Numerical investigation of a non-premixed hollow rotating detonation engine |
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| Affiliation: | 1. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China;2. Space Engineering University, Beijing 101416, China;1. Center for Combustion and Propulsion, Department of Mechanics and Engineering Science, State Key Laboratory on Turbulence and Complex System, Peking University, Beijing 100871, China;2. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China |
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| Abstract: | Rotating detonation engines (RDEs) are widely studied because of their compact configurations and high thermal cycle efficiency. In this paper, a series of numerical investigations of a non-premixed hollow RDE are performed. The transient explicit density-based solver in ANSYS Fluent is used to perform the simulations. For a hollow RDE without Laval nozzle, there is only one rotating detonation wave in the combustion chamber. Compared to the traditional annular RDE, the mixing quality is deteriorated, and the thrust of the engine decreases and becomes more unstable. When the hollow RDE is attached with a Laval nozzle, there are two rotating detonation waves in the combustion chamber. The pressure within the combustion chamber increases while the axial velocity decreases. The mixing quality is improved. The height of detonation waves decreases with larger contraction ratio of the nozzle. A Laval nozzle is beneficial for a hollow RDE to achieve steadier operation and higher thrust output. When the contraction ratio is 4, the propulsive performance of the engine is the highest. The maximum thrust achieved is 840 N. |
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| Keywords: | Hollow rotating detonation engine Mixing quality Laval nozzle Contraction ratio Propulsive performance |
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