Metal treatment – Process of modifying or maintaining internal physical... – Processes of coating utilizing a reactive composition which...
Reexamination Certificate
2001-08-31
2003-05-20
Sheehan, John (Department: 1742)
Metal treatment
Process of modifying or maintaining internal physical...
Processes of coating utilizing a reactive composition which...
C198S457040, C427S248100, C427S250000, C427S255320, C428S623000, C428S469000, C428S472200
Reexamination Certificate
active
06565672
ABSTRACT:
This invention relates to protective systems such as used to protect some components of gas turbine engines and, more particularly, to the treatment of the protective-coating surface.
BACKGROUND OF THE INVENTION
Higher operating temperatures for gas turbine engines are continuously sought in order to increase their efficiency. However, as operating temperatures increase, the high temperature durability of the components of the engine must correspondingly increase. Significant advances in high-temperature capabilities have been achieved through the formulation of nickel- and cobalt-base superalloys. Nonetheless, when used to form components of the turbine, combustor and augmentor sections of a gas turbine engine, such alloys alone are often susceptible to damage by oxidation and hot corrosion attack and may not retain adequate mechanical properties. For this reason, these components are often protected by an environmental and/or thermal-insulating coating, the latter of which is termed a thermal barrier coating (TBC) system. Ceramic materials and particularly yttria-stabilized zirconia (YSZ) are widely used as a thermal barrier coating (TBC), or topcoat, of TBC systems used on gas turbine engine components. The TBC employed in the highest-temperature regions of gas turbine engines is typically deposited by electron beam physical vapor deposition (EBPVD) techniques that yield a columnar grain structure that is able to expand and contract without causing damaging stresses that lead to spallation.
To be effective, TBC systems must have low thermal conductivity, strongly adhere to the article, and remain adherent throughout many heating and cooling cycles. The latter requirement is particularly demanding due to the different coefficients of thermal expansion between ceramic topcoat materials and the superalloy substrates they protect. To promote adhesion and extend the service life of a TBC system, an oxidation-resistant bond coat is usually employed. Bond coats are typically in the form of overlay coatings such as MCrAlX (where M is iron, cobalt, and/or nickel, and X is yttrium or another rare earth element), or diffusion aluminide coatings. A notable example of a diffusion aluminide bond coat contains platinum aluminide (NiPtAl) intermetallic. When a bond coat is applied, a zone of interdiffusion, termed a diffusion zone, forms between the substrate and the bond coat. The diffusion zone beneath an overlay bond coat is typically much thinner than the diffusion zone beneath a diffusion bond coat.
During the deposition of the ceramic TBC and subsequent exposures to high temperatures, such as during engine service, bond coats of the type described above oxidize to form a tightly adherent alumina (aluminum oxide or Al
2
O
3
) layer or scale that protects the underlying structure from catastrophic oxidation and also adheres the TBC to the bond coat. The service life of a TBC system is typically limited by spallation at or near the interfaces of the alumina scale with the bond coat or with the TBC. The spallation is induced by thermal fatigue as the article substrate and the thermal barrier coating system are repeatedly heated and cooled during engine service.
There is a need for an understanding of the specific mechanisms that lead to the thermal fatigue failure of the protective system, and for structures that extend the life of the coating before the incidence of such failure. The present invention fulfills this need, and further provides related advantages.
BRIEF SUMMARY OF THE INVENTION
The present invention provides an approach for fabricating an article protected by a protective system, and articles protected by the protective system. The life of the protective system is extended under conditions of thermal fatigue by delaying the onset of the protective coating/alumina scale convolution failure mode and also by slowing the growth of the alumina scale and by delaying the onset of the alumina-scale interface failure mode. The present approach is applicable to environmental-coating protective systems where there is no thermal barrier coating present. However, it realizes its greatest advantages when used in thermal barrier coating systems where the protective coating is a bond coat and a ceramic thermal barrier coating overlies the bond coat.
A method of fabricating an article protected by a protective coating system comprises the steps of providing an article substrate having a substrate surface, and thereafter producing a protective coating having a flattened, pre-oxidized protective-coating surface on the substrate surface. The step of producing the protective coating includes the steps of depositing a protective coating on the substrate surface, the protective coating having a protective-coating surface, processing the protective coating to achieve a flattened protective-coating surface, and controllably oxidizing the protective-coating surface. Optionally but preferably, a thermal barrier coating is deposited overlying the flattened, pre-oxidized protective-coating surface.
The article substrate preferably is a nickel-base superalloy, and most preferably is a component of a gas turbine engine. The bond coat may be a diffusion aluminide bond coat such as a platinum aluminide bond coat, or it may be an overlay bond coat.
The step of processing the protective coating includes the step of flattening the protective-coating surface. The protective coating is flattened substantially without removing metal from the protective-coating surface, as by peening the protective coating. Desirably, the step of processing the protective coating produces a protective-coating surface wherein an average grain boundary displacement height of the protective coating is less than about 3 micrometers, more preferably less than about 1 micrometer, and most preferably less than about 0.5 micrometer, over at least about 40 percent of the grain boundaries of the protective coating but more preferably over all of the grain boundaries of the protective coating. In most cases, the step of processing the protective coating is performed after the step of depositing the protective coating is complete. In some cases, however, the steps of depositing the protective coating and processing the protective coating are performed concurrently. Additionally, it is preferred that at least about 40 percent, and more preferably all, of the surface of the protective coating is flattened to have a grain displacement height of less than about 3 micrometers, more preferably less than about 1 micrometer, and even more preferably less than about 0.5 micrometer. The step of processing may optionally include roughening and cleaning the protective-coating surface prior to flattening.
The step of controllably oxidizing the protective coating preferably includes the step of heating the protective coating in an atmosphere having a partial pressure of oxygen of from about 10
−5
mbar to about 10
3
mbar, more preferably from about 10
−5
mbar to about 10
−2
mbar, at an oxidizing temperature of from about 1800° F. to about 2100° F., and for a time of from about ½ hour to about 3 hours. The controllable oxidation is preferably performed by heating the protective coating to a pre-oxidation temperature of from about 2000° F. to about 2100° F. in a heating time of no more than about 45 minutes (preferably from about 1 to about 45 minutes, and more preferably from about 15 to about 35 minutes), and thereafter holding at the preoxidation temperature for a time of from about ½ hour to about 3 hours, in an atmosphere having a partial pressure of oxygen of about 10
−4
mbar.
The present approach addresses two major mechanisms of thermal fatigue failure in thermal barrier coating systems. The flattening of the protective-coating surface reduces the tendency of the protective coating to form the convolutions that lead to spalling of the alumina that forms on the protective-coating surface. The controlled oxidation of the protective-coating surface improves the bond strength between the protective coating and
Darolia Ramgopal
Spitsberg Irene
Carmen Santa Maria McNees Wallace & Nurick LLC
Garmong Gregory
General Electric Company
Oltmans Andrew L.
Sheehan John
LandOfFree
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