Aircraft engines are exposed to degradation due to factors such as environment air pollution, fuel content, and ageing or degradation of engine’s components experienced within specified time. As turbofan operates, the engine components deteriorate and consequently affect the engine performance. Rotating components such as compressor and turbine are the most vulnerable components to the degradation and deterioration. Therefore this study is designed to investigate computationally the effect of components degradation on engine performance. A two-spool high bypass turbofan engine operated at cruise condition is selected for the evaluation. The reason two-spool high bypass turbofan is selected due to the availability of specifications of two-spool turbofan, GE-90 in the reference. The difference between one-spool and two-spool turbofan is the number of shaft rotating in the gas turbine. The one-spool turbofan only have one shaft connecting turbine and compressor. While, two-spool turbofan have two independent shaft with each one of the shaft connecting compressor and turbine. One shaft connect Low Pressure Turbine (LPT) to Low Pressure Compressor (LPC), while the other shaft connect the High Pressure Turbine (HPT) to High Pressure Compressor (HPC). The simulation was performed using Gas Turbine Simulation Program (GSP) software. The affected components considered are turbines and compressors with deterioration rate ranging from 0 % to 5 % are used. The effect of selected deterioration rate on global parameters such as engine thrust and thrust specific fuel consumption (TSFC) will be studied.
Studies on a two-spool hiigh bypass turbofan engine’s component deterioration effects on engine performance_ Awang Raisudin Awang Saifudin_A2_2014_NI