Derivation of Signatures for Faults in Gas Turbine Compressor Blading

Abstract A procedure for derivation of signatures for faults in blades of a gas turbine is presented. A variety of blade faults, corresponding to changes in angle or spacing of one or more blades are examined. A fluid dynamic simulation model is used to derive the unsteady pressure signals sensed by a stationary transducer for the cases of faulty blades. The blade fault signatures are derived by processing these signals using Fourier techniques. The features of blade fault signatures are studied. Finally, the possibilities they offer for discrimination and identification of different possible blade faults is also examined.