INVESTIGATION OF REMAINING USEFUL LIFE OF GAS TURBINE BLADE

The aim of this research is to investigate the remaining useful life of gas turbine blade. This investigation was done by predicting the turbine blades service life using Stress Rupture Test (SRT) under accelerated test conditions where the applied stresses to the specimen is between 400 MPa to 600 MPa and the test temperature is 850oC. The study will focus on the creep behaviour of the 52000 hours service-exposed blades. The test specimens - made up of Ni-based superalloy of the first stage turbine blades - are machined based on International Standard (ISO) 204. The results from the SRT will be further analyzed using these two main equations – Larson-Miller Parameter and Life Fraction Rule for remaining useful life analysis. Based on the results of the remaining useful life analysis, the 52000 hours service-exposed blade has the condition to operate until up to another 11911 hours