Abstract
When the aircraft turbine engine is working, gas turbine blades are exposed to mechanical or thermal loads. Their mutual operation, especially with significant variable values, substantially affects the blade reliability. The article presents the results of the tested turbine rotor blade with the deteriorated end face. The blade cooled internally with a multi-channel structure, was made from a nickel–cobalt alloy. As a result of the research, it was shown that the blade microstructure contains a significant amount of carbide precipitates in dendritic areas, especially in the upper blade section. It was stated that the directional coagulation of phase γ’, especially in the upper blade section, has started in the superalloy. It indicates a long-term exposure of this blade to high temperature. The process of γ’ phase directional coagulation to a significant extent is determined by the creep resistance of monocrystalline nickel superalloys under high temperature. The final effect of the research was to demonstrate that the wear of the end face was due to microstructure changes of its airfoil caused by high-temperature creep at uni-axial stress state, known as rafting.
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