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| Abstract No.: |
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Scheduled at:
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Thursday, May 22, 2014, Hall H1 9:20 AM
Aviation Industry 2
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| Title: |
Lanthanum and gadolinium zirconate thermal barrier coatings structure and properties evolution
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| Authors: |
Ivan Mazilin* / Technological Systems for Protective Coatings, Ltd., Russian Federation
Lev Baldaev/ TSPC Ltd., Russia
Dmitri Drobot/ Lomonosov Moscow University of Fine Chemical Technology, Russia
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| Abstract: |
Thermal barrier coatings (TBC) with ceramic topcoat are used to protect jet engine turbine blades and other parts against high temperatures, corrosion and erosion wear. State-of-the-art TBC topcoat material is the zirconium dioxide partially stabilized by 6-8% of yttrium oxide (7YSZ). The temperature limit for 7YSZ coatings was determined to be 1200ºC based on phase transitions and sintering properties. Further jet engine efficiency rising strongly depends on turbine inlet gas temperature (up to 2200 K at the moment). On that reason there is a need for a new thermal barrier coating material development.
Rare-earth zirconates (Ln2Zr2O7) with pyrochlore structure were found to be very promising materials. They possess high thermal stability up to the melting point (around 2300ºC), low thermal conductivity (1.5 W/m
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