Experimental study of protective coatings for turbine blades of a gas turbine engine with respect to isothermal heat resistance

Thermal protective coatings are used to protect the blades of gas turbines and are designed to extend their service life or increase the temperature of the gas in front of the turbine, and, consequently, efficiency. As a rule, a heat-protective coating consists of several layers, during operation, the structure and composition of which change due to the processes occurring in them, namely, oxidation of the metal layer and diffusion of its elements into the alloy, as well as sintering of the ceramic layer. As a result, the properties of each layer change. These changes, combined with applied external loads, can lead to cracks at the interface between the binder coating and the ceramic, and the ceramic layer may eventually break off. In addition to this internal degradation, interaction with the environment can accelerate the destruction of the coating. This article discusses the phenomena that occur in heat-protective coatings at high temperatures, and describes the mechanisms of their destruction with illustrations, the results of laboratory tests and the choice of a heat-protective coating option. The issues of durability of thermal protective coatings and technical approaches to their improvement are considered.

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