The present paper numerically conducted full-annulus investigation on the effects of circumferential total pressure inlet distortion on the performance and flow field of the axial transonic counter-rotating compressor. Results reveal that the inlet distortion both deteriorates the performance of the upstream and downstream rotors resulting in reduction of total pressure ratio, efficiency and stall margin of the transonic contra-rotating compressor. Regarding the development of distortion inside compressor, the downstream rotor reinforces the air-flow mixing effects and, thus, attenuates the distortion intensity significantly. Under the distorted inflow conditions, the detached shockwave at the leading edge of downstream rotor interacts with the tip leakage flow and causes the blockage of the blades passage, which is one important reason for the transonic contra-rotating compressor stall.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Effect of inlet distortion on the performance of axial transonic contra-rotating compressor


    Beteiligte:
    Liu, Hanru (Autor:in) / Wang, Yangang (Autor:in) / Xian, Songchuan (Autor:in) / Hu, Wenbin (Autor:in)


    Erscheinungsdatum :

    2018-01-01


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Influence of inlet distortion on transonic compressor blade loading

    Rabe, D / Bolcs, A / Russler, P | AIAA | 1995


    Effects of Rotating Inlet Distortion on Flow Stability of an Axial Compressor

    Zhang, Jing / Lin, Feng / Chen, Jing et al. | AIAA | 2007


    Transonic radial compressor inlet design

    Lohmberg, A. | Online Contents | 2003


    Effect of inlet distortion, co-swirl and counter-swirl on axial compressor/fan performance

    Roy, B. / Kumar, H. / Batra, A. et al. | British Library Conference Proceedings | 2000