Computational Analysis of Hydrogen-Fueled Scramjet Combustor Using Cavities in Tandem Flame Holder

Sukanta Roga; Krishna Murari Pandey

doi:10.4028/www.scientific.net/AMM.772.130

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 772Computational Analysis of Hydrogen-Fueled Scramjet...

Computational Analysis of Hydrogen-Fueled Scramjet Combustor Using Cavities in Tandem Flame Holder

Abstract:

This work presents the computational analysis of scramjet combustor using cavities in tandem flame holder by means of 3D. The fuel used by scramjet combustor with cavities in tandem flame holder is hydrogen, the fluid flow and the work is based on the species transport combustion with standard k-ε viscous model. The Mach number at inlet is 2.47 and stagnation temperature and static pressure for vitiated air are 1000K and 100kPa respectively. These computational analysis is mainly aimed to study the flow structure and combustion efficiency. The computational results are compared qualitatively and quantitatively with experimental results and these are agreed as well. Due to the combustion, the recirculation region behind the cavity injector becomes larger as compared to mixing case which acts as a flame holder. From the analysis, the maximum Mach number of 2.33 is observed in the recirculation areas.

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Periodical:

Applied Mechanics and Materials (Volume 772)

Pages:

130-135

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.772.130

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Online since:

July 2015

Authors:

Sukanta Roga*, Krishna Murari Pandey

Keywords:

Cavities in Tandem, CFD, Combustion Efficiency, Mach Number, Supersonic Combustion

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References

[1] K.M. Pandey and T. Sivasakthivel, CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software, International Journal of Engineering and Technology, Vol. 3, pp.446-453 (2011).

DOI: 10.7763/ijet.2011.v3.268

Google Scholar

[2] K.M. Pandey, S.K. Reddy K. K, Numerical Simulation of Wall Injection with Cavity in Supersonic Flows of Scramjet Combustion, International Journal of Soft Computing and Engineering, Vol. 2, pp.142-150 (2012).

Google Scholar

[3] D.J. Micka, J.F. Driscoll, Combustion characteristics of a dual-mode scramjet combustor with cavity ﬂameholder, Proceedings of the Combustion Institute, Vol. 32, pp.2397-2404 (2009).

DOI: 10.1016/j.proci.2008.06.192

Google Scholar

[4] S. Yungsterand K. Radhakrishnan, Simulation of Unsteady Hypersonic Combustion around Projectiles in an Expansion Tube. Institute for Computational Mechanics in Propulsion, NASA Glenn Research Center, MS 86/6, Cleveland, OH 44135, USA, Vol. 11, pp.1-12 (2001).

DOI: 10.2514/6.1999-2640

Google Scholar

[5] D. Cecere, A. Ingenito, E. Giacomazzi, L. Romagnosi and C. Bruno, Hydrogen/Air Supersonic Combustion for Future Hypersonic Vehicles. International Journal of Hydrogen Energy, Vol. 36, pp.11969-11984 (2011).

DOI: 10.1016/j.ijhydene.2011.06.051

Google Scholar

[6] K.M. Pandey and S. Roga, CFD Analysis of Scramjet Combustor with Non-Premixed Turbulence Model Using Ramp Injector, Applied Mechanics and Materials, Vol. 555, pp.18-25, doi: 10. 4028/www. scientific. net/AMM. 555. 18 (2014).

DOI: 10.4028/www.scientific.net/amm.555.18

Google Scholar

[7] Y. Pan, G.G. Tan, J.H. Liang, Z.G. Wang, Experimental Investigation of Combustion Mechanisms of Kerosene-Fueled Scramjet Engines with Double-Cavity Flameholders, Acta Mech. Sin., SpringerVo. 27, p.891–897 (2011).

DOI: 10.1007/s10409-011-0470-8

Google Scholar

[8] J. Tu, G.H. Yeoh and C. Liu, Computational Fluid Dynamics, Elsivier Inc (2008).

Google Scholar

[9] P. Gerlinger, P. Stoll, M. Kindler, F. Schneider and M. Aigner, Numerical investigation of Mixing and Combustion Enhancement in Supersonic Combustors by Strut Induced Stream wise Vorticity, Aerospace Science and Technology, ELSEVIER, Vol. 12, pp.159-168, (2008).

DOI: 10.1016/j.ast.2007.04.003

Google Scholar

[10] K.M. Pandey and S. Roga, CFD Analysis of Hypersonic Combustion of H2-Fueled Scramjet Combustor with Cavity Based Fuel Injector at Flight Mach 6, Scientific. Net, Applied Mechanics and Materials, Vol. 656, pp.53-63, doi: 10. 4028/www. scientific. net/AMM. 656. 53 (2014).

DOI: 10.4028/www.scientific.net/amm.656.53

Google Scholar