It is necessary to understand the mechanisms that have enabled improvements of performance parameters such as thermodynamics efficiencies, thrust or power, specific fuel consumption and specific power in aero engines, thus reducing environmental impact. In this study, a thermodynamic analysis of a turboprop engine is performed at full and partial load conditions. The maximum overall and exergy efficiencies of the turboprop are found to be 30.7 and 29.2%, respectively. The minimum specific fuel consumption and maximum shaft power are found to be 0.2704 kg (kWh)(-1) and 1948 shp at maximum load, respectively. More important, the optimum functional load conditions of the engine are observed at higher loads. The results from this study are expected to assist propeller aero-engine design work, where the first and second laws provide a more comprehensive assessment of performance, allowing the turboprop engine concept to be better tailored to specific types of regional transport aircraft.