Performing thermodynamic analysis by simulating the general characteristics of the two-spool turbojet engine suitable for drone and UAV propulsion

This study presents determining performance parameters as well as thermodynamic analysis through certain design parameters of a two-spool turbojet engine for utilizing as propulsion equipment in drones and UAVs. The general characteristics of the two-spool turbojet engine and the thermodynamic analysis outcomes that are the subject of the study guide the engine designers, scientists and researchers interested in this subject to measure the available energy level depending on the entropy generation level of the energy conversion system and to determine the exergy destructions in the components defined as sub-systems. The outcomes show that while the thrust of the engine is computed to be 516 daN, the thrust-specific fuel consumption (TSFC) rate and air-fuel ratio corresponding to the 4398.499 kW-fuel energy consumption rate of the designed turbojet engine were determined as 19.706 g kN(-1) s(-1) and 82.604, respectively. When considering the thermodynamic analysis, performance cycle and general characteristics of a two-spool turbojet engine in accordance with the design requirements, the focus should be on the combustion chamber component to improve the first law and second law efficiency ratios. Any innovation in the burner of the two-spool turbojet engine over the course of the design stage may mitigate the exergy generation rate. In particular for designers and researchers, it would be advantageous to optimize parametric engine design metrics with respect to thermodynamic analysis and performance results.

Automated summary

This study focuses on determining performance parameters and conducting thermodynamic analysis of a two-spool turbojet engine designed for drones and UAVs. The outcomes suggest that optimizing the combustion chamber component can improve engine efficiency. Designers and researchers can use these results to optimize engine design metrics.