An parametric analytical model was developed for the continuous rotating detonation turbine engine (CRDTE) to predict the engine performance for various compression ratios and turbine inlet temperatures. The results show that increasing the compression ratio first increases the specific thrust and the thermal efficiency but they then decrease. Increasing the turbine inlet temperature increases the specific thrust and the thermal efficiency. The engine has better overall performance than a conventional aero-turbine engine with the same cycle parameters over the entire working range as explained by the results. The specific thrust is significantly better than that of the advanced F119 aero-turbine engine and the specific fuel consumption is reduced slightly for the same cycle parameters. Thus, the CRDTE design is quite reasonable and this model can be used for engineering designs.
摘要 该文提出一种完整的连续旋转爆震涡轮发动机 (continuous rotating detonation turbine engine, CRDTE) 系统方案, 建立了其主要工作过程的数学模型以及参数化整机性能分析模型。研究了压气机总增压比、涡轮前总温等设计参数对发动机总体性能的影响。结果表明：随着压气机总增压比的增大, 发动机的比推力和循环热效率先增大后减小, 耗油率单调增大, 而涡轮前总温越大, 发动机的比推力和耗油率越高。与同参数传统燃气涡轮发动机进行了总体性能比较研究, 表明CRDTE在全工作范围总体性能具有优势, 并揭示了其获得性能增益的原因。与现役先进航空燃气涡轮发动机F119相比, 在相同循环参数条件下, CRDTE的比推力显著提升, 同时耗油率稍有降低。该旋转爆震涡轮发动机方案合理、可行, 为其工程化应用提供了依据。