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

Kamal Darlami; Rajan Bhandari; Abhishek Pandey; Sanjeev Adhikari; Sabin Subedi

doi:doi:10.11648/j.ajma.20200803.11

| Peer-Reviewed

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

Kamal Darlami, Rajan Bhandari, Abhishek Pandey, Sanjeev Adhikari, Sabin Subedi

Published in American Journal of Mechanics and Applications (Volume 8, Issue 3)

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

Views: Downloads:

Download PDF

Share This Article

Twitter
Linked In
Facebook

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

[1]	J. Sislian, "Scramjet Propulsion: Detonation-Wave Ramjets," Progress in Astronautics and Aeronautics., vol. 189, pp. 823-889, 2000.
[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

Plain Text BibTeX RIS

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

Copy | Download

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

Copy | Download

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

Copy | Download

@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}
}

Copy | Download

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 -

Copy | Download

Author Information

Kamal Darlami

Department of Mechanical and Aerospace Engineering, Pulchowk Campus, Institute of Engineering, Tribhuvan University, Kathmandu, Nepal
Rajan Bhandari

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

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

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

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

Download PDF

Sections

Plain Text BibTeX RIS

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

Copy | Download

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

Copy | Download

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

Copy | Download

@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}
}

Copy | Download