Thermal barrier coatings: Burner rig hot corrosion test results | Zendy

Philip Hodge | Zendy; S. Stecura | Zendy; M. A. Gedwill | Zendy; I. Zaplatynsky | Zendy; Stanley R. Levine | Zendy

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Thermal barrier coatings: Burner rig hot corrosion test results

Author(s) -

Philip Hodge,

S. Stecura,

M. A. Gedwill,

I. Zaplatynsky,

Stanley R. Levine

Publication year - 1980

Publication title -

journal of materials for energy systems

Language(s) - English

Resource type - Journals

eISSN - 2168-8133

pISSN - 0162-9719

DOI - 10.1007/bf02833361

Subject(s) - thermal barrier coating , materials science , cermet , combustor , coating , corrosion , metallurgy , gas turbines , combustion , composite material , ceramic , mechanical engineering , chemistry , organic chemistry , engineering

A Mach 0.3 burner rig test program was conducted to examine the sensitivity of thermal barrier coatings to Na and V contaminated combustion gases simulating potential utility gas turbine environments. Coating life of the standard ZrO2-12Y2O3/Ni-16.2Cr5.6Al-0.6Y (composition in weight percent unless stated otherwise) NASA thermal barrier coating system which was developed for aircraft gas turbines was significantly reduced in such environments. Two thermal barrier coating systems, Ca2SiO4/Ni16.2Cr-5.6Al-0.6Y and ZrO2-8Y2O3/Ni-16.4Cr-5.1Al-0.15Y and a less insulative cermet coating system, 50 vol pct MgO-50 vol pct Ni-19.6Cr-17.1Al-0.97Y/Ni16.2Cr-5.6Al-0.6Y, were identified as having much improved corrosion resistance compared to the standard coating.

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