Abstract：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.
计自飞, 张会强, 谢峤峰, 王兵. 连续旋转爆震涡轮发动机热力过程与性能分析[J]. 清华大学学报（自然科学版）, 2018, 58(10): 899-905.
JI Zifei, ZHANG Huiqiang, XIE Qiaofeng, WANG Bing. Thermodynamic process and performance analysis of the continuous rotating detonation turbine engine. Journal of Tsinghua University(Science and Technology), 2018, 58(10): 899-905.
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