Comparative performance analysis of combinedcycle pulse detonation turbofan engines (PDTEs)  

作　　者：Sudip Bhattrai Hao Tangn 

机构地区：[1]Nanjing University of Aeronautics and Astronautics,Nanjing,Jiangsu 210016,China

出　　处：《Propulsion and Power Research》2013年第3期214-224,共11页推进与动力（英文）

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.

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.

关 键 词：Single-stage-to-orbit(SSTO) Afterburners Integrated propulsion systems Turbine-based combined-cycle(TBCC) Rocket-based combined-cycle(RBCC) 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]