ContactISSN:e-ISSN: 2980-0064
Author Sign-inReviewer Sign-inRegister
TürkçeEnglish
HomeAim and ScopeABOUTGUIDE FOR AUTHORSSend ArticleLatest IssueArchiveContact Us

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

Ali Ismayilli,Mahmut Sami Büker

  • Ali Ismayilli: Necmettin Erbakan UNİVERSİTESİ
  • Mahmut Sami Büker: Necmettin Erbakan University
  •  Year : 2024
  •  Vol : 3
  •  Issue : 1
  •  Page : 27-43
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

Conflict of interest : The authors declare that they have no conflict of interest.

This article is published under the CC BY-NC 4.0 license.
Asrel Aerospace Research Letters
2024, Vol3, Issue1
E-ISSN: 2980-0064
Received : , Accepted : , Published Online :

References

  1. Balli, O., Dalkıran, A., & Karakoç, T. H. (2021). Energetic, exergetic, exergoeconomic, environmental (4E) and sustainability performances of an unmanned aerial vehicle micro turbojet engine. Aircraft Engineering and Aerospace Technology, 93(7), 1254-1275.
  2. Cengel, Y. A., Boles, M. A., & Kanoğlu, M. 2011, Thermodynamics: an engineering approach (Vol. 5, p. 445). New York: McGraw-hill.
  3. Chaudhary, A., Trivedi, Y., Mulchand, A., Chauhan, H., Dave, P., Patel, J., & Mehta, V. 2018, Design and CFD analysis of centrifugal compressor and turbine for supercritical CO2 power cycle. In The 6th International Symposium-Supercritical CO2 Power Cycles.
  4. Dağ, T., Ünler, T., & Uyaner, M., (2023). Elektrikli İnsansız Hava Aracının Maksimum Menzil Hesabı. Aerospace Research Letters (ASREL) Dergisi, 2(1), 10-18.
  5. Daşik, E., 2020, İHA’lar için kullanılacak olan bir turbojet motorun termodinamik çevrim analizi. Yüksek Lisans Tezi, Milli Savunma Üniversitesi, Hezarfen Havacılık ve Uzay Teknolojileri Enstitüsü, İstanbul.
  6. Guo, S., Duan, F., Tang, H., Lim, S. C., & Yip, M. S. (2014). Multi-objective optimization for centrifugal compressor of mini turbojet engine. Aerospace Science and Technology, 39, 414-425.
  7. İçke, R. Ö., 2016, Bir mikro turbojet motorun ters mühendislik ile incelenmesi, Yüksek Lisans Tezi, Dokuz Eylül Üniversitesi, İzmir.
  8. Karaşıray, N. C., 2009, Türk savunma sanayii’nde İHA’ların uçuşa elverişliliği ve tip sertifikasyonu gerekliliğinin incelenmesi, Yüksek lisans tezi, Kara Harp Okulu Komutanlığı, Ankara.
  9. KOCAMER, A., UZUN, M., & ÇOBAN, S. Static Analysis and Design of Fixed-Wing Tactical Unmanned Aerial Vehicle (TUAV) Retractable Main Landing Gear. ASREL, 125.
  10. Kurt, K., 2021, Radial Compressor Analysis Using CFD for a Micro-Jet, Yüksek Lisans Tezi, İstanbul Teknik Üniversitesi, İstanbul.
  11. Liu, S., Liu, C., Hu, Y., Gao, S., Wang, Y., & Zhang, H., 2016, Fatigue life assessment of centrifugal compressor impeller based on FEA, Engineering Failure Analysis, 60, 383–390. https://doi.org/10.1016/j.engfailanal.2015.11.035.
  12. Yücer, C. T., 2016, Thermodynamic analysis of the part load performance for a small scale gas turbine jet engine by using exergy analysis method, Energy, 111, 251-259.
  13. Zengin, Y., & Tokgöz, S. Tahliye Havasının Turbojet Performansına Etkisi. ASREL, 37.