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Symbiosis of deflagration and detonation in one jet system – A hybrid detonation engine

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  • Assad, Mohamad
  • Penyzkov, Oleq
  • Chernukho, Ivan

Abstract

For the first time, a model of a hybrid detonation engine has been developed and experimentally tested. It consists of two autonomous (independent of each other) jet plants: a rotating detonation module (RDM) and a well-known turbojet engine. The features of the RDM operation and the conditions for the existence of a detonation mode when using mixtures: jet fuel-oxygen and jet fuel-oxygen-air are studied. It has been established that the detonation mode in the jet fuel-oxygen mixture occurs soon after the start of the RDM (approximately after 3–5 ms), but the detonation wave velocities are relatively low. Further, the detonation mode is enhanced, and the detonation waves are accelerated to sufficiently high velocities – 2000 m/s or more. The air supply to the RDM contributes to the intensification of the detonation mode. In this case, the wave makes up to 12 rounds around the annular chamber at velocities up to 2700 m/s against 9 rounds (maximum) at velocities up to 2200 m/s when burning a jet fuel–oxygen mixture. The thrust created by the detonation module reaches 25% of the thrust of the turbojet engine associated with it.

Suggested Citation

  • Assad, Mohamad & Penyzkov, Oleq & Chernukho, Ivan, 2022. "Symbiosis of deflagration and detonation in one jet system – A hybrid detonation engine," Applied Energy, Elsevier, vol. 322(C).
    • Handle: RePEc:eee:appene:v:322:y:2022:i:c:s0306261922008005
    DOI: 10.1016/j.apenergy.2022.119474
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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. 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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    Cited by:

    1. Ding, Chenwei & Wu, Yuwen & Huang, Yakun & Zheng, Quan & Li, Qun & Xu, Gao & Kang, Chaohui & Weng, Chunsheng, 2023. "Wave mode analysis of a turbine guide vane-integrated rotating detonation combustor based on instantaneous frequency identification," Energy, Elsevier, vol. 284(C).

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