Email this article Study of performance of the aircraft gas turbine engine integrated with a gas dynamic laser
- Authors: Osipov B.M.1, Kopelevich L.A.2, Perel’shtein B.K.2
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Affiliations:
- Kazan State Power Engineering University
- Tupolev Kazan National Research Technical University
- Issue: Vol 60, No 3 (2017)
- Pages: 474-477
- Section: Aircraft and Rocket Engine Theory
- URL: https://journal-vniispk.ru/1068-7998/article/view/230242
- DOI: https://doi.org/10.3103/S1068799817030230
- ID: 230242
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Abstract
We consider a turbofan engine (TFE), where the turbine rotor blades of the low pressure turbine (LPT) are micro-Laval nozzles. We demonstrated the possibility of integrating the super jet turbine and a jet nozzle as a single binary system for the purpose of generation of powerful coherence radiation. We estimated the efficiency of the binary high pressure emitting system being a TFE part.
About the authors
B. M. Osipov
Kazan State Power Engineering University
Author for correspondence.
Email: obm0099@yandex.ru
Russian Federation, ul. Krasnosel’skaya 51, Kazan, Tatarstan, 420066
L. A. Kopelevich
Tupolev Kazan National Research Technical University
Email: obm0099@yandex.ru
Russian Federation, ul. Karla Marksa 10, Kazan, Tatarstan, 420111
B. Kh. Perel’shtein
Tupolev Kazan National Research Technical University
Email: obm0099@yandex.ru
Russian Federation, ul. Karla Marksa 10, Kazan, Tatarstan, 420111
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