HEAT-PROTECTIVE COATINGS FOR TURBINE BLADES OF AIRCRAFT GAS TURBINE ENGINES
doi: 10.25712/ASTU.2072-8921.2021.01.023
Keywords:
gas turbine engine, heat-resistant alloy, turbine blade, oxidation, chromoalitration, mixture, coating, microstructure, thermal fatigue cracks, thermal barrier layer, binder coating, residual stresses, temperature coefficient of linear expansion, durability, residual stressesAbstract
Heat-resistant nickel-based alloys, heat-resistant and heat-protective coatings are studied. The relevance of the research is to protect heat-resistant alloys from oxidation during high-temperature gas corrosion by applying heat-resistant heat-protective coatings. The microstructure of plasma and diffusion coatings of turbine blades and their changes during the operation of a gas turbine engine are examined. Studies of the multilayer heat-protective coating of turbine blades of aircraft gas turbine engines are carried out and the requirements for the composition, structure, and durability of its components – alloy, thermal barrier layer, binder coating, thermally grown oxide, and ceramic surface coating-are justified. As a result of the tests, the characteristics of the developed coating, their advantages in relation to the serial coatings of the turbine blades of the gas turbine engine were confirmed.
Downloads
Published
How to Cite
Issue
Section
License
Copyright (c) 2021 Vladimir P. Pankov, Alexander L. Babayan, Maxim V. Kulikov, Vladimir A. Kossoy, Boris S. Varlamov
This work is licensed under a Creative Commons Attribution 4.0 International License.
.
This work is licensed under a 
