmittance of a thermal barrier coating comprised of yttria-stabilized zirconia is such that 80% of incident radiation in the 1-3 &mgr;m wavelength range is transmitted through a 0.002″ coating. Since radiation emitted by the combustion gases, which contain water and carbon dioxide, will be concentrated in this wavelength range for the temperatures typically encountered during service, reducing radiation heat transport through the ceramic coating will enhance the insulating properties of the thermal barrier coating.
SUMMARY OF THE INVENTION
Accordingly, it is an object of the present invention to provide a method for forming a protective coating which reduces radiation heat transport.
It is a further object of the present invention to provide an article having a protective coating for reducing the radiative contribution to the overall heat transfer through a ceramic coating.
The foregoing objects are attained by the method and the article of the present invention.
In accordance with the present invention, a method for forming a protective coating which reduces radiation heat transport broadly comprises the steps of forming a ceramic coating on a substrate and embedding at least one reflective layer within the ceramic coating layer. In a preferred embodiment of the present invention, a plurality of reflective layers formed from a precious metal are embedded within the ceramic coating layer.
In accordance with the present invention, an article having a coating for reducing the radiative contribution to heat transfer through a thermal barrier coating is provided. The article broadly comprises a substrate, a ceramic coating formed on the substrate, and at least one layer of reflective material embedded within the ceramic coating to reduce radiation heat transport.
Other details of the method and the article of the present invention, as well as other objects and advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings, wherein like reference numerals depict like elements.


REFERENCES:
patent: 3031331 (1962-04-01), Aves et al.
patent: 3293064 (1966-12-01), Aves
patent: 3715265 (1973-02-01), Allen et al.
patent: 4471017 (1984-09-01), Poeschel et al.
patent: RE34173 (1993-02-01), Kerber
patent: 5350599 (1994-09-01), Rigney et al.
patent: 5512382 (1996-04-01), Strangman
Electro-Optical Industries, Material Emissivity Properties, 1997, (No month).

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