Probabilistic loads and stress analysis methods are presently applied to the second-stage blade of the SSME's high-pressure fuel turbopump, in order to illustrate how loads and stress responses can be quantified probabilistically and how the sensitivity of such component- and engine-level independent variables as engine inlet temperatures and local seal wear within the turbopump can be determined. Attention is given to a method for the derivation of probabilistic pressure, temperature, and centrifugal steady-state load descriptions of this second-stage blade from the top of the airfoil to its intersection with the firtree. Dependent-load random variables are obtained from a multilevel physical model in which duty cycle-dependent deterministic loads and related probabilistic variations are accounted for.


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    Titel :

    Probabilistic structural analysis of space propulsion system turbine blades


    Beteiligte:
    Newell, J. F. (Autor:in) / Rajagopal, K. R. (Autor:in) / Ho, H. (Autor:in)

    Kongress:

    AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference ; 1989 ; Mobile, AL, United States


    Erscheinungsdatum :

    01.01.1989


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






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