Study of performance of the aircraft gas turbine engine integrated with a gas dynamic laser


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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.

Sobre autores

B. Osipov

Kazan State Power Engineering University

Autor responsável pela correspondência
Email: obm0099@yandex.ru
Rússia, ul. Krasnosel’skaya 51, Kazan, Tatarstan, 420066

L. Kopelevich

Tupolev Kazan National Research Technical University

Email: obm0099@yandex.ru
Rússia, ul. Karla Marksa 10, Kazan, Tatarstan, 420111

B. Perel’shtein

Tupolev Kazan National Research Technical University

Email: obm0099@yandex.ru
Rússia, ul. Karla Marksa 10, Kazan, Tatarstan, 420111

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