Thermal cycle analysis of the detonation combustion aero-engine

Continuous rotating detonation combustion offers the advantage of self-supercharging over conventional combustion, improving the thermodynamic cycle of aero-engine. Performance simulation models for a continuous rotating detonation engine as well as its components based on the component method were established. The thermodynamic cycle parameters were analyzed, and the engine performance was compared under conventional and detonation combustion modes. The results demonstrate that the established performance simulation model meets the design requirements of a continuous rotating detonation engine. As fan pressure ratio increases, the engine thrust increases and its fuel consumption rate decreases; as compressor pressure ratio increases, the engine thrust decreases and its fuel consumption rate decreases. Compared to conventional combustion mode engines, under design conditions, the engine thrust in detonation combustion mode is slightly increased, and the fuel consumption is reduced by 9.17%. Under throttled conditions, engines in detonation combustion mode generate greater thrust and have lower fuel consumption.