摘要
Combined-cycle pulse detonation engines are promising contenders for hypersonic propulsion systems.In the present study,design and propulsive performance analysis of combined-cycle pulse detonation turbofan engines(PDTEs)is presented.Analysis is done with respect to Mach number at two consecutive modes of operation:(1)Combined-cycle PDTE using a pulse detonation afterburner mode(PDA-mode)and(2)combined-cycle PDTE in pulse detonation ramjet engine mode(PDRE-mode).The performance of combined-cycle PDTEs is compared with baseline afterbuming turbofan and ramjet engines.The comparison of afterburning modes is done for Mach numbers from 0 to 3 at 15.24 km altitude conditions,while that of pulse detonation ramjet engine(PDRE)is done for Mach 1.5 to Mach 6 at 18.3 km altitude conditions.The analysis shows that the propulsive performance of a tubine engine can be greatly improved by replacing the conventional afterbumer with a pulse detonation afterburner(PDA).The PDRE also outperforms its ramjet counterpart at all flight conditions considered herein.The gains obtained are outstanding for both the combined-cycle PDTE modes compared to baseline turbofan and ramjet engines.
基金
This work was supported by the National Natural Science Foundation of China(NSFC No.50776045,51076064)
China Scholarship Council's International Students Scholarship(CSC No.2011YXS867)from the Minister of Education,China and NUAA.
