Splitter plates usable as aeroelastic detuner devices for supersonic flutter in turbomachinery, through the introduction of both aerodynamic and structural detuning to enhance aeroelastic stability, are presently considered by a mathematical model. The model demonstrates that aerodynamic detuning is due to both the alternate circumferential spacing of the full chord airfoils and the variable circumferentially spaced splitters between each pair of full chord airfoils. Structural detuning is based on the lower natural frequencies of the splitters, by comparison with the full chord airfoils. The model's application to two unstable rotors demonstrates enhanced torsion mode flutter stability through the incorporation of splitters, where the critical parameters are chord length and the circumferential and axial locations of the splitters.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Splitter blades as an aeroelastic detuning mechanism for unstalled supersonic flutter of turbomachine rotors


    Contributors:
    Topp, D. A. (author) / Fleeter, S. (author)

    Publication date :

    1986-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Supersonic unstalled flutter

    Adamczyk, J. J. / Goldstein, M. E. / Hartmann, M. J. | NTRS | 1978


    Supersonic unstalled flutter

    Adamczyk, J. J. / Goldstein, M. E. / Hartmann, M. J. | NTRS | 1978


    Supersonic Unstalled Flutter

    J. J. Adamczyk / M. E. Goldstein / M. J. Hartmann | NTIS | 1978