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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Smith, Jeffrey Scheibel, John Classen, Daniel Paschke, Scott Elbel, Shane Fick, Kirk Carlson, Doug |
| Copyright Year | 2014 |
| Abstract | As gas turbine (GT) temperatures have increased, thermal barrier coatings (TBCs) have become a critically important element in hot section component durability. Ceramic thermal barrier coatings permit significantly increased gas temperatures, reduced cooling requirements, and improve engine fuel efficiency and reliability. TBCs are in use throughout the GT hot section with turbine blades, vanes, and combustion hardware, now being designed with TBCs or upgraded with TBCs during component refurbishment1, 2. While the industry standard 6–9 Wt. % Yttria Stabilized Zirconia (7YSZ) has been the preferred ceramic composition for the past 30+ years, efforts have been underway to develop improved TBCs3, 4. The principal development goals have been to lower thermal conductivity, increase the sintering resistance and have a more stable crystalline phase structure allowing use above 1200° C (2192° F)5, 6. NASA has developed a series of advanced low conductivity, phase stable and sinter resistant TBC coatings utilizing multiple rare earth dopant oxides7. One of the coating systems NASA developed is based on Ytterbia, Gadolinia and Yttria additions to ZrO2 (YbGd-YSZ). This advanced low conductivity (low k) TBC is designed specifically for combustion hardware applications. In addition to lower thermal conductivity than 7YSZ, it has demonstrated thermal stability and sintering resistance to 1650° C (3000° F). The Electric Power Research Institute (EPRI) and Cincinnati Thermal Spray (CTS) have teamed together in a joint program to commercialize the YbGd-YSZ TBC coating system for GT combustion hardware. The program consists of validation of coating properties, establishment of production coating specifications and demonstration of coating performance through component engine testing of the YbGd-YSZ TBC coating system. Among the critical to quality coating characteristics that have been established are a) coating microstructure b) TBC tensile bond strength c) erosion resistance d) thermal conductivity and sintering resistance and e) thermal cycle performance. This paper will discuss the coating property validation results comparing the YbGd-YSZ TBC to baseline production combustor coatings and the status of coating commercialization efforts currently underway. |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791845752 |
| DOI | 10.1115/GT2014-26359 |
| Volume Number | Volume 6: Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy |
| Conference Proceedings | ASME Turbo Expo 2014: Turbine Technical Conference and Exposition |
| Language | English |
| Publisher Date | 2014-06-16 |
| Publisher Place | Düsseldorf, Germany |
| Access Restriction | Subscribed |
| Subject Keyword | Industrial gases Cycles Temperature Nasa Sprays Bond strength Combustion Coatings Engines Electricity (physics) Thermal stability Fuel efficiency Gas turbines Engineering standards Thermal conductivity Hardware Turbines Testing Erosion Cooling Turbine blades Sinter (metallurgy) Durability Ceramics Sintering Thermal barrier coatings Combustion chambers Reliability |
| Content Type | Text |
| Resource Type | Article |
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