Performance of a microjet using component map scaling

Purpose - This paper aims to investigate the cycle performance of a small size turbojet engine used in unmanned aerial vehicles at 0-5,000 m altitude and 0-0.8 Mach flight speeds with real component maps. Design/methodology/approach - The engine performance calculations were performed for both on-design and off-design conditions through an in-house code generated for simulating the performance of turbojet engines at different flight regimes. These calculations rely on input parameters in which fuel composition are obtained through laboratory elemental analysis. Findings Exemplarily, according to comparative results between in-house developed performance code and commercially available software, there is 0.25% of the difference in thrust value at on-design conditions. Practical implications - Once the on-design performance parameters and fluid properties were determined, the off-design operation calculations were performed based on the compressor and turbine maps and scaling methodology. This method enables predicting component maps and fitting them to real conditions. Originality/value A method to be used easily by researchers on turbojet engine performance calculations which best fits to real conditions.

Automated summary

This paper investigates the cycle performance of a small size turbojet engine used in unmanned aerial vehicles at different altitudes and flight speeds, and develops a performance calculation code suitable for different flight regimes. The results show that this method can accurately predict the engine performance under real conditions.