As part of new aircraft engine development, fracture critical components are identified and studied. The engines turbine disks require careful consideration due to the many sharp notches into which compressor blades are inserted. These dovetail notches have varying geometries dependent upon the stage of the compressor in which the turbine disk is located, and pose a difficult problem for the fracture mechanics analyst. This paper describes the fatigue behavior of cracks located at two 'dovetail' notch geometries. Fatigue tests with transparent polymer models produced changes in crack size and shape as a function of elapsed cycles. Numerical stress intensity factor solutions were determined for both through-cracks (using a finite element code), and corner cracks (using a boundary element code) located at the notch bore. The numerical stress intensity factor solutions were verified by predicting fatigue lives, crack sizes and shapes for the experimental results. These predictions showed that the numerically determined stress intensity factors accurately predict fatigue lives, as well as crack size and shape for the dovetail geometries.


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    Title :

    Analysis of cracks at deep notches


    Additional title:

    Analyse von Rissen an tiefen Kerben


    Contributors:

    Published in:

    Publication date :

    1996


    Size :

    12 Seiten, 8 Bilder, 6 Tabellen, 18 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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