Spin testing of high-bypass turbofan engine fan blades discovered that disk bushings at the blade attachment location frequently backed out during operation causing a deep groove to wear into the attachment tang of the blade. Their movement was the result of insufficient interference fit between the fan disk and bushing. Finite element analysis and microscopic examination of the fan blade fracture surface show that the wear groove acts as a stress riser and the site for crack initiation and propagation. Weibull analysis shows that the wear groove significantly reduces the jet engine fan blade LCF life.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Engine fan blade low cycle fatigue testing


    Additional title:

    Niedrigfrequenz-Wechsellast-Ermüdungsprüfung eines Gebläseflügels eines Turboluftstrahltriebwerks


    Contributors:
    Le, D.D. (author)

    Published in:

    Publication date :

    1992


    Size :

    6 Seiten, 8 Bilder, 2 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    Fatigue behavior and climatic cycle testing of rotor blade components

    Drisga, Ivo / Dr.-Ing. (EAE) Glück, Nikolai / Dr.-Ing. Block, Tim Berend et al. | Springer Verlag | 2018


    Probabilistic Simulation of Engine Blade Creep-fatigue Life

    Mahadevan, Sankaran / Mao, Hongyin / Ghiocel, Dan | AIAA | 2002


    Crack Propagation of Compressor Blade on Low Cycle Fatigue Combined with High Cycle Fatigue

    Zheng, G. / Zhao, C. / Zhang, M. et al. | British Library Conference Proceedings | 1994


    Probabilistic Simulation of Engine Blade Creep-fatigue Life

    Mahadevan, S. / Mao, H. / Ghiocel, D. et al. | British Library Conference Proceedings | 2002