%T Determination of remaining useful life of gas turbine blade
%A M.A.M. Said
%A M.H. Osman
%A P.S.M.M. Yusoff
%A S.A. Sulaiman
%A S.M.A.S.A. Ghazali
%I EDP Sciences
%V 38
%O cited By 2; Conference of UTP-UMP Symposium on Energy Systems 2015, SES 2015 ; Conference Date: 7 October 2015; Conference Code:121434
%L scholars7250
%J MATEC Web of Conferences
%D 2016
%R 10.1051/matecconf/20163801011
%X The aim of this research is to determine the remaining usefttl life of gas turbine blade, using service-exposed turbine blades. This task is performed 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 8 50°C. The study will focus on the creep behaviour of the 52000 hours service-exposed blades, complemented with creep-rupture modelling using JMatPro software and microstructure examination using optical microscope. The test specimens, made up of Ni-based superalloy of the first stage turbine blades, are machined based on International Standard (ISO) 24. The results from the SRT will be analyzed using these two main equations Larson-Miller Parameter and Life Fraction Rule. Based on the results the remaining useflil life analysis, the 52000h service-exposed blade has the condition to opente in the range of another 4751 hr to 18362 hr. The microstructure examinations shows tmces of carbide precipitation that detenorate the grain boundanes that occurs during creep process. Creep-rupture life modelling using JMatPro software has shown good agreement with the accelerated creep rupture test with minimal enor. © Owned by the authors, published by EDP Sciences, 2016.
%K Carbides; Creep; Gas turbine locomotives; Gas turbines; Microstructure; Software testing; Turbine components, Carbide precipitation; First stage turbine blades; International standards; Larson-Miller parameter; Microstructure examination; Ni-based superalloys; Remaining useful lives; Stress rupture test, Turbomachine blades