φ180mm脉冲爆震发动机热力性能研究
Investigation on thermodynamic performance of pulse detonation engine with 180 mm
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摘要: 采用经验数据和计算相结合的方法预估直径180 mm,长度为2.2 m带气动阀的脉冲爆震发动机(Pulse Detonation Engine,简称PDE)的性能,并考虑PDE内的总压损失.计算结果和实测结果基本吻合.计算中发现,由于考虑了PDE内总压损失,PDE推力比理想情况低,油耗比理想情况大.该计算方法对预估实际PDE工作性能具有较大的参考价值.
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关键词:
- 航空、航天推进系统、脉冲爆震发动机(PDE) /
- 爆轰 /
- 性能预估 /
- 总压损失
Abstract: The performance of Pulse Detonation Engine(PDE) with aerovavle of diameter 180 mm、length 2.2 m was pre-estimated by using a method combining experiential data and computation, at the same time the total pressure loss inside the PDE was taken into account.The computational results basically match the results obtained from the experiments.It was found that the thrust of PDE was lower than that in ideal case and specific fuel consumption(SFC) was larger than that in ideal case, due to that the total pressure loss was considered.This computational method is valuable for pre-estimating the performance of PDE in actual operation. -
[1] Goracke D B,Levack D J H.Tripropellant engine drive cycle consideration for SSTO application[R].AIAA 95-2950. [2] Manski D.Cycles for earth-to-orbit propulsion[J].Journal of Propulsion and Power,1998,14(5):558-604. [3] Colasurdo G,Pastrone D,Casaliono L.Optimal performance of a dual-fuel single-stage rocket[J].Journal of Spacecraft and Rockets,1998,35(5):667-671. [4] 范育新,王家骅,李建中,等.脉冲爆震发动机净推力系数研究[J].南京航空航天大学学报,2004,36(3):273-277.FAN Yuxin,WANG Jiahua,LI Jianzhong,et al.Experimental investigation on net thrust characteristics of pulse detonation engine[J].Journal of Nanjing University of Aeronautics & Astronautics,2004,36(3):273-277. [5] Mawid M,Park T,Sekar B.Performance analysis of a pulse detonation device as an afterburner[R].AIAA 2000-3474. [6] LI C,Kailasanath K.A numerical study of reactive flows in pulse detonation engines[R].AIAA,2001-3933. [7] Kailasanath K,Patnaik G,LI C.Computational studies of pulse detonation engines:a status report[R].AIAA,99-2634. [8] Ebrahimi H B,Mohanraj R,Merkle C L.Numerical simulation of a pulsed detonation engine with hydrogen fuels[J].Journal of Propulsion and Power,2002,18(5):1042-1048. [9] Roy G D,Frolov S M,Borisov A A,et al.Pulse detonation propulsion:challenges,current status,and future perspective[J].Progress in Energy and Combustion Science,2004,30:545-672. [10] Chao T W,Wintenberger E,Shepherd J E.On the design of pulse detonation engines,GALCIT report FM 00-7[R].Graduate Aeronautical Laboratories,California Institute of Technology,Pasadena:CA 91125,2001. [11] Talley D,Coy E.Constant volume limit of pulsed propulsion for a constant ideal gas[J].Journal of Propulsion and Power,2002,18(2):400-406. [12] 张义宁,王家骅,张靖周.多循环吸气式脉冲爆震发动机推力直接测量[J].推进技术,2006,27(5):459-468.ZHANG Yining,WANG Jiahua,ZHANG Jingzhou.Impulse of cyclic air-breathing pulse detonation engine[J].Journal of propulsion technology,2006,27(5):459-468.
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