Abstract
The results of development and manufacture of a micro gas turbine engine for an unmanned aerial vehicle are presented. The calculation features of the main elements of the engine blading section, namely, a centrifugal compressor, a reverse-flow combustor, and a radial-axial turbine are considered. The design of the inlet and output duct, rotor bearings, and lubrication system is described.
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Russian Text © The Author(s), 2019, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2019, No. 4, pp. 115–123.
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Sychenkov, V.A., Limanskii, A.S., Yousef, W.M. et al. Micro Gas Turbine Engine for Unmanned Aerial Vehicles. Russ. Aeronaut. 62, 651–660 (2019). https://doi.org/10.3103/S1068799819040160
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DOI: https://doi.org/10.3103/S1068799819040160