Abstract
Structural changes in alloys and coatings of turbine blades of aviation gas turbine engines during their operation under the influence of high temperature and stress are considered. It is shown that the cause of the appearance of thermal fatigue cracks in the coatings of turbine blades is the discrepancy of the acting stresses on the blade to the coating parameters: aluminum content, thickness, and its strength. A heat-resistant TP for turbine blades of GTE has been developed, consisting of layers, each of which has markedly different physical, thermal, and mechanical properties, creating an essentially complex coating structure.
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