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Control of thrust characteristics of a scramjet combustor with vibrational combustion using acoustic resonators

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Combustion, Explosion and Shock Waves Aims and scope

Abstract

The effect of a resonator on the thrust characteristics of a scramjet combustor with vibrational combustion of hydrogen is studied experimentally. A cylindrical tube with a confuser entrance was used as a combustion chamber. The centerline of the resonator is perpendicular to the combustor axis. It is shown that the thrust characteristics of the combustor depend on the resonator position relative to the combustor and on the linear dimensions of the resonator.

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References

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Authors and Affiliations

  1. Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, 630090, Novosibirsk

    V. K. Baev, D. Yu. Moskvichev & A. V. Potapkin

Authors
  1. V. K. Baev
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  2. D. Yu. Moskvichev
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  3. A. V. Potapkin
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Additional information

Translated fromFizika Goreniya i Vzryva, Vol. 36, No. 5, pp. 3–6, September–October, 2000.

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Baev, V.K., Moskvichev, D.Y. & Potapkin, A.V. Control of thrust characteristics of a scramjet combustor with vibrational combustion using acoustic resonators. Combust Explos Shock Waves 36, 553–556 (2000). https://doi.org/10.1007/BF02699516

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  • DOI: https://doi.org/10.1007/BF02699516

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