Turbomachinery aeroelasticity is gaining renewed interest in the light of current trends, which tend toward thinner blade designs that are not only highly loaded, but also have minimal weight. This necessitates studies of many unsteady aerodynamic phenomena that now occur in acute forms. The present paper investigates the aerodynamic influence of vibrating blades in a compressor cascade using a two-dimensional cascade of airfoils subjected to controlled oscillation. In particular, the pressure distribution and moment on a given airfoil, when its two neighboring airfoils are oscillating sinusoidally at specified phase-difference angles, are investigated. The experimental results are used to establish the relation between the pressure field experienced by the central airfoil and the phase difference between the oscillating blades. The computational results are used additionally to study the secondary phenomenon of flow separation observed when the pressure distribution is such that the local flow incidence to the stationary airfoil is increased. Both the effects are examined quantitatively from the point of the flow being governed by the axial pressure gradient, showing how the geometry of the boundaries, together with the localized flow accelerations, can affect the global flowfield to cause varying amplitudes and phases of unsteadiness in the load.


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    Title :

    Aerodynamic Influence of Oscillating Adjacent Airfoils in a Linear Compressor Cascade



    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040



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