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The improvement of propulsion is an important engineering task, especially for aerospace vehicles. By changing the combustion process in the combustor from the usual isobaric deflagration to an isochoric detonation the cycle area can be enlarged (all other parameters being kept constant) and thus more efficiency is gained. The configuration of a circular detonator results in a rotating detonation engine (RDE) which is promissing a higher efficiency propulsor. A RDE using methane as fuel and oxygen as oxidizer (both in gaseous form) was developed, analyzed by numerical methods of different “fidelity” and tested. Depending on injector geometries and propellants mass flows different detonation patterns are found and a stable, long lasting operation is discussed.

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Comparison of Experimental and Numerical Results of a Methane-Oxygen Rotating Detonation Engine

  • 会议论文

  • 发表日期：

    2025年

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  • Ch. Mundt,
  • D. Vimercati,
  • S. Galindo-Lopez,
  • M. J. Cleary,
  • B. Thornber,
  • Q. Michalski,
  • A. Pudsey

摘要

The improvement of propulsion is an important engineering task, especially for aerospace vehicles. By changing the combustion process in the combustor from the usual isobaric deflagration to an isochoric detonation the cycle area can be enlarged (all other parameters being kept constant) and thus more efficiency is gained. The configuration of a circular detonator results in a rotating detonation engine (RDE) which is promissing a higher efficiency propulsor. A RDE using methane as fuel and oxygen as oxidizer (both in gaseous form) was developed, analyzed by numerical methods of different “fidelity” and tested. Depending on injector geometries and propellants mass flows different detonation patterns are found and a stable, long lasting operation is discussed.