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 language | English (US) |
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| Pages | 11-16 |
| Number of pages | 6 |
| State | Published - 1989 |
| Event | Convection Heat Transfer and Transport Processes. Presented at the Winter Annual Meeting of the ASME - San Francisco, CA, USA Duration: Dec 10 1989 → Dec 15 1989 |
Other
| Other | Convection Heat Transfer and Transport Processes. Presented at the Winter Annual Meeting of the ASME |
|---|---|
| City | San Francisco, CA, USA |
| Period | 12/10/89 → 12/15/89 |
ASJC Scopus subject areas
- Mechanical Engineering
- Acoustics and Ultrasonics