Estimation of an optimum thickness of high-temperature coatings beam structures on working blade of turbines taking into account action of centrifugal loads

Aerospace propulsion engineering


Аuthors

Bichkov N. G., Klimov D. A., Miktibekov B. , Nizovtsev V. .*

Central Institute of Aviation Motors, CIAM, 2, Aviamotornaya St., Moscow, 111116, Russia

*e-mail: 3991258@mail.ru

Abstract

Thermal barrier coating (TBC) ceramic top-coats made from Y2O3-stabilized ZrO2 (YSZ) have been used successfully in gas-turbine engine applications for more than 30 years. YSZ derives its favorable performance from a combination of properties that include low thermal conductivity, high thermal expansion coefficient, and phase stability to relatively high temperatures. With advanced engine requirements of improved performance and increased durability, a new generation of thermal barrier coatings is needed that will provide greater insulation (lower thermal conductivity) and permit higher operating temperatures.

Keywords:

thermal barrier coating (TBC); vacuum-plasma coating; electron-beam deposition; oxide ceramic; columnar structure.


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