Mathematical analysis of basic turbofan engine parameters for different altitude levels

In this study, the compressor stage change of turbofan motors and the change of by- pass ratio of the motors are examined at different altitude values. The obtained data were analyzed with MathCAD computer program. As a result of the study, it was observed that the altitude increase, the change in the compressor stage of the engines and the by-pass ratio of the engines affected the performance of the engines. In this study, the compression ratio of the compressor (when the altitude is constant) affects the engine performance the most. It has been observed that performance increases with the compression ratio and the amount of air entering the engine increases significantly. This was followed by the engine's by-pass ratio and altitude change. As a result of the study, it was determined that CFM56-5B3 for mid range and Trent 890-17 engine for long range were superior in terms of performance among the examined engines. Keywords: Turbo fan aircraft engine, Altitude change analysis, Compressor analysis, Engine performance analysis