Experiments have been performed in a three-stage axial compressor to investigate unsteady stator boundary-layer transition in an embedded stage environment. Quasi-wall shear stress data have been acquired on the suction surface of the second stage stator, in addition to unsteady flow angle measurements at the stator inlet. With two rotor blade rows upstream of the instrumented stator, blade row interactions representative of a multistage environment are present. The different blade counts for the upstream rotors provide an unsteady flowfield at the stator inlet featuring a beating pattern. There is no portion of fully laminar boundary-layer flow on this vane. The vane boundary layer is transitional near the leading edge, and transition to a fully turbulent boundary layer is complete by 45% suction side length. The presence of the rotor 1 wakes, when arriving in between the rotor 2 wakes, increases the normalized quasi-wall shear stress in the leading-edge region by 4% and decreases the amount of laminar transitional flow.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Unsteady Vane Boundary Layer Response to Rotor–Rotor Interactions in a Multistage Compressor


    Contributors:

    Published in:

    Publication date :

    2014-02-12


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Unsteady Vane Boundary Layer Response to Rotor-Rotor Interactions in an Embedded Compressor Stage

    Smith, N. / Key, N. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2013


    Multistage compressor stator/rotor interaction

    TWEEDT, D. L. / OKSHI, T. H. / HATHAWAY, M. D. | AIAA | 1985