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Chin. Phys. B, 2022, Vol. 31(10): 104701    DOI: 10.1088/1674-1056/ac80a9
ELECTROMAGNETISM, OPTICS, ACOUSTICS, HEAT TRANSFER, CLASSICAL MECHANICS, AND FLUID DYNAMICS Prev   Next  

Experimental study of the influence of annular nozzle on acoustic characteristics of detonation sound wave generated by pulse detonation engine

Yang Kang(康杨), Ning Li(李宁), Xiao-Long Huang(黄孝龙), and Chun-Sheng Weng(翁春生)
National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China
Abstract  Acoustic characteristics of the detonation sound wave generated by a pulse detonation engine with an annular nozzle, including peak sound pressure, directivity, and A duration, are experimentally investigated while utilizing gasoline as fuel and oxygen-enriched air as oxidizer. Three annular nozzle geometries are evaluated by varying the ratio of inner cone diameter to detonation tube exit diameter from 0.36 to 0.68. The experimental results show that the annular nozzles have a significant effect on the acoustic characteristics of the detonation sound wave. The annular nozzles can amplify the peak sound pressure of the detonation sound wave at 90° while reducing it at 0° and 30°. The directivity angle of the detonation sound wave is changed by annular nozzles from 30° to 90°. The A duration of the detonation sound wave at 90° is also increased by the annular nozzles. These changes indicate that the annular nozzles have an important influence on the acoustic energy distribution of the detonation sound wave, which amplify the acoustic energy in a direction perpendicular to the tube axis and weaken it along the direction of the tube axis.
Keywords:  pulse detonation engine      annular nozzle      detonation sound wave      acoustic characteristics  
Received:  04 May 2022      Revised:  01 July 2022      Accepted manuscript online: 
PACS:  47.40.Rs (Detonation waves)  
  43.25.Jh (Reflection, refraction, interference, scattering, and diffraction of intense sound waves)  
  43.28.Mw (Shock and blast waves, sonic boom)  
Fund: Project supported by the Natural Science Foundation of Jiangsu Province, China (Grant No. BK20220919) and the National Key Laboratory of Transient Physics Foundation Project, China (Grants No. 6142604210203).
Corresponding Authors:  Ning Li     E-mail:  phoenixkyo@163.com

Cite this article: 

Yang Kang(康杨), Ning Li(李宁), Xiao-Long Huang(黄孝龙), and Chun-Sheng Weng(翁春生) Experimental study of the influence of annular nozzle on acoustic characteristics of detonation sound wave generated by pulse detonation engine 2022 Chin. Phys. B 31 104701

[1] Roy G D, Frolov S M, Borisov A A and Netzer D W 2004 Prog Energy Combust. Sci. 30 545
[2] Wolański P 2013 Proc Combust. Inst. 34 125
[3] Lin L, Hu S A, Hu Y B, Xu G J, Jiao H Y and Weng C S 2020 Def. Technol. 16 178
[4] Xu G Y, Weng C S, Li N and Huang X L 2016 Int. J. Turbo. Jet Eng. 33 19
[5] H E, Reiff C G, Benwell B T and Kohlberg I 2000 38 th Aerospace Sciences Meeting & Exhibit , January 10—13, 2000, Reno, USA, p. 0610
[6] Wang Z W, Qin W F, Huang J J, Wei L S, Wang Y F and Zhang L F 2021 Aerosp. Sci. Technol. 117 106907
[7] Peace J T and Lu F K 2015 51 st AIAA/SAE/ASEE Joint Propulsion Conference, July 27—29, 2015, Orlando, USA, p. 4189
[8] Ferlauto M, Ferrero A and Marsilio R 2020 AIAA Propulsion and Energy 2020 Forum, August 24—28, 2020, VIRTUAL EVENT, p. 3777
[9] Allgood D, Glaser A, Caldwell N and Gutmark E 2004 10 th AIAA/CEAS AeroAcoust. Conference, May 10, 2004, Manchester, Great Britain, p. 2879
[10] Glaser A, Caldwell N and Gutmark E 2005 43 rd AIAA Aerosp. Sci. Meeting Exhibit, January 10—13, 2005, Reno, USA, p. 1345
[11] Glaser A, Caldwell N and Gutmark E 2006 12 th AIAA/CEAS AeroAcoust. Conference, May 8—10, 2006, Cambridge, USA, p. 2453
[12] Anand V, Glaser A and Gutmark E 2018 AIAA J. 56 2806
[13] Huang X Q, Li M Q, Yuan Y Y, Xiong Y F and Zheng L X 2015 Adv. Mech. Eng. 7 1
[14] Shaw L, Harris K, Schauer F and Hoke J 2005 11 th AIAA/CEAS AeroAcoust. Conference, May 23—25, 2005, Monterey, USA, p. 2952
[15] Kang Y, Li N, Weng C S and Wang C W 2018 Chin. Phys. B 27 104703
[16] Zheng L X, Li N and Yan C J 2009 47 th AIAA Aerosp. Sci. Meeting including The New Horizons Forum Aerosp. Exposition, Janurary 5—8, 2009, Orlando, USA, p. 297
[17] Huang X Q, Guo Z, Liu K, Li M Q and Zheng L X 2016 Proc. IMechE. part G: J. Aerospace Engineering 231 254
[18] Xu G Y, Wang C G, Zhu Y F, Li H Y, Gong L K and Wang J N 2020 Int. J. Turbo Jet Eng. published online
[19] Zhu Y F, Xu G Y, Wang C G, Gong L K and Wang J N 2020 Int. J. Turbo Jet Eng. 37 71
[20] Huang X L, Weng C S, Li N and Xu G Y 2017 J. Propul. Tech. 38 194
[21] Kang Y, Li N, Weng C S and Huang X L 2020 Chin. Phys. B 29 014703
[22] He H 2006 Numerical simulations of unsteady flows in a pulse detonation engine by the space-time conservation element and solution element method, Ph. D. Dissertation (Ohio: The Ohio State University)
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