An experiment was carried out on a first stage rotor blade in the compressor of an SO-3 engine to explain the reasons for its failures. The natural frequencies of rotor blades were measured and the tip-timing measurement of rotor blade was done in an engine working at various speeds. Various operation conditions were assumed, such as the presence of a foreign bodies in the engine inlet. Structure and flow calculations were carried out to compare the experimental results. The finite element method was used to calculate the natural frequencies of a mistuned bladed disk. The Fluent code was used to calculate the unsteady forces acting on rotor blades. The mistuned bladed disk was forced to vibrate when rotating at 15000 rpm. Three bladed-disk models were taken into consideration. In the model A, where all the blades had a first natural frequency of 346 Hz, no mistuning was assumed. In the model B, where the natural frequencies of the blades changed from 334 Hz to 359 Hz, a 3.6 % mistuning was assumed. Finally, in the model C ehere the natural frequencies changed from 318 Hz to 385 Hz, a 9.5 % of mistuning was done. The maximum blade stress in the model B increased by 36 % in relation to the model A, whereas, in the model C, the increase of maximum blade stress was only 26 %.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Dynamic analysis of first stage compressor bladed disk of an aircraft engine


    Beteiligte:
    Rzadkowski, R. (Autor:in) / Drewczynski, M. (Autor:in) / Solinski, M. (Autor:in) / Maurin, A. (Autor:in) / Maciejewska, A. (Autor:in) / Szczepanik, R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2011


    Format / Umfang :

    9 Seiten, 5 Bilder, 1 Tabelle, 17 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch