Schlieren visualizations of flowfield structures of supersonic film cooling in a backward-facing step were conducted in a Mach 2.95 suction wind tunnel with the film coolant tangentially ejected through half-Laval nozzles, all of which were designed in Mach 1.5 but with different lip thicknesses. The film coolants were fed with pressures matching the mainstream, and the flowfield changes of supersonic film cooling under different lip thicknesses between the slot and mainstream were clearly visualized under the conditions of the same step and slot heights. When the step height was kept the same, an increase in lip thickness decreased the angle of the shock wave emanating from the upper tip of the lip, and it decreased the strength of the reattachment shock wave when it was larger than a certain value. When the slot height was kept the same, the increase in lip thickness tended to decrease the angles of the shock waves emanating from the upper and lower tips of the lip and reattachment shock waves. This work provides an in-depth understanding of the flowfields of supersonic film cooling near the backward-facing step and may be used as a reference for the design of supersonic film cooling.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Effects of Lip Thickness on the Flowfield Structures of Supersonic Film Cooling


    Beteiligte:
    Song, Changqing (Autor:in) / Shen, Chibing (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2018-12-24


    Format / Umfang :

    7 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch