A study of the residual stresses and distortion processes in aircraft aluminium forgings was performed by finite element modeling. Results showed that the use of 7050-T7451 thick plate in place of the 7050-T7452 compression stress-relieved forgings improved the machining issues and distortion in parts. The reduction of residual stresses also enabled improvement in fatigue life, corrosion resistance, mechanical properties and performance of the parts.


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    Title :

    Residual stress analysis of aircraft aluminum forgings


    Contributors:
    Walker, D.M. (author) / Hom, R.Y. (author)

    Published in:

    Publication date :

    2002


    Size :

    4 Seiten



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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