A subsonic inlet of a pulse detonation engine (PDE) with aerodynamic valve is experimentally and numerically studied to obtain its flow structure and performance characteristics in both cold flow and ignited conditions. Results indicate that without combustion, the air flows into the inlet smoothly and no flow separation is found upstream the cone. However, after ignition, a detonation-induced pressure with a peak value of over 300 kPa is imposed on the inlet exit and it is found to oscillate periodically. Furthermore, since the aerodynamic valve cannot baffle the detonation-induced pressure effectively, the violent backpressure perturbation propagates upstream and passes through the aerodynamic valve within 2 ms. A reverse flow can be repeatedly observed near the inlet entrance in one cycle. Nearly half of the cycle is occupied by the reverse flow and its instantaneous Mach number can reach a peak of 0.8. To approximate the real experiment, the inlet flow field is numerically simulated and good agreements are found between the numerical and experimental results. In particular, the unsteady numerical results demonstrate again that due to the high detonation-induced pressure, there is a reverse flow in the entire entrance of the inlet. As a result of the reverse flow, a large reversed impulse is generated near the inlet entrance which is unfavourable to the PDE engine thrust. Hence, further studies should be carried out to improve the design of the aerodynamic valve.
WEN Yufen, TAN Huijun, LI Jianzhong, CHEN Wei, HAN Qixiang
. Investigation on the Inlet Flow Characteristics of a Pulse Detonation Engine with Aerodynamic Valve[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012
, 33(1)
: 44
-53
.
DOI: CNKI:11-1929/V.20110727.0907.003
[1] Bussing T, Pappas G. An introduction to pulse detonation engines. AIAA-1994-0263, 1994.
[2] Eidelman S. Pulse detonation engine: a status review and technology development road map.AIAA-1997-2740, 1997.
[3] Wintenberger E, Shepherd J E. Model for the performance of airbreathing pulse-detonation engines. Journal of Propulsion and Power, 2006, 22(3): 593-603.
[4] Yan C J, Fan W. Principles and crucial techniques of pulse detonation engine. Xi'an: Northwestern Polytechnical University Press, 2005: 239-257. (in Chinese) 严传俊, 范玮. 脉冲爆震发动机原理及关键技术. 西安: 西北工业大学出版社, 2005: 239-257.
[5] Oh J Y, Ma F H, Hsieh S Y, et al. Interactions between shock and acoustic waves in a supersonic inlet diffuser. Journal of Propulsion and Power, 2005, 21(3): 486-495.
[6] Mullagiri S, Segal C. Oscillating flows in inlets of pulse detonation engines. AIAA-2001-0669, 2001.
[7] Venkata N, Nelson L, Jonas G, et al. Forced oscillations in a mixed-compression inlet at Mach 3.5 for pulse detonation engine systems. Journal of Fluids Engineering, 2006, 128: 494-506.
[8] Ma F H, Choi J Y, Yang V. Internal flow dynamics in a valveless airbreathing pulse detonation engine. Journal of Propulsion and Power, 2008, 24(3): 479-490.
[9] Qiu H, Yan C J, Xiong C. Research on the effects of valveless operations of pulse detonation engine on supply system. Journal of Aerospace Power, 2010, 25(5): 987-992. (in Chinese) 邱华, 严传俊, 熊姹. 脉冲爆震发动机无阀工作对供给系统影响研究. 航空动力学报, 2010, 25(5): 987-992.
[10] Wang D X, Yan C J. Numerical study of the dynamics performance of an inlet for pulse detonation engines. Chinese Journal of Theoretical and Applied Mechanics, 2005, 37(6): 777-782. (in Chinese) 王丁喜, 严传俊. 脉冲爆震发动机进气道气动性能的数值研究. 力学学报, 2005, 37(6): 777-782.
[11] Chen W J, Zhang Q, Yan C J, et al. Elementary experimental investigation of air-breathing pulse detonation engines. Journal of Experiments in Fluid Mechanics, 2009, 3(2): 26-30. (in Chinese) 陈文娟, 张群, 严传俊,等. 吸气式脉冲爆震发动机原理性试验研究. 实验流体力学, 2009, 3(2): 26-30.
[12] Fan W, Yan C J, Huang X Q, et al. Experimental investigation on two-phase pulse detonation engine. Combustion and Flame, 2003, 133: 441-450.
[13] Li J Z, Wang J H, Fan Y X, et al. Experimental investigation on kerosene/air pneumatic valve pulse detonation engine. Journal of Aerospace Power, 2005, 20(5): 802-806. (in Chinese) 李建中, 王家骅, 范育新, 等. 煤油/空气气动阀式脉冲爆震发动机试验. 航空动力学报, 2005, 20(5): 802-806.
[14] James F W. Naturally aspirated fluidic control for diverting strong pressure waves: USA, US 2007/0015099A1. 2007-01-10.
[15] He X M, Wang J H. Investigation on the aerovalve two phase pulse detonation engine. Acta Aeronautica et Astronautica Sinica, 2004, 25(6): 529-533. (in Chinese) 何小民, 王家骅. 气动阀式两相脉冲爆震发动机研究. 航空学报, 2004, 25(6): 529-533.
[16] Zheng D F, Yang Y Y, Wang J H. Design and experimental study on whirl aero-valve for pulse detonation engine. Journal of Aerospace Power, 2010, 25(7): 1471-1477. (in Chinese) 郑殿峰, 杨义勇, 王家骅. 脉冲爆震发动机旋流式气动阀的设计与实验. 航空动力学报, 2010, 25(7): 1471-1477.
[17] Qiu H, Yan C J, Xiong C. Experimental investigation on characteristics of porus aerodynamic valve for pulse detonation engines. Journal of Experiments in Fluid Mechanics, 2010, 24(2): 39-45. (in Chinese) 邱华, 严传俊, 熊姹. 脉冲爆震发动机孔板型气动阀工作特性实验研究. 实验流体力学, 2010, 24(2): 39-45.
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