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.
Micro Gas Turbine Engine for Unmanned Aerial Vehicles
Russ. Aeronaut.
Russian Aeronautics ; 62 , 4 ; 651-660
2019-10-01
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch