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Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7

Received: 18 November 2020     Accepted: 1 December 2020     Published: 16 December 2020
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Abstract

The incomplete mixing of fuel and the drag induced in the engine are the main problems encountered in scramjets. Proper mixing of fuel can be achieved if the fuel is injected from the inlet of the engine. The fluid domain of Busemann Inlet at Mach 7 with boundary layer fuel injection using slot injectors along the wall was simulated with hydrogen fuel. Static pressure ratio at throat and inlet, along with Mach number at the throat were the design parameters of the Busemann inlet. Hydrogen fuel injection at two different equivalence ratios (0.3 and 0.7) was simulated successively at a temperature of 100 K and Mach 2.5. The state of mixing was studied for three different injection angles (30°, 45°, and 60°) for different equivalence ratios. The injection angles do not have a substantial effect on the hydrogen fuel mixing with the mainstream flow for equivalence ratio 0.3 Whereas, the dispersion of fuel increases as the increase in injection angles for equivalence ratio 0.7. But the total pressure recovery is maintained to the design value for equivalence ratio 0.3 rather than 0.7. Similarly, 45° fuel injection maintains a higher total pressure recovery than in other injection angles of 30° and 60°. Injection technique other than slot injection can be used to study further the effect of fuel mixing in Busemann Inlet.

Published in American Journal of Mechanics and Applications (Volume 8, Issue 3)
DOI 10.11648/j.ajma.20200803.11
Page(s) 33-39
Creative Commons

This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.

Copyright

Copyright © The Author(s), 2020. Published by Science Publishing Group

Keywords

Busemann Inlet, Hypersonic, Equivalence Ratio, Fuel Injection, Mass Fraction

References
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[2] D. M. Bushnell, "Mixing and Combustion Issues in Hypersonic Air-Breathing Propulsion," Combustion in high-speed flows., pp. 3-16, 1994.
[3] D. M. Van Wie, S. M. D’Alessio and M. E. White, "Hypersonic airbreathing propulsion.," Johns Hopkins APL technical digest, vol. 26, no. 4, pp. 430-437, 2005.
[4] J. Barth, "Mixing and combustion enhancement in a Mach 12 shape-transitioning," 2014.
[5] J. Turner, "An Experimental Investigation of Inlet Fuel Injection in a Three- Dimensional Scramjet Engine," 2010.
[6] V. Wheatley and P. A. Jacobs, "Fuel injection via rectangular crosssection injectors for mixing enhancement in scramjets.," in 17th Australasian Fluid Mechanics Conference 2010, 2010.
[7] T. K. Ngo, "Effect of injection strategy and mainstream combustion on skin friction reduction through boundary layer combustion in scramjet combustors.," 2016.
[8] F. Billig, J. Schetz and S. Favin, "Analysis of slot injection beneath a thick hypersonic boundary layer," in 25th Joint Propulsion Conference, 1991.
[9] F. Billig, J. Schetz and S. Favin, "Gaseous injection in high speed flow," in International Symposium on Air Breathing Engines, Athens, Greece, 1989.
[10] L. Foster and W. Engblom, "Computation of Transverse Injection into Supersonic Crossflow with Various Injector Orifice Geometries.," in 42nd AIAA Aerospace Sciences Meeting and Exhibit, 2004.
[11] J. E. Barth, V. Wheatley and M. K. Smart, "Effects of hydrogen fuel injection in a Mach 12 scramjet inlet," AIAA Journal 53.10, pp. 2907-2919, 2015.
[12] C. Macleod and C. E. Gerrard., "A review of air-fuel mixing and alternative methods in scramjets and scramjet-like engines," Journal of the British Interplanetary Society, vol. 69, no. 4, 2016.
[13] R. C. Rogers, A study of the mixing of hydrogen injected normal to a supersonic airstream, National Aeronautics and Space Administration, 1971.
[14] A. D. Gardner, A. Paull and T. J. McIntyre., "Upstream porthole injection in a 2-D scramjet model," Shock Waves, vol. 11, no. 5, pp. 369-375, 2002.
[15] H. Huh and J. F. Driscoll, "Shock-wave-enhancement of the mixing and the stability limits of supersonic hydrogen-air jet flames," Symposium (International) on Combustion, vol. 26, no. 2, pp. 2933-2939, 1996.
[16] Ansys Fluent, Software Package, Ver. 19.1, Ansys, Pennsylvania, United States.
[17] Pointwise, Software Package, 18.0 R3, Pointwise Inc., Texas, United States.
[18] Soni, R. Kumar and A. De, "Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics.," Journal of Mechanical Science and Technology, vol. 31, no. 3, pp. 1169-1179, 2017.
[19] Y. Andreopoulos, J. H. Agui and G. Briassulis, "Shock wave — turbulence interactions.," Annual Review of Fluid Mechanics, vol. 32, no. 1, pp. 309-345, 2000.
Cite This Article
  • APA Style

    Kamal Darlami, Rajan Bhandari, Abhishek Pandey, Sanjeev Adhikari, Sabin Subedi. (2020). Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7. American Journal of Mechanics and Applications, 8(3), 33-39. https://doi.org/10.11648/j.ajma.20200803.11

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    ACS Style

    Kamal Darlami; Rajan Bhandari; Abhishek Pandey; Sanjeev Adhikari; Sabin Subedi. Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7. Am. J. Mech. Appl. 2020, 8(3), 33-39. doi: 10.11648/j.ajma.20200803.11

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    AMA Style

    Kamal Darlami, Rajan Bhandari, Abhishek Pandey, Sanjeev Adhikari, Sabin Subedi. Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7. Am J Mech Appl. 2020;8(3):33-39. doi: 10.11648/j.ajma.20200803.11

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  • @article{10.11648/j.ajma.20200803.11,
      author = {Kamal Darlami and Rajan Bhandari and Abhishek Pandey and Sanjeev Adhikari and Sabin Subedi},
      title = {Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7},
      journal = {American Journal of Mechanics and Applications},
      volume = {8},
      number = {3},
      pages = {33-39},
      doi = {10.11648/j.ajma.20200803.11},
      url = {https://doi.org/10.11648/j.ajma.20200803.11},
      eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajma.20200803.11},
      abstract = {The incomplete mixing of fuel and the drag induced in the engine are the main problems encountered in scramjets. Proper mixing of fuel can be achieved if the fuel is injected from the inlet of the engine. The fluid domain of Busemann Inlet at Mach 7 with boundary layer fuel injection using slot injectors along the wall was simulated with hydrogen fuel. Static pressure ratio at throat and inlet, along with Mach number at the throat were the design parameters of the Busemann inlet. Hydrogen fuel injection at two different equivalence ratios (0.3 and 0.7) was simulated successively at a temperature of 100 K and Mach 2.5. The state of mixing was studied for three different injection angles (30°, 45°, and 60°) for different equivalence ratios. The injection angles do not have a substantial effect on the hydrogen fuel mixing with the mainstream flow for equivalence ratio 0.3 Whereas, the dispersion of fuel increases as the increase in injection angles for equivalence ratio 0.7. But the total pressure recovery is maintained to the design value for equivalence ratio 0.3 rather than 0.7. Similarly, 45° fuel injection maintains a higher total pressure recovery than in other injection angles of 30° and 60°. Injection technique other than slot injection can be used to study further the effect of fuel mixing in Busemann Inlet.},
     year = {2020}
    }
    

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  • TY  - JOUR
    T1  - Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7
    AU  - Kamal Darlami
    AU  - Rajan Bhandari
    AU  - Abhishek Pandey
    AU  - Sanjeev Adhikari
    AU  - Sabin Subedi
    Y1  - 2020/12/16
    PY  - 2020
    N1  - https://doi.org/10.11648/j.ajma.20200803.11
    DO  - 10.11648/j.ajma.20200803.11
    T2  - American Journal of Mechanics and Applications
    JF  - American Journal of Mechanics and Applications
    JO  - American Journal of Mechanics and Applications
    SP  - 33
    EP  - 39
    PB  - Science Publishing Group
    SN  - 2376-6131
    UR  - https://doi.org/10.11648/j.ajma.20200803.11
    AB  - The incomplete mixing of fuel and the drag induced in the engine are the main problems encountered in scramjets. Proper mixing of fuel can be achieved if the fuel is injected from the inlet of the engine. The fluid domain of Busemann Inlet at Mach 7 with boundary layer fuel injection using slot injectors along the wall was simulated with hydrogen fuel. Static pressure ratio at throat and inlet, along with Mach number at the throat were the design parameters of the Busemann inlet. Hydrogen fuel injection at two different equivalence ratios (0.3 and 0.7) was simulated successively at a temperature of 100 K and Mach 2.5. The state of mixing was studied for three different injection angles (30°, 45°, and 60°) for different equivalence ratios. The injection angles do not have a substantial effect on the hydrogen fuel mixing with the mainstream flow for equivalence ratio 0.3 Whereas, the dispersion of fuel increases as the increase in injection angles for equivalence ratio 0.7. But the total pressure recovery is maintained to the design value for equivalence ratio 0.3 rather than 0.7. Similarly, 45° fuel injection maintains a higher total pressure recovery than in other injection angles of 30° and 60°. Injection technique other than slot injection can be used to study further the effect of fuel mixing in Busemann Inlet.
    VL  - 8
    IS  - 3
    ER  - 

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Author Information
  • Department of Mechanical and Aerospace Engineering, Pulchowk Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal

  • Department of Mechanical Engineering, Thapathali Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal

  • Department of Mechanical Engineering, Thapathali Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal

  • Department of Mechanical Engineering, Thapathali Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal

  • Department of Mechanical Engineering, Thapathali Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal

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