Appraisal Burning Characteristic and Analysis Effect of Cavity in Scramjet Combustion Chamber
Main Article Content
Abstract
The combustion chamber clearly plays an critical role in generating thrust force so the aircraft can move forward. A scramjet (supersonic combustion ramjet) is a variant of a ramjet airbreathing jet engine in which combustion takes place in supersonic airflow. Researchers are constantly working to improve the efficiency of ultrasonic combustion furnaces by various methods such as: optimize fuel injectors, optimize combustion chamber geometry design, create hole cavity. In this research, the characteristic of supersonic airflow were investigated, and a comparison between the standard chamber and advanced chamber was made to determine the effects of a circular hole (cavity) on pressure and velocity of the fuel mixture through the scramjet. Two dimensional Reynolds-Averaged Navier-Stokes governing(RANS) equations with k−ε turbulence model and finite rate/eddy dissipation chemistry model have been considered for modelling chemical reacting flows. From the comparison of numerical results, it is found that the development of recirculation regions and additional shock waves from the edge of cavity flame holder is increased and achieved stabilized combustion. From this research analysis, the performance of the scramjet engine with cavity is significantly improved as compared to the design without cavity.
Keywords
Combustion chamber, Scamjet, Cavity, RANS Analysis, Shock wave, Thrust.
Article Details
References
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angle of attack on the performance of two-strut
scramjet combustor, International Journal of Hydrogen
Energy, vol. 41, no. 26, pp. 11455–11470, 2016,
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combustor with innovative designs of strut injector,
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25, pp. 13659–13671, 2020
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for ignition and flame stabilization in scramjets:
Review and experimental study, In 34th
AIAA/ASME/SAE/ASEE Joint Propulsion
Conference and Exhibit, American Institute of
Aeronautics and Astronautics Inc, AIAA, 1998,
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supersonic and subsonic combustion modes in a model
combustor, International Journal of Hydrogen Energy,
vol. 45, no. 1, pp. 1045–1060, 2020
https://doi.org/10.1016/j.ijhydene.2019.10.193.
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of reaction zone in a dual-mode scramjet combustor
during mode transitions, Aerospace Science and
Technology, vol. 99, 2020
https://doi.org/10.1016/j.ast.2020.105779.
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simulations of single and multi-staged injection of H2
in a supersonic scramjet combustor, Propulsion and
Power Research, vol. 3, no. 4, pp. 175–186, 2014,
https://doi.org/10.1016/j.jppr.2014.12.001.
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mechanisms for hydrogen on supersonic combustion
using large eddy simulation, International Journal of
Hydrogen Energy, vol. 44, no. 10, pp. 5007–5019,
2019
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Hsu, Fundamental studies of cavity-based flameholder
concepts for supersonic combustors, Journal of
Propulsion and Power, vol. 17, no. 1, pp. 146–153,
2001
https://doi.org/10.2514/2.5720.
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Clauss, and M. Oschwald, Experimental investigation
of the combustion process in a supersonic combustion
ramjet (SCRAMJET) Combustion Chamber, in:
DGLR-Jahrestagung 1994; 04. - 07.10.1994; Erlangen.