Modeling of transient processes in gas-turbine compressors and turbines for engine fault

Abstract

Transient performance analysis is important and effective for on line fault diagnosis in

gas turbine engines. The present transient thermodynamic model for compressor and

turbine is developed for this purpose. The algebraic solution and numerical solution are

coupled for the different control volumes according to the different physical laws

governing these control volumes. A new concept of plenum whose volume incorporates

the space from the down stream of the row to the upstream of the next row is introduced. A variable time step is used to solve the equations. The compressor and the turbine are modeled by three sections, that is, the rotor, the stator with lumped parameters, and the polonium with non-uniform parameters. The loss can be predicted

either by experimental correlations and the geometry or by isentropic efficiency in the

current model.