Investigations of the Effect of Constant-Area Section on Thermal Choking in a Dual-Mode Scramjet Combustor
Publication: Journal of Aerospace Engineering
Volume 29, Issue 5
Abstract
The present study attempts to fix the location of thermal throat by employing transverse fuel injection downstream and adding a short constant-area section in the divergent part in a realistic scramjet combustor configuration in order to depress the pressure rise effects on the isolator. Ground tests using a direct-connect model along with pressure measurements and three-dimensional numerical simulation are also performed for the present investigations. The results indicate that the thermal throat is fixed in the constant-area section for the configuration with a short constant-area section in the divergent part. Numerical simulations also indicate that the constant-area section is helpful for ignition and flame holding. The configuration with a short constant-area section increase heat release in the combustor and decrease entropy production. Numerical simulation results imply that there could exist more than one thermal throat in dual-mode scramjet combustor, and the constant-area section in a divergent part could reduce the number of thermal throat.
Get full access to this article
View all available purchase options and get full access to this article.
Acknowledgments
This work is supported by the National Natural Science Foundation of China (grant numbers 51376193 and 91441204).
References
Anderson, W. K., Thomas, J. L., and Van Leer, B. (1985). “A comparison of finite volume flux vector splitting for the Euler equations.” AIAA 85-0122, American Institute of Aeronautics and Astronautics, Reston, VA.
Ben-Yakar, A., and Hanson, R. K. (2001). “Cavity flame-holders for ignition and flame stabilization in scramjets: An overview.” J. Propul. Power, 17(4), 869–877.
Bonanos, A. M., Schetz, J. A., O’Brien, W. F., and Goyne, G. P. (2008). “Dual-mode combustion experiments with an integrated aeroramp-injector/plasma-torch igniter.” J. Propul. Power, 24(2), 267–273.
Gruber, M. R., Carter, C. D., Montes, D. R., Haubelt, L. C., King, P. I., and Hsu, K.-Y. (2008). “Experimental studies of pylon-aided fuel injection into a supersonic crossflow.” J. Propul. Power, 24(3), 460–470.
Gruber, M. R., Donbar, J. M., Carter, C. D., and Hsu, K.-Y. (2004). “Mixing and combustion studies using cavity-based flameholders in a supersonic flow.” J. Propul. Power, 20(5), 769–778.
Heiser, W. H., and Pratt, D. T. (1994). Hypersonic airbreathing propulsion, American Institute of Aeronautics and Astronautics, Washington, DC.
Heiser, W. H., and Pratt, D. T. (2000). “Aerothermodynamics of the dual-mode combustion system.” Scramjet propulsion, E. T. Curran and S. N. B. Murthy, eds., American Institute of Aeronautics and Astronautics, Reston, VA, 569–595.
Ingenito, A., and Bruno, C. (2010). “Physics and regimes of supersonic combustion.” AIAA J., 48(3), 515–525.
Jameson, A., and Yoon, S. (1986). “LU implicit scheme with multiple grid for the Euler equations.” AIAA 86-0105, American Institute of Aeronautics and Astronautics, Reston, VA.
Kok, J. C. (2000). “Resolving the dependence on free-stream values for the k- turbulence model.” AIAA J., 38(7), 1292–1295.
Le, J., Yang, S., Liu, W., and Xing, J. (2005). “Massively parallel simulations of kerosene-fueled scramjet.” AIAA 2005-3318, American Institute of Aeronautics and Astronautics, Reston, VA.
Le, J., Yang, S., and Wang, X. (2011). “Numerical investigations of unsteady spray combustion in a liquid kerosene fueled scramjet.” ISABE-2011-1524, American Institute of Aeronautics and Astronautics, Reston, VA.
Mathur, T., et al. (2001). “Supersonic combustion experiments with a cavity based fuel injector.” J. Propul. Power, 17(6), 1305–1312.
Mattingly, J. D. (2006). Elements of propulsion-gas turbines and rockets, American Institute of Aeronautics and Astronautics, Reston, VA.
Micka, D. J., Torrez, S. M., and Driscoll, J. F. (2009). “Heat release distribution in a dual-mode scramjet combustor—Measurements and modeling.” AIAA 2009-7362, American Institute of Aeronautics and Astronautics, Reston, VA.
Ortwerth, P. J. (2000). “Scramjet flowpath integration.” Scramjet propulsion, E. T. Curran and S. N. B. Murthy, eds., Vol. 189, American Institute of Aeronautics and Astronautics, Reston, VA.
Segal, C. (2009). The scramjet engine: Processes and characteristics, Cambridge University Press, New York.
Steger, J. L., and Warming, R. F. (1981). “Flux vector splitting of the inviscid gas-dynamics equations with application to finite difference methods.” J. Comput. Phys., 40(2), 263–293.
Tian, Y., Yang, S., Deng, W., and Zhang, W. (2014). “Study on air throttling technology in the scramjet combustor.” J. Propul. Technol., 35(4), 499–506 (in Chinese).
Tomioka, S., Murakami, A., Kudo, K., and Mitani, T. (2001). “Combustion tests of a staged supersonic combustor with a strut.” J. Propul. Power, 17(2), 293–300.
Turns, S. R. (2000). An introduction to combustion: Concepts and applications, 2nd Ed., McGraw-Hill, Singapore.
Xing, J. (2007). “Applications of chemical equilibrium and flamelet model for the numerical simulation of scramjet.” Ph.D. thesis, China Aerodynamics Research and Development Center, Mianyang, Sichuan Province, China (in Chinese).
Xing, J., and Yang, Y. (2011). “Three-dimensional simulation of vitiation effects on combustor performance for Scramjet.” J. Propul. Technol., 32(1), 5–10 (in Chinese).
Zhao, H. (2005). “Parallel numerical study of whole scramjet engine.” Ph.D. thesis, China Aerodynamics Research and Development Center, Mianyang, Sichuan Province, China (in Chinese).
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 29 • Issue 5 • September 2016
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Aug 19, 2015
Accepted: Feb 10, 2016
Published online: May 11, 2016
Published in print: Sep 1, 2016
Discussion open until: Oct 11, 2016
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.