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- Article name
- Perspective materials for thermal barrier coatings of aviation gas turbine engines components (Review)
- Authors
- POROZOVA S. E., , sw.porozova@yandex.ru, Perm National Research Polytechnic University, Perm, Russia
SMYSHLYAEVA T. V., , smyshlyaeva-tv@avid.ru, JSC "UEC-Aviadvigatel", Perm, Russia
MAKSIMOV D. A., , Maksimov-DA@pmz.ru, JSC "UEC-Perm Engines", Perm, Russia
- Keywords
- thermal barrier coatings / oxide / rare earth elements / zirconates / thermal cycling / aviation gas turbine engines
- Year
- 2020 Issue 1 Pages 26 - 36
- Code EDN
- Code DOI
- Abstract
- A review of recent developments in thermal barrier coatings (TBC) for the protection of blades and other parts of aviation gas turbine engines was carried out. It has been shown that a general trend in the design of new TBC is the use of double-layer or gradient ceramic systems based on rare earth oxides. The lower layer in the case of multilayer coatings is usually zirconium dioxide, partially stabilized Y2O3. The main criterion for the applicability of coatings is the results of thermocyclic tests. Coatings with lanthanum zirconate, hafnium zirconate and lanthanum hexaaluminate have better characteristics among those considered.
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