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Effects of Reversed Shock Waves on Operation Mode in H 2 /O 2 Rotating Detonation Chambers

Author

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  • Yanliang Chen

    (Center for Combustion and Propulsion, CAPT and SKLTCS, Department of Mechanics and Engineering Science, College of Engineering, Peking University, Beijing 100871, China)

  • Xiangyang Liu

    (Center for Combustion and Propulsion, CAPT and SKLTCS, Department of Mechanics and Engineering Science, College of Engineering, Peking University, Beijing 100871, China)

  • Jianping Wang

    (Center for Combustion and Propulsion, CAPT and SKLTCS, Department of Mechanics and Engineering Science, College of Engineering, Peking University, Beijing 100871, China)

Abstract

Operation modes are an important topic in the research of Rotating Detonation Chamber (RDC) as it can affect the stability of RDC. However, they have not been discussed in detail due to the limitation of measurement means in experiments. The aim of this research is to investigate the mechanism of different operation modes by numerical simulation. In this paper, a numerical simulation for RDCs with separate injectors is carried out. Different operation modes and mode switching are analyzed. There is a series of reversed shock waves in the flow field. It was found that they have great effects on operation mode and mode switching in RDCs. A reversed shock wave can transit into a detonation wave after passing through isolated fresh gas region where fresh gas and burnt gas distribute alternatively. This shock-to-detonation transition (SDT) phenomenon will influence the ignition process, contra-rotating waves mode and mode switching in RDCs. SDT makes the number of detonation wave increases, resulting in multi-wave mode with one ignition. Moreover, quenching of detonation waves after collision and SDT after passing through isolated fresh gas region are the mechanism of contra-rotating waves mode in RDCs with separate injectors. In addition, when the inlet total temperature increases, a shock wave is easier to transit into a detonation wave. The distance that a shock wave travels before SDT decreases when temperature increases. This will result in mode switching. Therefore, SDT determines that there is a lower bound of detonation wave number.

Suggested Citation

  • Yanliang Chen & Xiangyang Liu & Jianping Wang, 2021. "Effects of Reversed Shock Waves on Operation Mode in H 2 /O 2 Rotating Detonation Chambers," Energies, MDPI, vol. 14(24), pages 1-14, December.
    • Handle: RePEc:gam:jeners:v:14:y:2021:i:24:p:8296-:d:698673
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    References listed on IDEAS

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    1. Armani Batista & Mathias C. Ross & Christopher Lietz & William A. Hargus, 2021. "Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine," Energies, MDPI, vol. 14(12), pages 1-22, June.
    2. Hyung-Seok Han & Eun Sung Lee & Jeong-Yeol Choi, 2021. "Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C 2 H 4 /O 2 Propellant," Energies, MDPI, vol. 14(5), pages 1-20, March.
    3. Jan Kindracki & Krzysztof Wacko & Przemysław Woźniak & Stanisław Siatkowski & Łukasz Mężyk, 2020. "Influence of Gaseous Hydrogen Addition on Initiation of Rotating Detonation in Liquid Fuel–Air Mixtures," Energies, MDPI, vol. 13(19), pages 1-16, September.
    4. John W. Bennewitz & Blaine R. Bigler & Mathias C. Ross & Stephen A. Danczyk & William A. Hargus & Richard D. Smith, 2021. "Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths," Energies, MDPI, vol. 14(8), pages 1-30, April.
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