The theory and procedures for determining the characteristics of pressure oscillations in rocket engines with prescribed burning rate oscillations are presented. Analyses including radial and hub baffles and absorbers can be performed in one, two, or three diemsions. Pressure and velocity oscillations calculated using this procedure are presented for the SSME to show the influence of baffles and absorbers on the burning rate oscillations required to achieve neutral stability. Comparisons are made between the results obtained utilizing 1D, 2D, and 3D assumptions with regards to capturing the physical phenomena of interest and compuational requirements.
3D rocket combustor acoustics model
3-dimensionales schalttechisches Modell einer Raketenbrennkammer
AIAA-Papers ; 1-11
1992
11 Seiten, 2 Bilder, 4 Tabellen, 10 Quellen
Aufsatz (Konferenz)
Englisch
3D rocket combustor acoustics model
AIAA | 1992
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