Email this article Micro Gas Turbine Engine for Unmanned Aerial Vehicles
- Authors: Sychenkov V.A.1, Limanskii A.S.1, Yousef W.M.1, Ankudimov V.V.1, Seyid Jafari S.S.1
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Affiliations:
- Tupolev Kazan National Research Technical University
- Issue: Vol 62, No 4 (2019)
- Pages: 651-660
- Section: Aircraft and Rocket Engine Design and Development
- URL: https://journal-vniispk.ru/1068-7998/article/view/231176
- DOI: https://doi.org/10.3103/S1068799819040160
- ID: 231176
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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.
About the authors
V. A. Sychenkov
Tupolev Kazan National Research Technical University
Email: vladimir.ankudimov@inbox.ru
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
A. S. Limanskii
Tupolev Kazan National Research Technical University
Email: vladimir.ankudimov@inbox.ru
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
W. M. Yousef
Tupolev Kazan National Research Technical University
Email: vladimir.ankudimov@inbox.ru
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
V. V. Ankudimov
Tupolev Kazan National Research Technical University
Author for correspondence.
Email: vladimir.ankudimov@inbox.ru
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
S. S. Seyid Jafari
Tupolev Kazan National Research Technical University
Email: vladimir.ankudimov@inbox.ru
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
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