Study on life of turbine guide vane based on gas temperature load spectrum

To address the issue that the actual service load spectrum of aircraft engines recorded during flight is excessively long and thus difficult to be directly used for calculating the thermal fatigue life of turbine blades, this study takes the measured load data of aircraft engine exhaust temperature as the research object to predict the thermal fatigue life of turbine blades. By performing cycle processing and statistical analysis on the measured load spectrum, combined with material property parameters, the fatigue damage and equivalent life of turbine blades are evaluated. The calculated life results can provide data support and convenience for subsequent fatigue life calculations and tests. This paper establishes an accurate and efficient load spectrum processing flow. The research results show that the proposed load spectrum processing method can effectively improve the accuracy and applicability of the load spectrum, and provide reliable data support for the thermal fatigue life evaluation of aircraft engine turbine blades.