Calculations were carried out with application of current numerical methods and with the use of scientific-technical developments of a gas-dynamical resonator-thrust amplifier. The possibility of creating an exit device with a resonator for a small-size gas-turbine engine that in flight provides for thrust uprating by no less than 6% via gas mass attachment in the pulsating process is shown. In this way the size–mass characteristics of the exit device are preserved in the process.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
V. A. Levin, G. D. Smekhov, and A. I. Tarasov, Computational-Experimental Investigation of the Model of a Pulsating Detonation Engine, Preprint No. 42-98, Institute of Mechanics of the Moscow State University, Moscow (1998).
A. I. Tarasov and V. A. Shchipakov, Problems of creation of a gas-turbine pulsating detonation engine, Aviats.-Kosm. Tekh. Tekhnol., No. 9 (96), 40–43 (2012).
V. I. Bogdanov and D. S. Khantalin, Some aspects of calculation of a spherical gas-dynamical resonator-pulse amplifier of reactive thrust, Vestn. Rybinsk. Gos. Aviats. Tekh. Univ. im. P. A. Solov′eva, No. 3, 42–47 (2014).
Author information
Authors and Affiliations
Corresponding author
Additional information
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 90, No. 1, pp. 186–190, January–February, 2017.
Rights and permissions
About this article
Cite this article
Bogdanov, V.I., Khantalin, D.S. Uprating the Frontal Thrust of a Spherical Gas-Dynamical Resonator-Pulse Amplifier. J Eng Phys Thermophy 90, 176–180 (2017). https://doi.org/10.1007/s10891-017-1553-6
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s10891-017-1553-6