On the Supersonic Combustion of Hydrogen around a Conical Obstacle Considering Variable Specific Heats with Application to Scramjets

Sorin Berbente; Daniel Eugeniu Crunteanu; Corneliu Berbente

doi:10.4028/www.scientific.net/AMM.811.162

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 811On the Supersonic Combustion of Hydrogen around a...

On the Supersonic Combustion of Hydrogen around a Conical Obstacle Considering Variable Specific Heats with Application to Scramjets

Abstract:

One proposes a combined analytical-numerical method for the supersonic combustion around a conical obstacle, considering variable specific heats with temperature. One important aspect is to avoid the dissociation what is not possible if normal detonation waves (of Chapman-Jouguet type) occur. The Clarke model where the detonation wave is separated in a shock wave and a deflagation wave is able to reduce the temperature. Here conical waves are used. In order to characterize the combustion speed and intensity, new parameters are proposed. A comparison with the Chapman-Jouguet combustion is also presented.

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Periodical:

Applied Mechanics and Materials (Volume 811)

Pages:

162-166

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.811.162

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Online since:

November 2015

Authors:

Sorin Berbente, Daniel Eugeniu Crunteanu*, Corneliu Berbente

Keywords:

Air Exces, Average Specific Heat, Equivalent Mach Number, Equivalent Solid Cone

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References

[1] J.F. Clarke, D.G. Petty, The supersonic flow Associated with a Conical Flame Sheet, The Aeronautical Qarterly, XXI, nov. (1970).

DOI: 10.1017/s0001925900005527

Google Scholar

[2] Mc. Bride B.J., Zehe, M.J. and Gordon S.: NASA Glenn Coefficients for Calculating Thermodynamic Properties of Individual Species, NASA/TP-2002-21556, September (2002).

Google Scholar

[3] Racoţi D., Berbente C., Analysis of complex chemical models in hydrogen scramjet combustion, The First European Conference on H2–FUEL CELLS–MILLENIUM CONVERGENCE, Sept. 21-22, Bucharest 2007, ( on CD at Nr. 125).

Google Scholar

[4] C. BERBENTE, D. CRUNŢEANU, D. RACOŢI, On the interpretation of certain thermodynamical functions and coefficients for ideal gases in terms of average values within temperature intervals, TERMOTEHNICA, Anul XIII, nr. 1/2009, pp.33-42.

Google Scholar

[5] Crunteanu Daniel-Eugeniu, Racoti Dan, Berbente Corneliu, Analysis of normal combustion waves in CH4-air system, Applied Mechanics and Materials Vol 656 (2014).

DOI: 10.4028/www.scientific.net/amm.656.101

Google Scholar

[6] Andrew Higgins, Steady One-Dimensional Detonations, Shock Wave Science and Technology Reference Library, Vol. 6: Detonation Dynamics, DOI 10. 1007/978-3-642-22967-1_2, pp.33-105, Springer-Verlag Berlin Heidelberg, (2012).

DOI: 10.1007/978-3-642-22967-1_2

Google Scholar