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Simulation of continuous spin detonation in an annular combustion chamber in two-dimensional statement

Simulation of continuous spin detonation in an annular combustion chamber in two-dimensional... The article presents the results of a numerical simulation of the phenomenon of continuous spin detonation in a hydrogen-oxygen mixture in two-dimensional non-stationary formulation using periodic boundary conditions. The software implementation of the mathematical model is made in the Ansys Fluent software package. A methodology for adjusting the software package and an algorithm for initiating the detonation process for numerical simulation are presented. The method was verified by calculating and comparing with experimental data the propagation velocity of a plane detonation wave with various diluents. Using the developed modeling technique, the specific impulses and the velocities of continuous spin detonation were determined for fuel excess ratios in the range from 0.56 to 2.4. The simulation results showed good agreement with the results obtained by other authors. Also, the performed numerical simulation has shown that, on the average, the specific impulse of the combustion chamber of a detonation rocket engine is greater than the specific impulse of a liquid-propellant rocket engine by 17 %. It is shown that the use of the continuous spin detonation process can significantly reduce the length of the cylindrical part of the combustion chamber and the gas generator of the liquid engine. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Simulation of continuous spin detonation in an annular combustion chamber in two-dimensional statement

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Publisher
Springer Journals
Copyright
Copyright © I.N. Borovik, I.R. Farizanov, and L.S. Yanovskii 2022
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/s0869864322010103
Publisher site
See Article on Publisher Site

Abstract

The article presents the results of a numerical simulation of the phenomenon of continuous spin detonation in a hydrogen-oxygen mixture in two-dimensional non-stationary formulation using periodic boundary conditions. The software implementation of the mathematical model is made in the Ansys Fluent software package. A methodology for adjusting the software package and an algorithm for initiating the detonation process for numerical simulation are presented. The method was verified by calculating and comparing with experimental data the propagation velocity of a plane detonation wave with various diluents. Using the developed modeling technique, the specific impulses and the velocities of continuous spin detonation were determined for fuel excess ratios in the range from 0.56 to 2.4. The simulation results showed good agreement with the results obtained by other authors. Also, the performed numerical simulation has shown that, on the average, the specific impulse of the combustion chamber of a detonation rocket engine is greater than the specific impulse of a liquid-propellant rocket engine by 17 %. It is shown that the use of the continuous spin detonation process can significantly reduce the length of the cylindrical part of the combustion chamber and the gas generator of the liquid engine.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Jan 1, 2022

Keywords: continuous spin detonation; numerical simulation; detonation engine

References