Two dimensional and temperature effects on acoustic cavity tuning and performance in rocket combustors

C. E. Mitchell, F. E. Dodd, T. L. Acker, D. J. Howell

Research output: Contribution to conferencePaper

1 Scopus citations

Abstract

Acoustic cavity performance in liquid propellant rocket engines is assessed using analytical and numerical models. The tuning behavior of cavities in which two dimensional flow is present in both the aperture and backing cavity is predicted through the application of an integral-iterative method of analysis. The effect of both linear and nonlinear mean temperature variations on cavity reactance is included in the analysis. Results of tuning calculations are presented including tuning curves for two dimensional geometries and tuning curves for cavities with strong variations in mean temperature. The stabilizing impact of acoustic cavities on liquid rocket combustors is predicted using a stability model which includes combustion, nozzle and mean flow elements.

Original languageEnglish (US)
Pages11-16
Number of pages6
StatePublished - Dec 1 1989
Externally publishedYes
EventConvection Heat Transfer and Transport Processes. Presented at the Winter Annual Meeting of the ASME - San Francisco, CA, USA
Duration: Dec 10 1989Dec 15 1989

Other

OtherConvection Heat Transfer and Transport Processes. Presented at the Winter Annual Meeting of the ASME
CitySan Francisco, CA, USA
Period12/10/8912/15/89

ASJC Scopus subject areas

  • Mechanical Engineering
  • Acoustics and Ultrasonics

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    Mitchell, C. E., Dodd, F. E., Acker, T. L., & Howell, D. J. (1989). Two dimensional and temperature effects on acoustic cavity tuning and performance in rocket combustors. 11-16. Paper presented at Convection Heat Transfer and Transport Processes. Presented at the Winter Annual Meeting of the ASME, San Francisco, CA, USA, .