Design of aircraft power unit

This diploma thesis deals with basic design and calculation of an aircraft power unit (APU). For desired shaft power the thermal cycle is calculated. Basic dimensions of compressor, turbine and exhaust system are calculated as well as thermodynamic parameters of air and hot gases along the motor. Corresponding compressor map, turbine map and characteristics of the exhaust system are designed. Based on these characteristics, an effective shaft power is being calculated in various off-design conditions. Dependency of the shaft power vs. altitude is also presented. All the calculations are made in MATLAB. Finally, simplified motor cross-section is created