Abstract
In this paper, a novel method for high temperature fatigue strength assessment of nickel superalloy turbine blades after operation at different times (303 and 473 h) was presented. The studies included destructive testing (fatigue testing at temperature 950 °C under cyclic bending load), non-destructive testing (Fluorescent Penetrant Inspection and Eddy Current method), and finite element modelling. High temperature fatigue tests were performed within load range from 5200 to 6600 N using a special self-designed blade grip attached to the conventional testing machine. The experimental results were compared with the finite element model generated from the ANSYS software. It was found that failure of turbine blades occurred in the area with the highest stress concertation, which was accurately predicted by the finite element (FE) model.
Highlights
The power and efficiency of an aircraft engine mainly depends on the inlet gas temperature
Ten turbine blades made of nickel superalloy operated during 303 h and 473 h (5 pieces each) provided by the aviation sector were subjected to mechanical and non-destructive testing
A fluorescent dye was applied to the surface of the object to detect structural defects that may affect the integrity or quality of the part in question
Summary
The power and efficiency of an aircraft engine mainly depends on the inlet gas temperature. It is desirable to increase the temperature of the flue gas to the combustion temperature of aviation fuel, which is about 2300 ◦ C. The limitations are the strength properties of the alloys from which the blades are made. Nickel super alloys are typically used in such conditions. Additional application of thermal barrier coatings (TBC) on nickel-based superalloys allows to increase the effective service temperature to 1300 ◦ C, while the temperature on the blade attachment does not exceed 300 ◦ C [1]. An aggressive environment is another factor that affects the durability of engine turbine blades
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