The creep-fatigue behavior of a fully impingement-cooled blade for four cyclic cases was analyzed by using the Elas 55, finite-element, nonlinear structural computer program. Expected cyclic lives were calculated by using the method of Strainrange Partitioning for reversed inelastic strains and time fractions for ratcheted tensile creep strains. Strainrange Partitioning was also applied to previous results from a one-dimensional cyclic analysis of a film-impingement-cooled vane. The analyses indicated that Strainrange Partitioning is more applicable to a constrained airfoil such as the film-impingement-cooled vane than to the relatively unconstrained fully impingement-cooled airfoil.STAR category 39


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    Title :

    Cyclic Structural Analyses of Air-Cooled Gas Turbine Blades and Vanes


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Engineering and Manufacturing Meeting ; 1976



    Publication date :

    1976-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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