The potential advantages of rotating detonation combustion are gradually approved, and it is becoming a stable and controllable\nenergy conversion way adopted to the propulsion devices or ground-engines. This study focuses on the rotating detonationbased\nturboshaft engine, and the architecture is presented for this form of engine with compatibility between the\nturbomachinery and rotating detonation combustor being realized. The parametric performance simulation model for the\nrotating detonation-based turboshaft engine are developed. Further, the potential performance benefits as well as their\ngeneration mechanism are revealed, based on the comprehensive performance analysis of the rotating detonation-based\nturboshaft engine. Comparisons between the rotating detonation turboshaft engine and the conventional one reveal that the\nformer holds significant improvements in specific power, thermal efficiency, and specific fuel consumption at lower compressor\npressure ratios, and these improvements decrease with the increase of compressor pressure ratio and increase as turbine inlet\ntemperature increases. The critical compressor pressure ratio corresponding to the disappearance of specific power\nimprovement is higher than that corresponding to the disappearance of thermal efficiency and specific fuel consumption. These\ncritical compressor pressure ratios are positively correlated with flight altitude and negatively correlated with flight velocity. The\nconductive research conclusion is guidable for the design and engineering application of rotating detonation-based engines.
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