Numerical Study of Effect of Fuel Injection Angle on the Performance of a 2D Supersonic Cavity Combustor
Publication: Journal of Aerospace Engineering
Volume 25, Issue 2
Abstract
Direct injection into a cavity-based supersonic ramjet combustor has been recently considered to be an effective way of stabilizing the flame over a wide range of operating conditions. In the present study, two-dimensional (2D) supersonic combustor with direct fuel injection from the cavity floor with various fuel injection angles is simulated for both nonreacting and reacting conditions using Fluent software. The various complex flow features like upstream shocks, compression waves, and Mach reflection are formed in the flow field. Low velocity recirculation regions are observed in the cavity, which assists in flame holding. Heat release was observed to have significant effects on various flow structures formed both in the main stream and cavity regions. In nonreacting conditions, injection at 135° shows maximum pressure losses followed by injection angle of 120°. However, the 120° injection angle case exhibits better mixing over other cases. The present study indicates that any change in injection angle does not have any significant effect on the air entrainment. In reacting conditions, the 120° injection angle shows highest combustion efficiency because of better mixing properties exhibited by this location.
Get full access to this article
View all available purchase options and get full access to this article.
References
Abdel-Salam, T. M., and Carson, R. A. (2004). “Three-dimensional numerical study of a dual-mode scramjet combustor.” 37th AIAA Thermophysics Conf., AIAA-2002-805, American Institute of Aeronautics & Astronautics, Reston, VA.
Baurle, R. A., Eklund, D. R., and Gruber, M. R. (2001). “Numerical study of scramjet combustor fueled by aerodynamic ramp injector in dual mode combustion.” AIAA Conf., AIAA, Reston, VA, 0379.
Ben-Yaker, A., and Hanson, R. K. (2001). “Cavity flame-holders for ignition and flame stabilization in scramjets: an overview.” J. Propul. PowerJPPOEL, 17(4), 869–877.
Fluent 6.3 [Computer software]. (2006). Fluent Inc., Lebanon, NH.
Gruber, M., Donbar, J., Carter, C., and Hsu, K.-Y. (2004). “Mixing and combustion studies using cavity based flameholders in a supersonic flow.” J. Propul. PowerJPPOEL, 20(5), 769–778.
Heisner, W. H., Pratt, D. H., Dailey, D. H., and Mehta, U. B. (1994). “Hypersonic air breathing propulsion.” AIAA education series, AIAA, Washington, DC.
Hsu, K. Y., Donbar, J. M., Gruber, M. R., and Carter, C. D. (2004). “Mixing and combustion studies using cavity based flame holders in supersonic flow.” J. Propul. PowerJPPOEL, 20(5), 769–778.
Kim, K. M., Baek, S. W., and Han, C. Y. (2004). “Numerical study on supersonic combustion with cavity-based fuel injection.” Int. J. Heat Mass TransferIJHMAK, 47(2), 271–286.
Mathur, T., et al. (2001). “Supersonic combustion experiments with a cavity-based fuel injector.” J. Propul. PowerJPPOEL, 17(6), 1305–1312.
Mishra, D. P., and Sridhar, K. V. (2007). “Fuel injection and flame stabilization in a supersonic combustor.” Int. Conf. on High Speed Trans-Atmospheric Air and Space Transportation (ICHSTAST), Aeronautical Society of India, New Delhi, India.
Mohamed Ali, M. C., and Kurian, J. (2005). “Cavity-based injections into supersonic flow.” J. Propul. PowerJPPOEL, 21(6), 1130–1132.
Rajasekaran, A., and Babu, V. (2006). “Numerical simulation of three-dimensional reacting flow in a model supersonic combustor.” J. Propul. PowerJPPOEL, 22(4), 820–827.
Rasmussen, C. C., Driscoll, J. F., Hsu, K.-Y., Donbar, J.M., Gruber, M. R., and Carter, C. D. (2005). “Stability limits of cavity–stabilized flames in supersonic flow.” Proc. Combust. Inst., 30(2), 2825–2833.
Seiner, J. M., Dash, S. M., and Kenzakowski, D. C. (2001). “Historical survey on enhanced mixing in scramjet engines.” J. Propul. PowerJPPOEL, 17(6), 1273–1286.
Sridhar, K. V. (2008). “Computational studies of mixing and flame holding in a cavity based 2D supersonic combustor.” M. Tech. thesis, Indian Institute of Technology, Kanpur, India.
Sundararaj, K., and Dhandapani, S. (2006). “Numerical simulation of staged transverse injection of fuel in a ducted supersonic air stream with SST turbulence model.” Int. J. Fluid Dynam.IJCFEC, 2(2), 245–262.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 25 • Issue 2 • April 2012
Pages: 161 - 167
Copyright
© 2012. American Society of Civil Engineers.
History
Received: Dec 4, 2009
Accepted: Nov 8, 2010
Published online: Dec 4, 2010
Published in print: Apr 1, 2012
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.