The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure

In the current global economic conditions, airlines need to curtail financial expenses. It is known that share of airline costs for maintenance and repair (MR) in total cost structure amounts at least 20%, which more than 40% aircraft engines (AE). According actual expertise, this item expenditure will continue grow due inevitable sophistication AE structures, specified by increase efficiency ecological compatibility. One possible ways curbing expenses transit operation on-condition components are currently until overhaul life exhausted. For example, turbine blades gas (GTE) can be pertinent such elements. a common fact operate challenging environment: they affected excessive temperatures, severe centrifugal loads, aggressive media, their destruction generally occurs because accumulation fatigue damage creep. The alloy microstructure significantly degrades deforms before macroscopic develops. early detection microscopic tool allows transition GTE oncondition operation. article presents method calculating minimum creep rate Inconel 738LC based on microstructural changes under operating conditions. obtained results proposed used residual parameter.