ملخص
ABSTRACT Gas turbine engines deteriorate over time; their performance will change. Using GPA, the degraded component can be identified, after which corrective steps can be taken. In this thesis, GPA has been performed by using the GSP, which has modern capabilities to analyze the performance of the CF6-80C2 engine model. CF6-80C2 engine model was created by using GSP, based on test cell measurements data that have been taken from the references, and by adapting the model to the test cell data according to adapting procedures, and some assumptions made due to lack of information about the engine. The Take -off power setting has been chosen as a design point of the engine model. Offdesign performance simulation was built in GSP, based on generic components maps that have been scaled to match the measured CF6 -80C2 performance design point, describing the performance of the compressors and turbines of the engine model. The deterioration simulations assumptions on the CF6-80C2 engine model have been applied in GSP, by changing the corrected mass flow rate and isentropic efficiency of the engine components. Seven deterioration cases have been studied, which have been divided into two categories, the first one has studied single-component deterioration, and its effect on all engine components, and the other one has studied combined component deterioration. The results of the studied cases have been shown in bar chats, to present the percentage changes in the pressure and temperature of each engine station, N2 speeds, fuel flow, and thrust, and GSP charts to present the changes in the pressure ratios and temperature ratios with changes of corrected mass flow rate and isentropic efficiency of the engine components. EGT margin of the engine deteriorated cases have been studied and plotted. The results of the CF6-80C2 GSP engine model have been compared with a case study of the GPA exponential data of the test cell for CF6-80C2 from [2]. The comparison between the GSP model and GPA experimental data shows very good agreement, staying with +/- 0.39% as the maximum difference range for all measured engine parameters that are compared.