This paper reports on work completed to develop an analytical method for predicting the transient non-linear response of a complete aircraft engine system due to the loss of a fan blade, and to validate the analysis by comparing the results against actual blade loss test data. The solution, which is based on the component element method, accounts for rotor-to-casing rubs, high damping and rapid deceleration rates associated with the blade loss event. A comparison of test results and predicted response show good agreement except for an initial overshoot spike not observed in test. The method is effective for analysis of large systems.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Blade loss transient dynamic analysis of turbomachinery


    Beteiligte:
    Stallone, M. J. (Autor:in) / Gallardo, V. (Autor:in) / Storace, A. F. (Autor:in) / Bach, L. J. (Autor:in) / Black, G. (Autor:in) / Gaffney, E. F. (Autor:in)

    Kongress:

    Joint Propulsion Conference ; 1982 ; Cleveland, OH


    Erscheinungsdatum :

    01.06.1982


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Blade loss transient dynamic analysis of turbomachinery

    Stallone, M. J. / Gallardo, V. / Storace, A. F. et al. | NTRS | 1983


    Blade loss transient dynamic analysis of turbomachinery

    Stallone, M.J. / Gallardo, V. / Storace, A.F. et al. | Tema Archiv | 1983


    Blade loss transient dynamic analysis of turbomachinery

    STALLONE, M. / GALLARDO, V. / STORACE, A. et al. | AIAA | 1982


    Blade loss transient dynamic analysis of turbomachinery

    STALLONE, M. J. / GALLARDO, V. / STORACE, A. F. et al. | AIAA | 1983


    Turbomachinery Blade Modal Analysis Using Contact Elements

    St-Georges, Lyne / Thomas, Marc / Guerra, Mario | SAE Technical Papers | 2004