Barrier Coatings for Turbine and Compressor Blades of Powerful Gas Turbine Engines
Abstracts of the 5th International Conference on Surfaces, Coatings and Nanostructured Materials (NANOSMAT 5) 2010
Aleksandrs Urbahs, Konstantins Savkovs, Margarita Urbaha

Presently compressor pressure ratio of powerful gas turbine engines has reached 35…40 with a tendency of further growth. In this case, the operating air temperatures in compressor’s tail stages are 500 0С and above. At such temperatures the main cause of blade destruction is gas corrosion and erosion due to interaction between dusted high-temperature air flow and blade surfaces. It requires new technological solutions providing safe operation of aircrafts. One of the solutions to this problem is creation of heat- and erosion-resistant coatings that are able to resist high-temperature air stream.


Atslēgas vārdi
barrier coatings, turbine and compressor blades

Urbahs, A., Savkovs, K., Urbaha, M. Barrier Coatings for Turbine and Compressor Blades of Powerful Gas Turbine Engines. No: Abstracts of the 5th International Conference on Surfaces, Coatings and Nanostructured Materials (NANOSMAT 5), Francija, Reims, 19.-21. oktobris, 2010. Reims: Nanosmat, 2010, 117.-117.lpp.

Publikācijas valoda
English (en)
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