Micro Gas Turbine Engine for Unmanned Aerial Vehicles


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Resumo

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.

Sobre autores

V. Sychenkov

Tupolev Kazan National Research Technical University

Email: vladimir.ankudimov@inbox.ru
Rússia, ul. Karla Marksa 10, Kazan, 420111 Tatarstan

A. Limanskii

Tupolev Kazan National Research Technical University

Email: vladimir.ankudimov@inbox.ru
Rússia, ul. Karla Marksa 10, Kazan, 420111 Tatarstan

W. Yousef

Tupolev Kazan National Research Technical University

Email: vladimir.ankudimov@inbox.ru
Rússia, ul. Karla Marksa 10, Kazan, 420111 Tatarstan

V. Ankudimov

Tupolev Kazan National Research Technical University

Autor responsável pela correspondência
Email: vladimir.ankudimov@inbox.ru
Rússia, ul. Karla Marksa 10, Kazan, 420111 Tatarstan

S. Seyid Jafari

Tupolev Kazan National Research Technical University

Email: vladimir.ankudimov@inbox.ru
Rússia, ul. Karla Marksa 10, Kazan, 420111 Tatarstan

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