As the first step of development of a small size Rotating Detonation Engine (RDE) for student rocket project, a middle size RDE which has a combustor with a 100-mm diameter, has been designed and examined its combustion characteristics. Hydrogen and Air mixture gas was supplied up to 110 g/s of mass flow rate. The thrust and wavefront velocity were measured as the function of equivalent ratio. Home-made pressure transducers made of PZT were employed to detect propagated wavefront. Also, chemiluminescence of detonation front was visualized with a high-speed camera. Obtained wavefront velocities indicated about 60% of Chapman-Jouguet (C-J) velocity due to unexpected deceleration of wavefront inside an igniter. After the first experiment, the wavefront velocity inside the igniter was improved by increasing mass flow rate of the igniter. The results were compared to literature and discussed to improve performance of the middle size RDE.

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Fundamental Characteristics of ∅100 RDE with H2/Air

  • S. Takezawa,
  • R. Suzuki,
  • R. Ozawa,
  • F. Wang,
  • T. Mizukaki

摘要

As the first step of development of a small size Rotating Detonation Engine (RDE) for student rocket project, a middle size RDE which has a combustor with a 100-mm diameter, has been designed and examined its combustion characteristics. Hydrogen and Air mixture gas was supplied up to 110 g/s of mass flow rate. The thrust and wavefront velocity were measured as the function of equivalent ratio. Home-made pressure transducers made of PZT were employed to detect propagated wavefront. Also, chemiluminescence of detonation front was visualized with a high-speed camera. Obtained wavefront velocities indicated about 60% of Chapman-Jouguet (C-J) velocity due to unexpected deceleration of wavefront inside an igniter. After the first experiment, the wavefront velocity inside the igniter was improved by increasing mass flow rate of the igniter. The results were compared to literature and discussed to improve performance of the middle size RDE.