An analytical model for determining the free vibration characteristics of advanced composite turbopropellers (prop-fans) is presented. The blade is modeled using a number of straight beam-type finite elements, where the elastic axis of each element is a piecewise straight representation of the curved line of shear centers of the swept blade. The finite-element model is obtained from Hamilton's principle with allowances for: generally anisotropic material behavior, arbitrary cross-sectional properties, large pretwist angles, out-of-plane cross-section warping, and geometrically nonlinear behaviour based upon moderate deflection theory. The natural frequencies and mode shapes of the rotating blade are calculated assuming linear perturbations about the nonlinear static equilibrium position of the blade. This model is sufficiently general to analyze other advanced composite aerospace structures. Numerical results are presented to illustrate the versatility of the method by applying it to 1) a conventional propeller (TRW-Hartzell 101/16) and 2) a highly swept and pretwisted isotropic turbopropeller (NASA SR-3). Excellent agreement with experimental test results is obtained for the lower modes of both the conventional propeller and the advanced turbopropeller.


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    Title :

    Vibration analysis of composite turbopropellers using a nonlinear beam-type finite-element approach


    Additional title:

    Schwingungsanalyse von Verbund-Turbopropellern mit einer nichtlinearen Naeherungsmethode mit finiten traegerartigen Elementen


    Contributors:

    Published in:

    AIAA Journal ; 27 , 11 ; 1606-1614


    Publication date :

    1989


    Size :

    9 Seiten, 9 Bilder, 21 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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