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Diagnostics of acoustic properties of the combustion zone by means of periodic changes in the nozzle throat area

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Combustion, Explosion, and Shock Waves Aims and scope

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Abstract

A mathematical model is proposed, which allows calculating the amplitude of forced pressure oscillations in the combustor of a liquid-propellant rocket engine, caused by periodic changes in the nozzle throat area, with allowance for acoustic properties of the combustion zone. Results calculated for some particular cases are given.

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References

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Authors and Affiliations

  1. Russian Research Center “Applied Chemistry,”, St. Petersburg, 197198, Russia

    Ya. A. Lisochkin

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  1. Ya. A. Lisochkin
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Correspondence to Ya. A. Lisochkin.

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Translated from Fizika Goreniya i Vzryva, Vol. 44, No. 6, pp. 12–17, November–December, 2008.

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Lisochkin, Y.A. Diagnostics of acoustic properties of the combustion zone by means of periodic changes in the nozzle throat area. Combust Explos Shock Waves 44, 627–631 (2008). https://doi.org/10.1007/s10573-008-0096-8

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  • DOI: https://doi.org/10.1007/s10573-008-0096-8

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