Unsteady blade row interactions play an important role in the performance of multi-stage turbomachinery. However, most aerodynamic optimizations of multi-stage turbomachinery are based on mixing-plane steady flow simulations. To take into account the unsteady flow features in the optimization cycle, this paper develops an adjoint-based unsteady aerodynamic optimization system for multi-stage turbomachinery. To the authors' best knowledge, this is the first work in the literature conducting the unsteady adjoint aerodynamic optimization of multi-stage turbomachinery. The unsteady flow equations and the discrete adjoint equations are solved using a finite volume code, with the harmonic balance method adopted to reduce the cost of unsteady simulations. The system is applied to the unsteady aerodynamic optimization of a 1.5-stage compressor. Results show the efficiency and capability of the proposed framework for the unsteady aerodynamic optimization of multi-stage turbomachinery.


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    Titel :

    An Efficient Unsteady Aerodynamic Optimization System for Multi-Stage Turbomachinery


    Beteiligte:


    Erscheinungsdatum :

    2016




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    52.30 Strömungskraftmaschinen, Turbomaschinen / 52.30