Abstract
The application of the combination of rotating detonation combustor and turbine to propulsion system is a recent research focus. This paper verifies the feasibility of this combined propulsion method through numerical simulation, and the flow law and flow loss mechanism in the turbine stator passage under complex inlet conditions are obtained. The results show that the flow field in the turbine stator has serious circumferential unevenness. The interaction between the rotating pulsating wave and the blade is the main cause of flow loss.
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