Thermodynamic Analysis Of An Air Compressor Of Micro Turbojet Engines Used For Propulsion In UAVs

Mahmut Sami Büker

doi:10.56753/ASREL.2024.3.3

Mahmut Sami Büker, Ali Ismayilli

Year : 2024
Vol : 3
No : 1
Page : 27-43

DOI : 10.56753/ASREL.2024.3.3

In this study, computational fluid dynamics (CFD) and thermodynamic analyses of the radial compressor whell, one of the key components of the small-scale micro turbojet engine used for propulsion in UAV’s, were conducted. The micro turbojet engine was analyzed under sea level conditions (101.325 Pa, 288.15 K). The compressor models were designed with 12 full blades, and the blade thickness for the compressor models was set at 1.3 mm. CFD analyses were carried out at three different operating speeds, namely 45.500, 55.500 and 65.500 rpm, with the same mass flow rates (1 kg/s) and pressure ratios (4.8). The energy efficiencies of these models were determined, followed by traditional exergy analyses, resulting in exergy efficiencies of 79.25%, 86.02% and 81.70% respectively. In this study, computational fluid dynamics (CFD) and thermodynamic analyses of the radial compressor blade, one of the key components of the small-scale micro turbojet engine used for propulsion in UAV’s, were conducted. The micro turbojet engine was analyzed under sea level conditions (101.325 Pa, 288.15 K). The compressor models were designed with 12 full blades, and the blade thickness for the compressor models was set at 1.3 mm. CFD analyses were carried out at three different operating speeds, namely 45.500, 55.500 and 65.500 rpm, with the same mass flow rates (1 kg/s) and pressure ratios (4.8). The energy efficiencies of these models were determined as 94.29%, 94.44% and 94.68%, respectively. Then, traditional exergy analyses were found to be 79.25%, 86.02% and 81.70%, respectively. In this study, computational fluid dynamics (CFD) and thermodynamic analyses of the radial compressor blade, one of the key components of the small-scale micro turbojet engine used for propulsion in UAV’s, were conducted. The micro turbojet engine was analyzed under sea level conditions (101.325 Pa, 288.15 K). The compressor models were designed with 12 full blades, and the blade thickness for the compressor models was set at 1.3 mm. CFD analyses were carried out at three different operating speeds, namely 45.500, 55.500 and 65.500 rpm, with the same mass flow rates (1 kg/s) and pressure ratios (4.8). The energy efficiencies of these models were determined as 94.29%, 94.44% and 94.68%, respectively. Then, traditional exergy analyses were found to be 79.25%, 86.02% and 81.70%, respectively.

Cite this Article As : İsmayilli, A., & Büker, M. S. (2024). İHA’larda itki için kullanılan mikro turbojet motorun hava kompresörünün termodinamik analizi. Aerospace Research Letters (ASREL), 3(1), 27-43. https://doi.org/10.56753/ASREL.2024.3.3

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Thermodynamic Analysis Of An Air Compressor Of Micro Turbojet Engines Used For Propulsion In UAVs, Araştırma Makalesi,
2024, Vol. 3 (1)

Received : 22.03.2024, Accepted : 23.05.2024 , Published Online : 30.06.2024