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.


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    Title :

    3D rocket combustor acoustics model


    Additional title:

    3-dimensionales schalttechisches Modell einer Raketenbrennkammer


    Contributors:

    Published in:

    Publication date :

    1992


    Size :

    11 Seiten, 2 Bilder, 4 Tabellen, 10 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English