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.


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    Title :

    Blade loss transient dynamic analysis of turbomachinery


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

    Conference:

    Joint Propulsion Conference ; 1982 ; Cleveland, OH


    Publication date :

    1982-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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