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http://dx.doi.org/10.12989/aas.2020.7.3.187

Numerical investigation of detonation combustion wave propagation in pulse detonation combustor with nozzle  

Debnath, Pinku (Department of Mechanical Engineering, National Institute of Technology Agartala)
Pandey, K.M. (Department of Mechanical Engineering, National Institute of Technology)
Publication Information
Advances in aircraft and spacecraft science / v.7, no.3, 2020 , pp. 187-202 More about this Journal
Abstract
The exhaust nozzle serves back pressure of Pulse detonation combustor, so combustion chamber gets sufficient pressure for propulsion. In this context recent researches are focused on influence of nozzle effect on single cycle detonation wave propagation and propulsion performance of PDE. The effects of various nozzles like convergent-divergent nozzle, convergent nozzle, divergent nozzle and without nozzle at exit section of detonation tubes were computationally investigated to seek the desired propulsion performance. Further the effect of divergent nozzle length and half angle on detonation wave structure was analyzed. The simulations have been done using Ansys 14 Fluent platform. The LES turbulence model was used to simulate the combustion wave reacting flows in combustor with standard wall function. From these numerical simulations among four acquaint nozzles the highest thrust augmentation could be attained in divergent nozzle geometry and detonation wave propagation velocity eventually reaches to 1830 m/s, which is near about C-J velocity. Smaller the divergent nozzle half angle has a significant effect on faster detonation wave propagation.
Keywords
detonation wave; nozzle shape; pulse detonation combustor; computational fluid dynamics;
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Times Cited By KSCI : 4  (Citation Analysis)
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1 Barbour, E.A., Hanson, R.K., Morris, C.I. and Radulescu, M.I. (2005), "A pulsed detonation tube with a converging-diverging nozzle operating at different pressure ratios", Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, U.S.A., January.
2 Chen, W., Fan, W., Zhang, Q., Peng, C., Yuan, C. and Yan, C. (2012), "Experimental investigation of nozzle effects on thrust and inlet pressure of an air-breathing pulse detonation engine", Chin. J. Aeronaut., 25(3), 381-387. https://doi.org/10.1016/S1000-9361(11)60399-3.   DOI
3 Cooper, M. and Shepherd, J.E. (2008), "Single-cycle impulse from detonation tubes with nozzles", J. Propulsion Power, 24(1), 81-87. https://doi.org/10.2514/1.30192.   DOI
4 Debnath, P. and Pandey, K.M. (2017), "Exergetic efficiency analysis of hydrogen-air detonation in pulse detonation combustor using computational fluid dynamics", Int. J. Spray Combust. Dyn., 9(1), 44-55. https://doi.org/10.1177%2F1756827716653344.   DOI
5 Dyer, R.S., Kaemming, T.A. and Baker, R.T. (2003), "Reaction ratio and nozzle expansion effects on the PDE performance", Proceedings of the 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, U.S.A., July.
6 Hsu, Y.C., Chao, Y.C. and Chung, K.M. (2018), "Detonation transmission with an abrupt change in area", Adv. Aircraft Spacecraft Sci., 5(5), 533-550. https://doi.org/10.12989/aas.2018.5.5.533.   DOI
7 Kailasanath, K. (2000), "Review of propulsion applications of detonation waves", AIAA J., 38(9), 1698-1708. https://doi.org/10.2514/2.1156.   DOI
8 Kuzmin, A. (2019), "Shock wave instability in a bent channel with subsonic/supersonic exit", Adv. Aircraft Spacecraft Sci., 6(1), 19-30. https://doi.org/10.12989/aas.2019.6.1.019   DOI
9 Yan, Y., Fan, W., Wang, K. and Mu, Y. (2011), "Experimental investigation of the effect of bell-shaped nozzles on the two-phase pulse detonation rocket engine performance", Combust. Explos. Shock Waves, 47(3), 335-342. https://doi.org/10.1134/S0010508211030117.   DOI
10 Yan, Y., Fan, W., Wang, K., Zhu, X. and Mu, Y. (2011), "Experimental investigations on pulse detonation rocket engine with various injectors and nozzles", Acta Astronautica, 69(1-2), 39-47. https://doi.org/10.1016/j.actaastro.2011.03.002.   DOI
11 Pandey, K.M. and Debnath, P. (2016), "Review on recent advances in pulse detonation engines", J. Combustion, 1-16. https://doi.org/10.1155/2016/4193034.
12 Allgood, D., Gutmark, E., Hoke, J., Bradley, R. and Schauer, F. (2006), "Performance measurements of multicycle pulse-detonation-engine exhaust nozzles", J. Propulsion Power, 22(1), 70-77. https://doi.org/10.2514/1.11499.   DOI
13 Ma, F., Choi, J.Y. and Yang, V. (2005), "Thrust chamber dynamics and propulsive performance of multitube pulse detonation engines", J. Propulsion Power, 21(4), 681-691. https://doi.org/10.2514/1.8182.   DOI
14 Ma, F., Choi, J.Y. and Yang, V. (2005), "Thrust chamber dynamics and propulsive performance of single-tube pulse detonation engines", J. Propulsion Power, 21(3), 512-526. https://doi.org/10.2514/1.7393.   DOI
15 Morris, C.I. (2005), "Numerical modeling of single-pulse gasdynamics and performance of pulse detonation rocket engines", J. Propulsion Power, 21(3), 527-538. https://doi.org/10.2514/1.7875.   DOI
16 Mouronval, A.S., Hadjadj, A. Kudryavtsev, A.N. and Vandromme, D. (2002), "Numerical investigation of transient nozzle flow", Shock Waves, 12, 403-411. https://doi.org/10.1007/s00193-002-0171-0.   DOI
17 Shao, Y., Liu, M. and Wang, J.P. (2010), "Continuous detonation engine and effects of different types of nozzle on its propulsion performance", Chin. J. Aeronaut., 23(6), 647-652. https://doi.org/10.1016/S1000-9361(09)60266-1.   DOI
18 Sutton, G.P. and Oscar, B. (2010), Rocket Propulsion Elements, (8th Edition), John Wiley & Sons, INC.
19 Li, Q., Fan, W., Yan, C., Hu, C. and Ye, B. (2007), "Experimental investigation on performance of pulse detonation rocket engine model", Chin. J. Aeronaut., 20(1), 9-14.   DOI
20 Tangirala, V.E., Dean, A.J., Tsuboi, N. and Hayashi, A.K. (2007), "Performance of a pulse detonation Engine under subsonic and supersonic flight conditions", Proceedings of the 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, U.S.A., Janaury.