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

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基于旋转爆轰的涡轮轴发动机的综合性能分析

旋转爆轰燃烧的潜在优势逐渐得到认可，已成为推进装置或地面发动机采用的稳定，可控的能量转换方式。这项研究集中在基于旋转爆震的涡轮轴发动机上，提出了这种形式的发动机的架构，实现了涡轮机械与旋转爆震燃烧器之间的兼容性。建立了基于旋转爆轰的涡轮轴发动机的参数性能仿真模型。此外，基于对基于旋转爆轰的涡轮轴发动机的综合性能分析，揭示了潜在的性能优势及其产生机理。旋转爆震涡轮轴发动机与常规发动机的比较表明，前者在较低的压缩机压力比下具有比功率，热效率和比燃料消耗的显着改善，并且这些改善随着压缩机压力比的增加而减小，并且随着涡轮机的增加而增加。入口温度升高。对应于比功率改善的消失的压缩机临界压力比高于对应于热效率和比燃料消耗的消失的压缩机临界压力比。这些临界压缩机压力比与飞行高度正相关，与飞行速度负相关。传导性研究结论对于旋转爆轰发动机的设计和工程应用具有指导意义。