The purpose of this paper is to study experimentally the effect of transition and also the roughness height on the flow structure of the shock wave boundary layer interaction in the blades passage of a compressor cascade.

    Design/methodology/approach

    A model of a turbine compressor passage was designed and assembled in a transonic wind tunnel. In the experiment, the distributed roughness with different heights and locations was used to induce transition upstream of the shock wave.

    Findings

    Recommendation regarding the roughness parameters for the application depends on what is more important as goal, whether the reduction of losses or unsteadiness. In case if more important are the losses reduction, a good choice for the roughness location seems to be the one close to the shock wave position.

    Research limitations/implications

    The knowledge gained by this paper will enable the implementation of an effective laminar flow technology for engines in which the interaction of a laminar boundary layer with a shock wave takes place in the propulsion system and causes severe problems.

    Originality/value

    The paper focuses on the influence of the boundary layer transition induced by different roughness values and locations on aerodynamic performance of a compressor cascade. Very valuable results were obtained in the roughness application for the boundary layer transition control, demonstrating a positive effect in changing the nature of the interaction and also some negative influence in case of oversized roughness height, which cannot be found in the existing literature.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Transition effect on aerodynamic performance of compressor profile


    Contributors:

    Published in:

    Publication date :

    2020-03-19


    Size :

    1 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Investigation of Cooling Effect on the Aerodynamic Performance in the Intercooled Compressor

    Liu, Long-Gang / Li, Xue-Song / Ren, Xiao-Dong et al. | AIAA | 2018



    AERODYNAMIC PROFILE

    RUTTEN JEAN | European Patent Office | 2024

    Free access


    AERODYNAMIC PROFILE

    BRUTYAN MURAD ABRAMOVICH / VOLKOV ANDREJ VIKTOROVICH / POTAPCHIK ALEKSANDR VLADIMIROVICH et al. | European Patent Office | 2020

    Free access