两相脉冲爆轰发动机尾喷管的实验研究

推进技术 ›› 2014, Vol. 35 ›› Issue (2): 282-288.

• 新型动力 • 上一篇

两相脉冲爆轰发动机尾喷管的实验研究

王研艳,翁春生

南京理工大学瞬态物理国家重点实验室,江苏南京 210094;南京理工大学瞬态物理国家重点实验室,江苏南京 210094

发布日期:2021-08-15
作者简介:王研艳(1985—),女,博士生,研究领域为脉冲爆轰推进。E-mail:wangyyjh@126.com通讯作者:翁春生(1964—),男,博士,教授,研究领域为推进技术。E-mail:wengcs@126.com
基金资助:
国家自然科学青年基金(11002074)；高等学校博士学科点专项科研基金(20113219120045);国防预研基金(9140c300202120c30)。

Experimental Investigation on Nozzles of Two-Phase Pulse Detonation Engine

National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China;National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China

Published:2021-08-15

摘要/Abstract

摘要： 为了提高脉冲爆轰发动机的推进性能,实验研究了12种不同构型尾喷管对火箭式两相脉冲爆轰发动机爆轰特性和推进性能的影响,并对各类尾喷管的增推原因进行分析。结果表明满填充工况下各类喷管内的爆轰特性不尽相同,收敛喷管可得到最大压力峰值；在满填充工况下频率为10Hz时12种喷管构型中拉伐尔喷管的推力增益最大,塞式收敛扩张喷管其次；拉伐尔喷管的出口面积比对推力增益有较大影响,但收敛段-扩张段长度比对推力增益影响甚微。 

关键词: 脉冲爆轰发动机;推进性能;爆轰特性;尾喷管;实验研究 

Abstract: Pulse detonation rocket engines (PDREs) with twelve different nozzles were studied experimentally to evaluate their detonation characteristics and propulsive performance in multi-cycle systems. The reason of the thrust variations of two-phase PDREs affected by different nozzles was analyzed. As the results, the detonation waves are quite different in the tested nozzles of PDREs, with the highest pressure peak appearing in the convergent nozzle when the engines are full filled with fuel. It is also found that the Laval nozzle offers the highest thrust augmentation among the tested nozzles, followed by the plug-in-convergent-divergent nozzle at the operation frequency of 10Hz. In addition, the exit-to-inlet area ratio of the Laval nozzle has significant influence on thrust augmentation, while the convergent-to-divergent length ratio has little influence. 

Key words: Pulse detonation engine; Propulsive performance; Detonation characteristics; Exhaust nozzle; Experimental analysis

王研艳,翁春生. 两相脉冲爆轰发动机尾喷管的实验研究[J]. 推进技术, 2014, 35(2): 282-288.

WANG Yan-yan,WENG Chun-sheng. Experimental Investigation on Nozzles of Two-Phase Pulse Detonation Engine[J]. Journal of Propulsion Technology, 2014, 35(2): 282-288.

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] Brophy C M, Dausen D F, Smith L R, et al.Fluidic Nozzles for Pulse Detonation Combustors[R].AIAA 2012-1035.
[3] Kimura Y, Hayashi A K, Yamada E, et al.Performance Evaluations of Exhaust Nozzles for Pulse Detonation Engines[R].AIAA 2008-984.
[4] 范玮, 严传俊, 李强, 等.脉冲爆震发动机尾喷管的实验[J].航空动力学报, 2007,2(6):869-872.
[5] Wang Z W, Yan C J, Fan W, et al.Experimental Investigation of the Nozzle Effects on a Two-Phase Valveless Air-Breathing Pulse Detonation Engine[R].AIAA 2008-991.
[6] Tsuboi N, Kimura Y, Hayashi A K, et al.Numerical Study and Performance Evaluation for Pulse Detonation Engine with Exhaust Nozzle[R].AIAA 2009-5315.
[7] Allgood D, Gutmark E, Hoke J, et al.Performance Measurements of Multi-Cycle Pulse Detonation Engine Exhaust Nozzles[R].AIAA 2005-222.
[8] 孙孔倩,樊未军,杨茂林.爆震管喷管流动数值研究[J].推进技术,2009,0(3):360-365.(SUN Kong-qian, FAN Wei-jun, YANG Mao-lin.Numerical Simulation of Nozzle Flow on Detonation Duct[J].Journal of Propulsion Technology, 2009,0(3):360-365.)
[9] Yan Y, Fan W, Wang K, et al.Experimental Investigations on Pulse Detonation Rocket Engine with Various Injectors and Nozzles[J].Acta Astronautica, 2011,9:39-47.
[10] Ma F, Choi J Y, V Yang.Propulsive Performance of Air Breathing Pulse Detonation Engines[J].Journal of Propulsion and Power, 2006,2(6):1188-1203.
[11] Caldwell N, Gutmark E, Hoke J, et al.Investigation of Fundamental Processes Leading to Pulse Detonation Engine/Ejector Thrust Augmentation[R].AIAA 2008-116.
[12] Peng C X, Fan W, Zhang Q, et al.Experimental Study of an Air-Breathing Pulse Detonation Engine Ejector[J].Experimental Thermal and Fluid Science, 2011,5:971-977.
[13] 黄玥,唐豪,李建中,等.多管脉冲爆震发动机共用尾喷管特性的数值模拟[J].南京航空航天大学学报,2009,1(4):432-438.
[14] 曾昊, 何立明, 章雄伟, 等.喷管收敛-扩张角对爆震发动机性能影响分析[J],推进技术, 2011,2(1):97-102.(ZENG Hao, HE Li-ming, ZHANG Xiong-wei, et al.Investigation on the Effects of Nozzles with Different Convergent-Divergent Angle on PDE Performance[J].Journal of Propulsion Technology, 2011,2(1):97-102.)
[15] Kailasanath K.A Review of Research on Pulse Detonation Engine Nozzles[R].AIAA 2001-3932.

两相脉冲爆轰发动机尾喷管的实验研究

Experimental Investigation on Nozzles of Two-Phase Pulse Detonation Engine

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