Advances in aircraft and spacecraft science

  • 제7권3호
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  • Pages.187-202
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  • 2020
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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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)
  • 투고 : 2019.03.07
  • 심사 : 2019.11.13
  • 발행 : 2020.05.25
⟨ 이전 논문 다음 논문 ⟩

초록

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.

키워드

참고문헌

  1. 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.
  2. 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.
  3. 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.
  4. 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.
  5. 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. https://doi.org/10.1177/1756827716653344
  6. 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.
  7. 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.
  8. Kailasanath, K. (2000), "Review of propulsion applications of detonation waves", AIAA J., 38(9), 1698-1708. https://doi.org/10.2514/2.1156.
  9. 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
  10. 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. https://doi.org/10.1016/S1000-9361(07)60002-8
  11. 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.
  12. 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.
  13. 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.
  14. 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.
  15. 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.
  16. 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.
  17. Sutton, G.P. and Oscar, B. (2010), Rocket Propulsion Elements, (8th Edition), John Wiley & Sons, INC.
  18. 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.
  19. 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.
  20. 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.