无阀式煤油脉冲爆震火箭发动机工作循环特性研究

推进技术 ›› 2018, Vol. 39 ›› Issue (5): 971-978.

无阀式煤油脉冲爆震火箭发动机工作循环特性研究

鲁唯,范玮,王可,张启斌,王彦斌

西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:鲁唯，男，博士生，研究领域为新概念推进技术及燃烧与流动。E-mail: luw23@126.com 通讯作者:范玮，女，博士，教授，研究领域为新概念推进技术及燃烧与流动。
基金资助:
国家自然科学基金(91441201；91641101；51376151)。

Study on Cycle Processes of a Valveless Kerosene-Fueled Pulse Detonation Rocket Engine

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探索脉冲爆震火箭发动机(Pulse Detonation Rocket Engine，PDRE)在无阀自适应工作方式下的工作特性，采用煤油为燃料，富氧空气为氧化剂，开展了验证性实验，并分析了单个工作循环中不同过程的特征时间。实验实现了PDRE在工作频率为60Hz下稳定工作。结果表明，在PDRE稳定工作的前提下，从点火到排气之间的时间相对固定；推进剂的填充时间占用了单个周期内的大部分时间，是限制发动机工作频率提高的主要因素；适当提高填充压力有助于提高PDRE工作频率；实验测得60Hz工作频率下，推进剂比冲为122±11s。

关键词: 脉冲爆震；无阀；煤油；频率；特征时间

Abstract: In order to study on the pulse detonation rocket engine at high frequency， experimental verification was performed on the valveless self-adaptive mode. Kerosene was utilized as fuel， and oxygen-enriched air as oxidizer. Characteristic time of each process during one cycle was also analyzed.?Fully developed detonation waves at a steady operating frequency of 60Hz were successfully obtained in the PDRE. The results indicated that， the time from ignition to exhaust is relatively fixed. Propellants injection occupied most of the time during one operating cycle， which limited the maximum frequency of the engine. It is feasible to improve the upper limit operating frequency of the PDRE by increasing the injection pressure in an appropriate range. The propellant-based specific impulse is 122±11s when the operating frequency of the engine is 60Hz.

Key words: Pulse detonation；Valveless；Kerosene；Frequency；Characteristic time

鲁唯,范玮,王可,张启斌,王彦斌. 无阀式煤油脉冲爆震火箭发动机工作循环特性研究[J]. 推进技术, 2018, 39(5): 971-978.

LU Wei,FAN Wei,WANG Ke,ZHANG Qi-bin,WANG Yan-bin. Study on Cycle Processes of a Valveless Kerosene-Fueled Pulse Detonation Rocket Engine[J]. Journal of Propulsion Technology, 2018, 39(5): 971-978.

参考文献

[1] 严传俊, 范玮. 脉冲爆震发动机原理及关键技术[M]. 西安:西北工业大学出版社, 2005.
[2] Wintenberger E, Austin J M, Cooper M, et al. Analytical Model for the Impulse of Single-Cycle Pulse Detonation Tube[J]. Journal of Propulsion and Power, 2003, 19(1): 22-38.
[3] Schauer F, Stutrud J, Bradley R. Detonation Initiation Studies and Performance Results for Pulsed Detonation Engine Applications[C]. Reno: 39th AIAA Aerospace Sciences Meeting & Exhibit, American Institute of Aeronautics and Astronautics, 2001.
[4] Landry K, Shehadeh R, Bouvet N, et al. Effect of Operating Frequency on PDE Driven Ejector Thrust Performance[C]. Tucson: 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005.
[5] 陈巍, 范玮, 李建玲, 等. 脉冲爆震火箭发动机高频实验研究[J]. 推进技术, 2011, 32(3): 443-446. (CHEN Wei, FAN Wei, LI Jian-ling, et al. Experiments on High Frequency Pulse Detonation Rocket Engine[J]. Journal of Propulsion Technology, 2011, 32(3): 443-446.)
[6] Li J, Fan W, Chen W, et al. Propulsive Performance of a Liquid Kerosene/Oxygen Pulse Detonation Rocket Engine[J]. Experimental Thermal and Fluid Science, 2011, 35(1): 265-271.
[7] 陈帆, 范玮, 王可, 等. 基于旋转阀的脉冲爆震火箭发动机实验[J]. 推进技术, 2013, 34(6): 860-864. (CHEN Fan, FAN Wei, WANG Ke, et al. Experiments on Rotary-Valved Pulse Detonation Rocket Engines[J]. Journal of Propulsion Technology, 2013, 34(6): 860-864.)
[8] Valaev A A, Zhimerin D G, Mironov E A, et al. Method and Apparatus for Intermittent Combustion[P]. US Patent: 3954380, 1976.
[9] Endo T, Obayashi R, Tajiri T, et al. Thermal Spray Using a High-Frequency Pulse Detonation Combustor Operated in the Liquid-Purge Mode[J]. Journal of Thermal Spray Technology, 2015, 25(3): 494-508.
[10] Matsuoka K, Mukai T, Endo T. Development of a Liquid-Purge Method for High-Frequency Operation of Pulse Detonation Combustor[J]. Combustion Science and Technology, 2015, 187(5): 747-764.
[11] Matsuoka K, Muto K, Kasahara J, et al. Development of High-Frequency Pulse Detonation Combustor without Purging Material[J]. Journal of Propulsion and Power, 2017, 33(1): 43-50.
[12] Matsuoka K, Muto K, Kasahara J, et al. Investigation of Fuid Motion in Valveless Pulse Detonation Combustor with High-Frequency Operation[J]. Proceedings of the Combustion Institute, 2017, 36(2): 2641-2647.
[13] 李牧. 多循环爆震起爆研究[D]. 西安:西北工业大学, 2007.
[14] 李牧, 严传俊, 王治武, 等. 无阀两相脉冲爆震发动机循环过程实验分析[J]. 推进技术, 2007, 28(1): 97-102. (LI Mu, YAN Chuan-jun, WANG Zhi-wu, et al. Experimental Analysis on Cycle Processes of Two-phase Valveless Pulse Detonation Engine[J]. Journal of Propulsion Technology, 2007, 28(1): 97-102.)
[15] Wang K, Fan W, Lu W, et al. Study on a Liquid-Fueled and Valveless Pulse Detonation Rocket Engine without the Purge Process[J]. Energy, 2014, 71(1): 605-614.
[16] Wang K, Fan W, Lu W, et al. Propulsive Performance of a Pulse Detonation Rocket Engine without the Purge Process[J]. Energy, 2015, 79(1): 228-234.
[17] Lu W, Fan W, Wang K, et al. Operation of a Liquid-Fueled and Valveless Pulse Detonation Rocket Engine at High Frequency[J]. Proceedings of the Combustion Institute, 2017, 36(2): 2657-2664.
[18] Gordon S, McBride B J. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications I: Analysis[R]. NASA RP 1311, 1994.
[19] McBride B J, Gordon S. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications II: User Manual and Program Description[R]. NASA RP 1311, 1996.
[20] Dabora E K, Ragland K W, Nicholls J A. Drop Size Effects in Spray Detonations[J]. Proceedings of the Combustion Institute, 1969, 12(1): 19-26.
[21] Ragland K W, Dabora E K, Nicholls J A. Observed Structure of Spray Detonations[J]. Physics of Fluids, 1968, 11(11): 2377-2388.
[22] Endo T, Kasahara J, Matsuo A, et al. Pressure History at the Thrust Wall of a Simplified Pulse Detonation Engine[J]. AIAA Journal, 2004, 42(9): 1921-1930.　　　　　　　　　　　　　*　收稿日期:2017-05-05；修订日期:2017-07-25。基金项目:国家自然科学基金(91441201；91641101；51376151)。作者简介:鲁唯,男,博士生,研究领域为新概念推进技术及燃烧与流动。E-mail: luw23@126.com通讯作者:范玮,女,博士,教授,研究领域为新概念推进技术及燃烧与流动。E-mail: weifan419@nwpu.edu.cn(编辑:梅瑛)