Proceedings of the Advances in Materials, Machinery, Electrical Engineering (AMMEE 2017)

Numerical Study of Non-Equilibrium Plasma Assisted Combustion on Spacecraft Rocket Engine

Authors
Zheng Zhang, Xueke Che, Jinlong Li, Wansheng Nie, Zhi Zheng, Siyin Zhou
Corresponding Author
Zheng Zhang
Available Online June 2017.
DOI
https://doi.org/10.2991/ammee-17.2017.117How to use a DOI?
Keywords
non-equilibrium plasma, plasma-assisted combustion, rocket engine, numerical simulation.
Abstract
The non-equilibrium plasma has unique advantages in ignition and combustion. In this paper, the plasma-assisted combustion scheme of the spacecraft rocket engine is designed. The numerical simulation method is used to study the influence of non - equilibrium plasma on the combustion in GH2/GO2 single co-axial injector rocket engine. Mainly to consider the plasma chemical kinetics, the discharge generated O, H and OH are added to the flow field as source term. The simulation results show that the temperature in the axial area increases with the increase of the chemical reaction rate in the combustion chamber, and the mixing effect of hydrogen and oxygen can be improved.
Open Access
This is an open access article distributed under the CC BY-NC license.

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Proceedings
Advances in Materials, Machinery, Electrical Engineering (AMMEE 2017)
Part of series
Advances in Engineering Research
Publication Date
June 2017
ISBN
978-94-6252-350-0
DOI
https://doi.org/10.2991/ammee-17.2017.117How to use a DOI?
Open Access
This is an open access article distributed under the CC BY-NC license.

Cite this article

TY  - CONF
AU  - Zheng Zhang
AU  - Xueke Che
AU  - Jinlong Li
AU  - Wansheng Nie
AU  - Zhi Zheng
AU  - Siyin Zhou
PY  - 2017/06
DA  - 2017/06
TI  - Numerical Study of Non-Equilibrium Plasma Assisted Combustion on Spacecraft Rocket Engine
BT  - Advances in Materials, Machinery, Electrical Engineering (AMMEE 2017)
PB  - Atlantis Press
UR  - https://doi.org/10.2991/ammee-17.2017.117
DO  - https://doi.org/10.2991/ammee-17.2017.117
ID  - Zhang2017/06
ER  -