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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    3D rocket combustor acoustics model


    Weitere Titelangaben:

    3-dimensionales schalttechisches Modell einer Raketenbrennkammer


    Beteiligte:
    Priem, R.J. (Autor:in) / Breisacher, K.J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1992


    Format / Umfang :

    11 Seiten, 2 Bilder, 4 Tabellen, 10 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    3D rocket combustor acoustics model

    PRIEM, RICHARD / BREISACHER, KEVIN | AIAA | 1992




    Experiment of Rocket-Ram Annular Combustor

    Yatsuyanagi, N. / Sakamoto, H. / Sato, K. et al. | British Library Conference Proceedings | 1993


    Finite area combustor theoretical rocket performance

    Gordon, Sanford / Mcbride, Bonnie J. | NTRS | 1988